SCIENTIFIC ABSTRACT SHCHUKIN, V. B. - SHCHUKIN, YE.A.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001548920014-7
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Document Release Date: August 23, 2000
• Sequence Number: 14
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

A-IMAZIN , V.A. ; :34CHUKIN , V,B~ ; RM-11 , III.S.
Detection of the leucopcietic activity of blood plasma in
diseases of the biood system. Lab, delo no.3:160-165 165.
(MIRA 18:3)
1, Ka-fedra fakul'tetskoy terapii (zaveduyushchiy - prof. T.S.
istmanova) ! Leningradskogo meditsinskogo instituta im. I.P.
Pavlova.

SHCHUKIR, V.F. inzhener.
Investigating the moment of force acting on units of a continuous
steel casting installation. Stall 17 no.4:320-322 Ap 157.
NLRA 10:5)
I.Novo-Tullski7 metallurgicheaki7 zavod.
(Steel--Blectrometallurgy)
(Mechanics)

SECEMIM., V. F., CP-ndidate Ttch Sci (diss) -- '~Dmerimental inves ttiga tion oi- th,5
l, 9 1, p Jfai
c.-ff,~cts in Uie contLiTacus casting of steel". Moscaw, 195 - 1- _p ( n
Adm~in of Sri F.,?s and resign orcnnizatiomq of -,;he Gosplan USSR, Centl6al S-1 Res
lq-)Q ].()Q)
Inst of Toch awl brchlyrbuilding, Ts,111THTNish), .1.50 roplef, (n, ITO PTI - $

SHCMM IN, V. I.
Organization of the operation and repair of building machinery.
FAnerg.etroi. no-5:197-201. '58. (MIRA 12:5)
1. Glavnyy mekhanik ru7byshevgidrostroya.
(Volga Hydroelectric Power Station--Building machinery)

KAGAN. V.N. , S.H'HUK1N, V. 1. ; TSEGEL'SK IT, V.L. , laz1h.. , nauchn.
red ,-PATENOVSKAYA, M,L red-Jzd-va, IYCCHALINA, 11-S-1,
tekhn, red
[Ga5 welding and cutting in construction] Gazovaia, svarka
i rezka v stroitel~stve, Moskva, Gosstroilzdat, 1963. 1131p.
(MIRA 16. 11)
(Ga-= weld~.ng and cutting)

- , i - ~ I ~, - ~ 1 ! , jI'\ ~
PHASE I TREASURE ISLAND BIBLIOGRAPHICAL REPORT AID 451 - I
BOOK Call No.: AF640322
Author: SHCHUKIN, V. K., Kand. of Tech. Sci.
Full Title: ASSAULT ON THE SKY (HOW TO STUDY THE ATMOSPHERE)
Transliterated Title: Shturm neba (Kak izuehayetsya atmosfera)
Publishing Data
Originating Agency: None
Publishing House: State Publishing House of Technical and
Theoretical Literature
Date: 1953 No. pp.: 48 No. of copies: 150,000
Editorial Staff: None
Text Data
Coverage: This monograph of the series "Scientific-Popular Library" de-
scribes atmospheric phenomena and their investigation in an extremely
popular form. It is a propaganda book asserting that all discoveries
in meteorology and all achievements in aviation are due to Russian
scientists. The booklet contains brief descriptions and illustrations
of various meteorological instruments. It mentions ascensions of
Soviet flyers on aerostats and stratosphere balloons, with names, dates
and attained heights (p. 21-24). It describes briefly sonde balloons
the radiosonde balloon of Prof. P. A. Molchanov, rockets (pp. 29-37,
TABLE OF CONTENTS PAGE
Introduction 3
1/2

-rot-'-ass.v v zIA-kc-st'nore, ktivn,-.-kii jri-~efele,,,r2khil!
Oborons-i

BOGARSKIY , Andrey Vladirnircvich; STICEUKRI, V,K,
[Working processes in liquid-fuel jet enginonPlabochie
protsessy v zhidkostno-r~aktivnykh dvigateliakh, 14oskva,
Gos.izd-,vo obor, prollIrshl,,,, 1953. 424 P. (MIRA 15:8)
(Jet propulsion)

AID P - 4363
Subject USSR/Heat Engineering
Card 1/1 Pub. 110-a - 8/19
Authors Shchukln, V. K., Kand. Tech. Sci. Kazan Aviation
Institute
Title The relation between the dimensions of a one-stage
flow-compressor and Its efficiency.
Periodical Teploenergetika, 4, 27-35, Ap 1956
Abstract Research on this relationship was made to determine
the efficiency and uniformity of exit air flow. A
comparison is made between flow-compressors with
internal and external air intake. 13 diagrams.
Institution None
Submitted No date

AUTHOR: Shchukin, V.K. soV/147 -58-1-14/22
TITLE: ~Ioii Ratio of a Jet Engine for 11inimum
Transverse Dimensions (Stepen' szhatiya kompressora,
obespechivayushchaya minimal'nyye poperechnyye gabarity TRD)
PERIODICAL: Izvestiya Vysshikh Uchebnykh Zavedeniy,
Aviatsionnaya Tekhnika, 10/58, Nr 1, PP 113-125 (USSR),
ABSTRACT: An engine with a two-stage compressor and no re-heat
is discussed. The transverse dimensions are conveniently
evaluated in terms of the "frontal thrust". The intake, com,-
pressor, combustion chamber, turbine and exhaust Dipe are con-
sidered separately. In the first part of the article,
expressions are given for the "frontal thrust" in the various
parts of the engine. In the secoad Dart, the compression ratio
corresponding to the maximum "frontal thrust" is aiscussed,
Finally, the optimum, corapression ratio and the maximum. "frontal
thrust" are plotted against an undefined parameter M1 h for
various local velocities and temDeratures. It aDDears that
an increase in the local velocity causes an increase in the
optimum compression ratio and a reduction in the maximum,
"frontal thrust". At sonic sDeeds, v.Then the transverse
Uard 1/2

SOV/147 -58-1-14/22
On the Compression Ratio of a Jet BnCine for L!i-ri-mum Transver e
Dim;ansions
dimensions are determined by the compressor, the local
velocity has little effr~ct on the maximum "frontal
thrust" and at large supersonic speeds a reduction in the
local velocity leads to an increase in the capacity of
the turbine, which in these conditions is largely the
limiting criterion. The optimum compression ratio
increases with K where 5 is the ratio of the r.-D-m.
in the second stage to the r.p.m. in the first stage of
the compressor. There are 9 fi-gures and 2 tables
ASSOCIATION: Kafedra teplovykh dvigateley, Kazanskiy aviatsionnyy
institut (KazanlAviation Institute, Chair of Heat
Engines)
SUBMITTED: October 4, 1957
Card 2/2 1. Jet engines--Design 2. Combustion chadbers--Analysis
3. Compressors--Applications

SOV/14?-58-3-13/18
AUTHOR: Shchukin , V. K.
TlTiE: Boosting of Turbo-Jet Engines in High Speed Flight by
injection of a Liquid khead of -the Compressor
(Vozmozhnosti f orsirovaniya TRD -vpryskom zhidkosti pered
kompressorom pri bol'shikh skorostyakh poleta)
PEIZIODICAL:Izvestiya Vysshikh Uchebnykh Zavedeniy A-viatsionnaya
Tekhnika
pp 105-111 (USSR)
Nr 3
1958
,
,
,
kBSTRACT: Augmentation of the thrust of turbojet engines can be
obtained without a change of the turbine speed by
injecting a liquid in front of the turbine compressor
at a station between X and 1 (Fig.1). The liquid
evaporates and this increases the pressure and decreases
the temperature at the given station. As a result of
these changes the mass flow of the air through the engine
is increased as.well as the pressure difference through
the nozzle givihg eventually an increased thrust.
Relating the expressions for the thrust of a boosted
engine and for the engine without boosting when working
at its maximum rating we get Eq.1, where w - velocity
Card 1/6 of flow; P M and T31E - stagaation pressure and temperature;

SOV/147-58-5-13/18
Boosting of Turbo-Jet Engines in High Speed Fiight by Injection of
a Id quid khead of the Compressor
a coefficient in the mass flow equation;
quantity of the injected liquid per kg of air;
P /Ph - rate of boosting of the engine;
X ;1duced velocity;
q(X) - gas dynamics function;
0 - coefficient expressing the mass flow increase as a
result of addition of fuel and liquid.
The indices denote the respective stations in the engine
as shown in Fig.1i the index o denotes the boosted
range of work of the engine. Relating the specific
liquid consumption during the boosted cycle to the
specific fuel consumption of the unboosted engine at
the maximum output (conditions of flight being the same
in both cases) vie get Eq.2,,
. whe re T~ ~:W/cph and Cr
is the specific consumption of the fiquid pL~,r kg of
thrust of the boosted engine,
C h - is specific fuel consumption without boosting;
- quantity of fael per kg of air used without boosting
the engine; that balance between x and 1 gives
Card 2/6 Eq.3, where t - teraperature in OC; OpB - specific heat

SOV/147-58-3-13/18
Boosting of Turbo-Jet Engines in High Speed Flight by Injection of
a Liquid Ahead of the Compressor
of air (per unit weight); r - latent heat of
vaporization of the liquid; tx and cm - temperature
and specific heat of the liquid; epr7 - specific heat of
the vapour of the liquid. Relation between specific
consumption of fuel in boosted and unboosted engine is
given by Eq.4, while balance of heat for the combustion
chamber yields Eq.5, where S - is the weight content of
the combustive component in the injected liquid. Hu and
Hut - calorific value of the fuel and the combu~tive
component of the liquid; f ~nd J 0 - coefficient of the
completeness of combustion of fuel and liquid. The
economy of the engine work with boosting is given by the
total specific consumption (Eq.6). The amount of liquid
which can be injected depends on the design of the
compressor ana tne following two factors: 1) saturatuion
limit of the given liquid vapour in the air; 2) limiting
speed of air flow at the entrance to compressor which
must remain subsonic. If the liquid is a mixture of water
Card 3/6 and alcohol Eq.7 and 12 give the limiting amount of

~30 V/147-58- 7-13/18
Boosting of Turbo-Jet i!bagines in High Speed Flight by Injection of
a Liquid Ahead of the Coapressor
mixture which can be injected, Here dpVED and (IPRED -
water vapour content in one kg of the air intake
in the state of saturation; 9B and gop - weight content
of water and alcohol per kg of air intake; ys and
ySUK - specific weight of dry saturated vapour and dry
air; k - adiabatic index; To - relative blimidity of the
atmospheric air (air intake). The temperature ratio of
Eq.? may be taken as given in Eq.,13 and press-ure rat-io
as given by Eq.14. At the start and at low speeds the
amount of admissible liquid injection is small but, it
grows with velocity of flight, and height as shovim in
Fig.2. It has been assumed that the engine is always
r,anning at its maximUM zpeed,, Augmentation of thrust
and changes in economy due to boosting for a giv-en
engine depends on the amount of injected liq~aid, main
parameters of the design and tha conditions of flight.
This shown in Fig.3 (the speed is given by -M- = 1~7;
the hei4it is 11 1un and the compression ratA is
Oko - 11,8)~ With compression ratio greater than. 8 it
Card 4/6 nas been assumed that the engine is of two-cas'cade type;

S OV/"-:,-4 7-5, 8 - 3-13/18
Boosting of Turbo-Jet Engines in High Speed F!iF)at by Injection of
J
a Liquid Ahead of the Compressor
and the regulation of the engine to obtain the maximum
thrust was assumed to be achieved by maintaining constant
the revolutions of the first cascade of the compressor
and by keeping constant the temperature at the inlet to
the turbine. Water is taken as the injected
Finally it was assumed that the coefficient of Pi-Iness
ofcombustion is the same in the boosted and unboosted
flight. Fig.4 shows that the rate of boosting of the
engine varies only slightly vr-th the charactieristio
parameters of the engine (i.e. compression ratirr1rt
and the temperature of gases before the turbine kro
T N) but with larger compression ratio it grows faster.
F~E.5 shows the variation of the rate of boosting with
the speed of flight. It can be seen that the extra
thrust increases with speed and beight but at the same
time the economy deteriorates; the overall fuel and
liquid consumption increases. It must be mentioned that
when boosting an engine by means of injection of a liqaid
ahead of the compressor it may prove necessary to J_r.-:~ease
Card 5/6 the diameter of the air iaQ-akes in order to admit a

SOV/147-58-3--13/18
Boosting of `2urbo-iet Engines in High Speed Flight by Injection of
a Liquid Ahead of the Compressor
larger air intake due to injected liquid (this applies
mainly when boosting takes place in conditions of
.maximum air flow). This will lead to increase in the
thrust needed per unit of frontal area as shown in
Eq.15, where I= - thrust developed -per unit of frontal
area based on The air intake; GB=--weight rate of flow
of the air through the engine; /P where P
Py = PY-v Y y is the
specific thrust. There are 5 figures.
ASSOCIATION: Kazanskiy Aviatsionnyy Institut, Kafedra Teplo-,-ykh
Dvigateley (Kazan' Institute of Aeronautics, Chair of
Heat Engines)
SUBMITTLD: 21st November 1957.
I(Jard 6/6

SUV/ 1LL7- 58-1-1
-11/15
TITLE Boos-uinj Turbojet En6ines b-,- Injection of Io7mnressed Air
befor,z! t~.e Compressor (Forsirovaniyc. czhatiyem
voz(I'uk:ha Dered Ii-ompressorom)
PERIODI~;.r'-L; Izve~~tiya Vysshikh UchebriVII-1h Zavedeniy, Aviats-ionnaya
telklhnika,, 191,-6, P-r 4, pp 92-100 (USSR)
ABSTRAUIP-. Fi~,- I -
shov;s diag-i-am-;,iiatically the system. Compressed air
fl-'Oal ti boLule through noz--le-- (ducts) and
i,.7. int-roduced into the engine upstreata of the coapressor.
Th-is r~-lsuits in a hi6her overall com,pression ratio of
~-!O System, a higher gas flow and finall-y an increased
t I - u S- The coaDressed air injectors analysed in this
article consisted of four active n--,zzles and the relative
lanq-,th of :;-he mixinS chamber was 2 (with_12 nozzles
;-~ , , ien 1, and
ch~iracterist----s were obtained vil
,,iu~ 0 'hey ar-~~ s'ightly inferior). The increase of
~Uhe thiust due to boostint~ is limited by the capacity of
the air int,-ike cf tile engine. -~Et can -be exDressed thus:
Cra apa
GSU-Cr,"_1 cr (1)
a r --i 1./'17 B C! Bo)

'~Tl 1 LLr7- 58,-LL- 1 l/ 1 5
_L
Eoo_stin~~ Turb 04 et 'Sni_~Jnes by CO~7~;T'e~S=;"' _jj' 71-fore
the C-ompressor
This equa-6ion relates the mass flow of Uhe air through
0
~he i nlectors at tho liriiit of their ranf~e of operation
-IV i ti I that throue..h bhe air wiiere:
G
I - liuiitin~; oir flo%,~ tbroui_,h the injectors,
np
GB - air flow throuL_,.-L the un-boosted enSiae,,
O
a'-,
Cl d CF
-pressure coefficients of the sub-critical
a. E
T)arts of t-he active nozzles and the inlet
part of the passive air duct, respectively,
-
~ - the ratio of
the full active*and -Dassive
a air uressures,
- the ratio of Z:he Dassive and active air
sta-nation temperatures,
- reduced velocity of the air at the intake
C. of the un-boosted e.P_I:,-ine,
q - -)-as dy-namics funcrion,
n - coefficient of ejecti6n.
Fig 2 shows dependence ~)f the extra capacity of the air
'
bard 2/7 intak e on the -oaraineters 3-f the inject
ors at ~4 = 1

SOV/147-58-zL-11/15
Boostin- Turbojet by Injection of C'o--pressed AiT Before
t,- J -
the Compressor
dui-inb starti_rb: conditiori-_. ;~he rela-cion
nP
esti-.,iated periml-ntal data. and it was
assuated bil-at aa crB C',
A
--..-;ves the -e~-,i-e of the en6ine during s"arting
CI of bocstin,~,
conditions ,~onst and critical pressure gradient in
e t u rb i _,ae _11.e re
thr7_~.st of ttie b,~,osted en6ine,
P thrust of tLe un-boosted engine.
increase in CD
-/overall compression ra-cio due to injectors,
and I compression ratios across the compressor
TUK ~,Jl K 0 -of the boosted and iuiboosted engine
Card 3/7 r e s -.) , _a c (" i,! - e 11 -1 .

~ : ti 7114 ~/7- rl~,)'-4- I 1/ 15
o (,, S t i n, , I'u ~, u ~) j e t-L n e s L,: f 1 n .4 e c t ia n o f1 p r e s E, e d -A- i r B e I" o r C.
As proved bv the aut.I-Lor it', his pLtb 14 cation; "SimultarLeous
o-ce-ration of a aech~~ical coapres~-ur --nd q jet
co!apressor (injector) "'Kazan' Insti-~;ute of ~'-~eronautica.J-Lhg.;
Pub-licati-on XLI relatiens (3) and (4) relate the
performance cf the two components, where:
- lompression ratio o~' the injector
(JA - ~~--essure coef-47'icient of che diffuser without
injec Lcr,
- an,,;Ia of diffusion cf the passap~e C-1,.
-CA and T-I - stagnation pressure and temperatare of the
flOW5
F cro--s-sectional area of the duct.
F (botto-m ,-rar-rs) shovis the characteristics of the
injector and the upper ~-,raphs represent some intermediate
stages of the relation (4). in the analysis of the
co,apres~-ion ratio throuSh the compressor, the adiabatic
nrocess vas assumed. The economy of the engine was
assessed by relaUing the specific fuel ccnsumption v.-ith
Car6 !V7
''lie zq~ecific air consumption. Fi!~ 4 shows possibilities

,~,j V/ jLL7- 5,`3-4- 11/15
BoosLir-,.~,, Tu-i~luoje,. b,)r Injection of ComDress~d Air Before
tile Coapressor
Card 5/7
of boostint~ ~-he engine
from a bottl= at G
a c the thrust
by the supply of compressed air
and --* = T' ' (top
P --s seen
in-rRases with active
increased U
Soer-ifio f~,:tel
C
i i F, wii i u i t h e boos,,7ed decreases in conformity
Fpeclfic t1irust. Luiiddle C;raphs). Specific
air increases %,.i~~h (-r and th a decrease of
(t)Qt'~ GTi
k, I Ii -:,-ra-ohs) Fi~r sh-As the relation P = f(~
B B
fot 1i ar- i (-; u svalues cf Pa As th,~ 'U-hrust increases the
econotay of the bo-)stad en-ine dete---iorates, Althou~,-h an
increase of oressi-Lre gradient -in t'-,le acc-ive nozzle is
as far as L"he spe~~ific consumption of the
a4-r iE concerned, the chan6e in this 6radient affects
-,a aad Troduces a change of the design point
cond-i-c-Lo-lis '--h~--, inject,or. -"'hiis affects only a little
U--e cha en---,ine. a- * 1'= 4 but for
n-):~ly ol. P or r,
0 a
In-re-ses of tirae thrust (P< 1.22) L-he gradient

11/15
V/ 14 58
Boostin~~ --drbo-jet "r.6--ii-es by iri~ecticn Co:azireEsed ~_i_r Befcre
see,-is to ~;-ive a ,--ru-ater c~conomy, Ens (?) and (6)
a `/he _L U C,
L~Ive -U rel a-ions determininL, when rhe injector may
become c~,ocked. here suffix "0" derotes parameters of
t,hu un-boo6tt2ki Fi,.; the corresponding
,_rap~,,s witi7i p'O and a --- 0~1~ Up to tile chockinc, of'
,..he injector nozzle the specific -chrust of the boosted
eu6ine increases wilth 0 and the specific consumption of
air decreases; but once chockin6 develops the thrust
rer-.-ia4~_ns E~-Uationary and the air consumption increases. The
_,oidpressfon, ratio (i,e, due to the comnressor and
inje~~tor) re~maizns also unchan-Eed, For cozaparison
sake Fig 6 i,`ves also the lines of possible increase of
~__ L
the t-hrust by dischargink~ tiche bottles directly into
atmosphere through an additional nozz:,~le (hoT4 zontal
lines in tl-.e 'Li6ure since this joes no-~: depend upon -the
-c-_--:.aT)erauure of ~uhe a-ir in ul-le intal-ke) . For t~~ = 1 the two
effects do, not differ uluch-, but for Ov>l tine injector
ui-a!,"-~ effe,2t'Vt:, Rext, tlhie au-ilhor 6ives
for boos-in-~~
Card 16,1~7 ~e acions bet,,.-e:_n 'k, he a:.i o,~u, t o f a 4- r r e ~i u r e 6L .. U
and th~_ t-i.-ae of the boos-cin-6 oneration (EQ

1/15
Boos I Injecti. or-, o:` Co---- .1-ir Before
.j
the Corimre ssor
anc-; thu voLumu of the botLle-:7 for -.A-,i_~, amount uf air
-while Fig 7 sHows these r6latiozn: liln the form
of -cer one ton of tte initial thr-_Lst of the
& n~:, in-_~, Final: -1 y, F i p- L", s 13 iovis ho-w boos' Lin- 4s affected
!D-v L-ho t rat ure of the ases at IL-.he entry into the
turb-Ii-le an.-IL by the compression ratio of the mechanical
c,.)mpresso.r. It is seen that the main engine parameters
a L. - -
rdl.y affect the ~-!-.rust increase Li_.d the specific fuel
consw-n:~t-f-ori, bu-r, -,~h~, specific consumption of the air is
affe,_~ted -~tLlron6iy. There are 6 f,_Ll-ure-s.
ASSliCIA.I.T07~ Kafedra te-plovy-k1i dvigat-aley (Chair of Heat Engines)
Nazano-1-:17 avlatsionnTj j-nstitut (Kazan' Institlute o f
Aercaiautics32-
Card 7/17

(0); T ';00k'. v::IL0rrATI0N SOV13182
Shchukin) VM~i.rw
Shturm neta the 2d ed., Flzmatgiz, 111)59. 62 p.
(Series- vyp. 000 copies printed.
Scientif it-. E,!.: E l.: 'I. A. Ed.: V. 11.
IMPOSE: Iri-endod for th,=! gt-nei-al reLd-~r inl:erest~-.l in tht~ stildy
of the
COVERAGE: Th-l-S li-ooklet is a p--,pular accaunt of S(--)-.j-iet studies o-f atmosphere
and outer sual:10. Instruffi,,nta uLed by the meteorologi(,al am, described.
C,
Soviet eal-th and prcspects of spane travf~l are brMl-fly
tree--ted. lin aro mentioned. No references axe given.
TABLE OF COTTiMNIZ:
Why Men Stlidy th-~ Sl,-ios
Card 1/2

Assr.ult
SOV/51 ~,2
What. Kind oil' lnform-V f.,
Exploraf.L-)n
Expl.
hy Rne-ket,~-,
W-ans nf Artificial &4.rt'-ki Satell t,
How- St-dy Hle Wi, ~hc-~tt, Sf riting, the Instnuients Irt,-) Spac!e 47
Beyond t!7,=, Bc-aridvr,Le-; -~i Atm,~~spiaere c, 6
Conclusi~-,vs 61
AVAIIAFIZ: Libr-rt-,, ~ f
Card 2/2 AS/os
2/1:3/6o

s/147/6-1/000/004/015/021
E 19 4 / E I -') ~5
RS Fedorov, I. G. , ~~hchllkiri, V,K, , Mukhachev, G.A. , and
Idiatullin, N.S.
TITLE Heat transfer and hydraulic resistance of channels
with pressed spherical projections
PERIUDlCAL: lzvestiya vysshikh uchebriykh zavedeniy,
Aviatsionnaya teklinika, no.4, 196-l, 120-3-2-,
TEXT: Plate type heat exchangers are particularly suitable
for aviation because of their small size and weight. Sheets with
pressed projections are particularly usefiil because the
projections increase the strength and improve the cooling.
V.G. Fa-stovskiy and Yu.F. Petrovskiy (Ref.4: Teploenergetika, no.1,
1959) made an experimental study of a heat exchanger in which the
rectangular ducts had spherical projections on the air side and
hollou-s on the steam side. The work showed that the heat transfer
coefficient of such surfaces was greater by a fact-or of 2.5-2.8
than for smooth surfaces. The improvement is attributed to
increased turbulence of the flow. The work described here was
Card(-I~,r

Heat transfer arid hvdraUliC .... s/147/61/000/004/015/021
E194/El-35
carried out on rectan.-ular ducLri consisting of two plates with
spherical projections. The projections were of various
transverse pitch and were located both in honeycomb and straight
line-order. The main characteristics of the ducts are given in
the table. The relationship Nu = f(Re) was investigated in the
range of Reynolds numbers Icloo to 16500, and f(Pe) in the
range Re = 500 to 18000. The experimental rig is described.
The water sides of the hPat exchang
,ers were filled to one third of
their height i.;-ith dis-cilled water and electric heaters were
installed to evaporate the water. The Asrater vapour condensing on
cooling surfaces gives tip its latent-heat of vapourisation to a
flow of air passing through the ducts of the heat exchanger.
The usual measurement arrange me nt s were made. Each of the four
bundles described in the table was itivestigatcd u'nder about
twenty conditions with different rates of air flow covering the
Reynolds number range from 500 to 18000; in each case the
measurements urere repeated after 15-20 minutes. A procedure was
worked out and the operation of the equipment was checked by
using a smooth-walled plate-type heat exchanger. Further tests
Card 2/ 6

Heat transfer and hydraulic S/147/61/000/004/015/021
E194/E135
showed that the heat balance error calculated from the input to
the internal heater and from the change in enthalpy of the
cooling air is about 6-100,~. The r.m.s. error of the determina-
tion of oir flow, and of the 11e, and Nu numbers and of the
resistance coefficient are, respectively, 2.2, 2.5, 4.5 and 5%.
Heat transfer results are well represented by the following
equations.
With honeycomb arrangement:
INU = 0.54 x 10- 4 Rel-55 (Re = 1000-2300), (3)
f f
Nu = 0.95 x 10- 3 Rel-17 (Re = 2300-10000), (4)
f f
INU = 0.0276 Re o.8 (Re = loooo-16500). (5)
f f
With the In-Line arrangement;
Nu = o.44 x lo- 4 Rel-55 (Re = 1000-2300), (6)
f f
Card 3/ 6

Heat transfer and hydraulic ... S/147/61/000/004/015/021
E194/E155
N U 0.8 x 10-3 1.17
I f = Ref (Re = 2300-10000), (7)
Nu = 0.0,248 Re 0.8 (Re = loooo-16500). (8)
f f
The results show that for given values of the Reynolds number the
Nu criterion is 15-201yo higher in bundles with honeycomb arrange-
ient of projections than those with 'the in-line arrangement.
The Nu criterion of the bundles is greater by a factor of
2.1-1.65 than the Nu criteria for a bundle of flat sheets in
the Re number range 2500-16500. These results are not entirely
in line with those given in Ref.4, and the reasons for this are
discussed. The following expressions adequately represent the
results of resistance tests:
A (Re = 500-2300), (9)
(Re 0.30
f
B (Re = 2300-18ooo). (10)
Card Re 0.089
4/ 6 f

Heat transfer and hydraulic ... s/147/61/ooo/oo4/ol.5/021
E194/E135-
The values of the coefficient-9 A and B in Eqs (9) and (10)
are given in the table. The results show that ducts with
spherical projection have higher resistance -,than do smooth ducts,
the actual, amount depending upon the pitch and arrangement of
the projections. There are 3 figures and 1 table.
ASSOCIATION; Kafedra teplovyk-h dvigateley, Kazanskiy
aviatsionnyy institut (Department of Heat Engines,
Kazan' Aviation institute)
SUBMITTED: March 10, 1961
Key to Table Headings: (1) Number of bundle; (2) Arrangement of
projections-, (3) Shape of duct; (4) Length of bundle, mm.;
(5) Height of bundle, mm; (6) Equivalent diameter d9K MM;
(7) Transverse pitch Sl, mm; (8) Longitudinal pitch S21 Wm;
(9) Coefficient A; (10) Coefficient B.
Card 5/6

J.~ 3 25) J 8
0c, S/096/62/000/001,/007/008
-),18 1 E025/E435
AWHO-11 Sh-hukl_n V.,K_ Candidate of Technical Sciences
_ -----------------
TIF'ILF The tempe-rature state of porous wal'-'s In Effusion
COO-l-Ing
PER !OD TCAL: Tr-picenergetika, no.l., 1962.. 80-82
T EXIT Ir ~; z-rated t-hat the. opinion expressed in non.-Soviet,
I t e r -3 thal- In tLe absence of rad-lated hea-11- the temperature of
-3 coo'.~-r a-~ ,he oo_4tput of a pore is identilcal with the
t-ezp,~ra'ru.re of the. wall is incorrec'-. The difference between the
t,~-mperatur.-7 of the cooler and that of the wall at t1he output: is
d=r-rmiapd by the conditions of heat exrhange within -,he wall and
::.n, irs boundar-_.es and.without estimating and taking ac,~ount~ of
rheFP condit.-ons, i~ is impossible to es-~ablish to what extent the
-wpE-rq_r.u:~c- of he rcoler at the output section approximates to
'ha- of: -he wall Fcr giT-en temperatures of a hot gas and of a
ar -ha inpu,,~ of the cooling sysT.-em and for given conditions
-aloulated
the thermal state of the porous wall can be
!Tom a EVI-stem of four equal:,'Lon,~ -z,3:-h of wbich describes a balanc.e
of per I iw~ -,-f wall slarface, (The propagation of heat along
0
-d rieat transmi-l~-d by thermal
The I

S"/096/62/01-)0/00.--L,/007.//008
T eM.PP 7 a.' 1.1 T a~ e o f por ous E025/'E!-a5
i i- tly t the hcc surfa,e of the oo, wall eq-ual-c. The
of ~Iie. cooler on f A -
:z~ iiaa, -.c;.~ent lowing o-!- the cold
The h-=W- transmitted
r. a ':'t thp w, i and with.,ri t.~ie pc.-res
h. - q r'-X(Avjrq~" To th- cooler in the pores equa_~s. rhe -.hange in
~-3T on-nf. of th,:~ .:r-oller within the porous wFill., The hear
from the hot gaE to the wal.1 equals tLe change in
crjnt~-n,_ of -the rooler from. the inpuir of rhe system to ~he exit
o a Th,~ heat 6iven out by cold surfare ot the porous wall
'hA -c6i,~: zquals -,.h,~ -hange of hear, content of the c.ooler lip
'T!-: enT'rance 'be porouS wall- For The first and sec,ond
of th-c- rela~-,ons Th- varia-Lon of wall with thickness
and for the sc-ond relation algo -t- variation ot
'r lemv,~ratur-? with wall thi,:kness,, ThE- -orresponding
~QuqTion.:~ are giv~:-n and solved,, and the results ompared wIth those
c-t'ra;n-d on the assumption that the temperature-- of the wal.'L and
r 8 r c- e ia, at, the exit of. a pcr,~ and the rela-rive error
q,
I a t -a Two numerical examples are qu',ed (Ref-~3
S A- D -7iz!7 r. 7 n Teploenerget ika - no,. 9 1961~ f,--- Crainless :z7eel
1.0 an -pe. , iv~lv and -i~ air
OorocltieE 0~ d 50', 1

32538
S/096/62/000/001/007/008
The temperature state ofE porous E025/F~435
between the error in the calculation of the wall temperature
caused by the assumption of equality of wall and cooler
temperatures and a parameter representing the intensity of heat
exchange within the porous wall, and the ratio of the temperatures
of the hot gas and cooler. The effect on the error of the thermal
,-onductivity of the porous material, of the thickness of the
specimen and of the intensity of heat exchange on the side of the
hot; -as are shown in the curves. It is apparent from the graphs
that. the errors are serious: they increase with the ratio of the
temperatures of the hot gas and the cooler, with decrease of
intensity of heat exchange within the wall, with decrease of the
thickness of the wall and of its thermal conductivity, The
variation of the error with the coefficient of heat transfer from
The hot gas has a maximum. In some of the cases quoted the
errors exceed 30%. There are 6 figures and 3 references:
I Soviet-bloc and 2 non-Soviet-bloc. The two references to
English language publications read as follows:
Ref-l-, P.Grootenhuis. J. of the Royal keronautical Society,
.no.5?8. 1959, Ref.2: I. Friedman. J. Am. Rocket Soc., no.79,1949.
Card 3/4

-'.8
SIO 62/000/001/007/008
The temperature state of porous ... E025/E435
ASSOCD',.TIGN~ 7r,-_azansk-Ly avia-Gsionnary institut.
(Kazan' Aviation Institute)
Card 4/4 x

S/096/62/000/006/009/011
E194/E454
AUTHORS: Fedorov, I.G., Engineer, Idiatullin, N.S., Engineer,
S� ~huki~nV.~K. , Candidate of Technical Sciences,
.,Iukhachev, G.A., Candidate of Technical Sciences
TITLE: Heat transfer and hydraulic resistance of slot shaped
ducts with conical indentations in honeycomb arrangentent
PERTODICAL: Teploenergetika, no.6, 1962, 57-60
TEXT: Heat transfer and air resistance tests were made on a
plate type heat exchanger with ducts 3 mn, wide, 145 mm high and
475 mm long, The ducts were made of 0.5 mm sheet in which had been
pressed indentations in the shape of truncated cones with a base
diameter of 6.5 mm, cone angle of 300 and height 'of 1.5 mm,
arranged in honeycomb order at various pitches. The tips of the
cones of one plate were in contact with the corresponding tips of
indentations in the opposite plate of the duct. Two such sheets
soldered together at the edges and with fixing flanges attached
formed the test bundles. Electrically heated water supplied heat
to the test bundle and it was removed by a flow of air. The test
arrangements are described, The tests were carried out with a
Card 1/3

S/096/62/000/006/009/011
Heat transfer and hydraulic,... E194/E454
constant wall temperature of 1100C with an inlet air temperature
of 22 to 23-50C and a discharge air temperature ranging from 91 to
1060C, the mean air pressure in the duct was 1.01 to 1.23 kg/cm2,
the air fLow 2 to 92 K-g/hour and the specific thermal loading
(0.18 to 11.6) x 103 Iccal/nI2 hour. The difference between the
heat input to the heaters and the heat gained by the air was
6 to 10%. The methods used to check the equipment are described.
For all the investigated ducts the experimental points lie within
,_ 6% of three straight lines of various slopes. The following
equation applies for Reynolds numbers Re = 750 to 2500
LNU = 0.155 x 10-3 Rel.41 (1)
f f
for Re = 2500 to 10000
NU = 1.017 x 10-3 Rel-17 (2)
f f
and for Re = 10000 to 18000
Nu. = 0.0315 Re 0.8
f
(3)
Card 2/3

s/oq6/62/ooo/oo6/ooq/on
Heat transfer and hydraulic'... E194/E454
For Reynolds numbers of 2000, 4000 and in the range from 10000 to
18000 the Nuss,-It criterion for ducts with conical indentations is
greater than for a S1110oLh duct, by 2.0, 1.62 and 1.75 times
respectively. The surface increase caused by the indentations
ranges from 5 to 10',o so the main cause of greater heat exchange
with indentations is increased turbulence of flow. The resistance
of the ducts was ineasured under both isothermal and nonisothermal
conditions and the results are given in the form of empirical
formulae with constants tabulated for ducts.of different shape and
pitch. There are 3 figures and I table.
ASSOCIATION: Kazanskiy aviatsionnyy institut
(Kazan' Aviation Institute)
Card 3/3

STIL-11TSOVY V.V.; 51fC1 lc~-BRCVY A.K.; FUKS, G.I.; KUTATELADZE,, S.S.;
F
LYKOV, JI.V.; PREEEDVODITE A.S.; KOILIIKOV, P.K.; DUSHCHENKO., V.P.;
,%,,AKS3MC)VP G.A.; KFL~SIIIKOV, V.V.
Readers$ response to I.T. Ellperin's article "Tcrmiriology of heat and
mass transfer" in Inh No.l., 1961. Inzh.-fiz. zhur. 5 no.7:113-133
11 162. (MIRA 15:7)
1. Ehimiko-tekhnologicheskiy institut, g. Ivanovo (for Strelltsov ).
2. Aviatsionnyy institut, Kazan' (for Shchukin, Rebrov). 3. Foli-
tekhnicheskiy institut, Tomsk (for Fuks). 4. Institut teplofiziki
Sibirskoc!o otdeleniya AN SSSR, Novosibirsk (for Kutateladze)o 5.
Energeticheskiy irstitut U,, BSSR, Unsk (for Lykov). 6. Gosudarstven-
nyy universitet imeni Lomonosova., '.Ioskva '(for Predvoditelev). 7. '
Institut inzhenerov zheleznodorozhnogo transporta, Moskva (for Konakov).
8. Institut legkoy promyshlennosti., Kiyev (for Dushchenko).
9. Vsesoyuznrf zaochnyy inatitut pishchevoy promyshlonnosti, Moskva
(for Maksimov). 10. Tekhnologicheskiy institut pishchevoy
promyslilennosti., Moskva (for Kras-nikov)
(Heat-Transmission) 6ss Irensfer)

SHCHUKIN V.K. kand.tekhn.nauk
P , __a
Temperature state of a porous wall in effusion cooling.
Teploenergetika 9 no.l.-80-82 JTa 162. (I-EM 24-12)
1. Kazanskiy av-iatsionnyy institut.
(Heat-Radiation and absorption)

SHCHUKIN, VA *- KAIMnCV, I.I.; ZINGER, N.M., kand. tekhn.nauk,
--r-
r.isenzent; FALIKO, C.S.,-iazh., red.; ELIKIND, V.D., tekhn.
red.
[Gas ejectors ]Gazostrainye lmmpressory. Moskva, Mashgiz,
1963. 145 p. (MIRA 16s8)
(Compressors)

.
I 0.~~
ACC NR: AT6007554 JDA-1v1/EWJXT(CZ., UR 2529/63/000/076/0026/0035
AUTHOR: Shchukin, V.K.
ORG: Kazan Aeronautical Institute, Kazan (Kazanskiy aviatsionnyy institut)
TITLE: Supplemental condition of similitude for flows in the field of mass inertia
forces
SOURCE: Kazan. Aviatsionnyy institut. Trudy, no. 76, 1963. Aviateionnyye dvigateli I
(Airctaft engines) 26-35
TOPIC TAGS: hydrodynamics, hydrothermodynamical incompressible fluid, jet engine,
flow field, convective flow, turbine blade, jet engine
ABSTRACT: The author develops a generalized criterion of simulitude for an incompres
sible fluid flow in the field of mass forces. Interest in this topic is generated by
the complex character of fluid flow under the action of active mass forces, which de-
creases the probability of successful analytical solution, and thus favors an experi-
mental approach. Convective flows offer well-kiiown examples of active mass forces phe-
nomena; stronger acceleration fildoz occur e.g. within the hollow cooled turbine bla-
des~dvf a jet engine. Active mass forces engender special flow patteims, distinct from'
turbulence or*laminar flow, such as the double whirls in flow through bent tubes; to-
roidal whirls of Taylor in the gap between rotating coaxial cylinders, etc.. Starting
Card . 1J2

L 207o8-66
ACC NR, AT6007554
with an analysis of convective flows of a heated fluid without forced motion,and of
a uniform density fluid with forced rotation, the author analyses the general case of
active mass forces determined by simultaneous changes of density and acceleration,
using the method of similitude constants. Three interim criteria are obtained; elimi-
nation of the velocity variable from one of the criteria leads to the general crite-
rion: 3
P
where:,A F - the space differential of force on a fluid element; l- length;p-density,
and V - the kinematic viscosity of the fluid. Forms of this general criteribn, P, for
specific flow cases, are developed. Comparison of the IIPII criterion with various cri-
teria of simulitude used at present for the generalization of experimental data per-
taining to hydrodynamics and heat exchange in the presence of mass inertia forces
shows that these criteria represent special cases of the P- criterion. The P - crite-
rion, for certain specific flow cases# reduces to the criteria of Dean, Taylor, and
others. Orig. art. has: 26 formulas.
SUB CODE: 20 SUBM DATE: l4Kar63 ORIG REF: 007 OTH HEF: 008
Ca,d 2/2

T. i2l65-6.1_ EPR/EPP(c)/EWT(l)/EPF(n)-2/tD9 AFFTC/A;Sb/IJP(Ci/
SSD
ACCESSION NR: AP3004291 /007/6007/0012
s/ol7o/63/06
'AUTHOR: Shchukin, K.
TITLE: Methods of evaluating the local heat-exchm2ie coefficient in flow around,
a
cylindrical surface
I
Is
OURCE: lnzhenerno-fizi~heskiy zhurnal, v. 6, no. 7, 1963,:7-12
teM_
i TOPId TAGS: Local heat-exchange coefficient, cylindrical surface, radial
~Deraturo gradient
PSTRACT: When a liquid flows in a curved channel (see Fig. 1 of Enclosure 1)
-there'is a secondary circulation which changes the conditions of interaction
6otween liquid and wall, and affects the character of the change in the heat-
hange coefficient according to the length of the channel. If the absence or
_9X-c
4~at flows along the cylinder axis is to be insured in an-experimental setup,
etemperature field in the cylindrical walls forming the channel will be two-~
d3mensional. Under this condition, the local heat-exchange coefficients on the
i .'surfaces alb' and de can be determined from the experimentally measured distri-
butiioh of the temperatures on the contours atbleld' and abed, respectively
Cqe

L~1~1~65_63
ACCESSION NR: AP3004Z91
:from the gap in temperatures between liquid and the wall Delta t. Hence,
determining the heat-exchange coefficient is simply a matter of finding the radial
-temperature gradient on the heat-exohange sr-.rface from the known temperatur-s
t6~ all the surfaces of the contour. The article discusses the analytical and
rid'methods of solving this problem. With complete heat isolation of the side
-and~end surfaces and an assigned distribution of the temperatures on surfaces
ab and cd (or albl and eld') the temperature field in the area abcd (or alb1cidt.).1,
'is found by solving the differential equation of heat conductivity
I a2i
+ + =0.
&2 ar r2 ~(r radial coordinate,q7= an-,..
gular coordinate). Figure 3 (see Enclosure 2) shows that ignoring the curvature
of even a thin plate can result in substantial error in determining the tempera-
ture gradient from.the surface temperatures. The temperature gradient on the
wall surface necessary to evaluate the heat-exchange coefficient can also be
determined by the grid method described by A. V. Kantorovich, "Tables for the...
Numerical Solution of the Boundary Problems of the Theory of Harmonic Functions
2

17"J'i , : : I I ~~-

L 11607-65 EiIT(1)/EVIT(m)/EPF(c)/r=PF(n)-2/EPR/EiVP(J)/,~.'-/EPA(bb)-2,/B4A(l) PC-4
Pr--:47Ts~-47Pi-4/Pu-4 RPL/ASD(f)-~/As(mp)-2/AEDC(a)/AFWL/SSD/BSD/AFETR JD
Y111ALK RM
ACCESYmN NR Am4o46710- BOOK EXPLOITATION S/
Bolgarskiy, Andrey Vladimirovich (Professor); Mukhachev, Gennadiy
Alekseyevich.(Docent); Shchukin,tI.-Vik~oiz,..KQ4stan,ti~,Qvich (Docent
Thermodxnamic and heat transferl(Termodinamika i teploperedacha), Moscowt
,1.., "Vy*sshaya shkola", 1964, 457 p. illus., biblio.j tables. 9,500 Copies
printed.
TOPIC TAGS: thermodynamics, heat transfer
TABLE OF CONTENTS [abridged I
Foreword
Part 1.
Ch. I. Introduction 5
Ch. II. Parameters of the working body 10
Ch. III. Thermal capacity of.gases 2.5
Ch. IV. First law of thermodynamics 40
Ch. V. Basic thermodynamic processes 51
Ch. VI. Second law of thermodynamics 63
Ch. VII. Change in,enthropy in processes. 'Enthropy diagrams 812,-
Cord 113

L 17607-65
ACCESSION NR Am4o46716
Ch. VIII. Real gases 97
Ch.- IX. Cycles of piston engines 119
Ch. X. Compressor -- 131 j,
Ch. XI. Cycles of gas turbines 142.
Ch. XII. Gas flow -- 154
Ch. XIII. Basic laws of thermodynamics applied to chemical processes '172
Ch. XIV. Equilibrium of thermodynamic-systems'and dissociation 191
Ch. XV. Combustion processes -_ 204
Ch. XVI. Kinetics of chemical reactions 214.
Part 2.
Ch. I. Introduction 221
Ch. II. Thermal conductivity in a stationary regime.-- 231
Ch. III. Heat transfer and methods.of studying it -- 253
Ch. IV. Heat transfer in free:and limited movement of a liquid.-- 282
Ch. V. Heat transfer at high-speed movement of a gas 296
Ch. VI. Heat transfer in rarefied gase's 313
Ch. VII. Radiant heat exchange -- 350
Card 2/3

SHCH11KIN, VA.
Determining heat transfer coefficient's in a pipe by the
tempernture distribution on the contour of its longitudinal
section. Izv. vys. ucheb. zav,; av. tekh. 7 no.3s96-105 164.

ACCESSION NR: AP4043425 S/0147/64/000/003/009610105
AUTHOR: Shchukin, V. K.
TITLE: Determining the heat loss factors in a tube according to the tempera-
ture distribution on the contour of its longitudinal section
SOURCE: IVUZ. Aviatsionnaya tekhnika, no. 3, 1964, 96-105
TOPIC TAGS: heat loss, temperature distribution, thermal insulation,
heat transfer
ABSTRACT: The author notes that the determination of the heat loss factor on
the basis of the experimentally measured temperature distribution on the sur-
faces of the wall participating in the heat transfer process eliminates the
need for heat flow measurements and imposes no limitations on the possible
variation in temperature along the length of the wall. Special attention is
called to the work of B. S. Petukhov ("Teplacnergetika", No. 10, 1956), con-
taining a discussion of a method for determining the heat loss factor in a
tubc according to the distribution of temperatures on its generatrices. The
author observes that this method was based on the assumption that the ends of
the tube were thermally Insulated, although experience indicates that this
Card 1/3

ACCESSION NR: AP4043425
condition is extremely difficult to realize in actual practice. In this con-
nection, therefore,'the author presents a new method for determining the co-
efficient of heat loss with an arbitrary distribution of temperatures on all
four sides of a longitudinal section through the tube. Since liquid heat loss
in a tube with an axiosymmetrical temperature field is considered, the tempera-
ture of the liquid in the longitudinal section of the tube is determined from
the heat balance (a liquid with no internal heat sources is postulated). An
expression is derived for tile local heat loss factor for a specific segment.
For tile axiosymmetrical problem and a constant coefficient of thermoconductivity
for the tube (,U, the differential equation of thermoconductivity can be
wriLten in the following form:
.1. 0.
or-' r or (jZj
This equation is solved by tile Fourier method. The same problem is also con-
sidered for the case in which tile wall of the tube ht., volumetric heat loss
Card 2/3

ACCESSION NR: AP4043425
(such conditions are encountered in the study of heat exchange in a magnetic
field with Joule effect liberation in the tubing wall or with the tube treated
by Lhe passage of an electrical current). The analysis given in this article.
for the convergence of series for a tube with thermally insulated ends and
ititernal hent sources in the wall, as well as Petukhovts experimental verifi-
cation of a method for a tube with thermally insulated ends without internal
liberation, provides a basis for the belief that the convergence of the series
does riot limit the area of applicability of the method. It is also claimed
that the same technique can be employed to study heat loss in the case of an
external longitudinal flow around the tube. Orig. art. has: 45 numbered
formulas and I figure.
ASSOCIATION: none
1~1'1~~!ITTHD: 25Jan64
ENCL: 00 SUB CODE: TD
NO REF SOV: 003 OT11FR: 000
3/-3

L ~7620-65
W(e)/EWT(3.)/~DIT(m)/EPF(n)-2/EWP(t)/~.W(k)/EWP(b) Pf 4/Fu-4
J DIWM
all
ACCESSION NR: AP5005538 S/0147/65/OOOJO01/0087/00
AUTHOR: Shchukin, V. K.; Koval'nogov, A. F.
TITLE: Temperatures of porous plates with internal heat release during effusion
cooling
SOURCE: IVUZ. Aviatsionnaya tejKhni 1 96 ~87
~a, no. 5., -94
TOPIC TAGS: porous plate, coating, heat transfer, fuel element, reactor core
ABSTRACT: The cooling of porous plates with internal heat release by passage Of
gas canbe used in nuclear reactors with porous fuel elements or for heating gas
by passage through'electrically heated porous plates., The maximum temperature and
the temperature profile are of importance for. determining the thermal stress in the
plate. A method developed previously 4 P. Schneider is the assumption. -
that the temperatures of thegas inside the pores.and the pore. walls are equal. To.
inveEltigate the effect of this simplifying assumption, exact formulas were derived
which allow for the temperature difference between the gas and the wall, and plats,
were obtained for the error caused by the simplifying assumption as a function-of
the heat transfer coefficient and thermal conductivity of the material (porous-
Card 1/2

ASSOCIATION: none
SUBMITTED: 27Dec63 ENCL: 00 SUB CODE:
AS)
NO R.EF SOV: 001 OTHR: 004 ATD PRESS:
.3190
Card 2/2

L 43895-65 EPF(c)/EPF(n)-Z/tPk/EWT(1)/.'C-WG(m) Pr_4/Ps-4/Pu-4 VAV.
ACCESSION Nk_:_AY56ib575 UR/0170/65/60b/W /651b
AUTHOR: Shabukin, V. K.
TITIM: Thick wall method for investigating heat transfer iii transverse-flow~tdbes
SOURCE: Inzhenerno-fizicheskiy zhurnal, v- Bt no- 4P 1965t 504-510
TOPIC TAGS: heat transfer, heat conduction, thermal conductivity# Fourier eeriest
temperature distribution
ABSTRACT: Three,different expressions are given foz calculating thermal diffusivitir
0( by the use of temperature distribution data from tube surfacese -The temperature
9
gradient term in the expression for CC, !a determined by
ar
solving the cylindrical Fourier-conduction equation'iii-tiro dimensions, subject to
boundary conditions,
extended to the
f (ri, T). The solution is then
case of temperature-dependentheat source terms in the heat-conduction equation.
Expressions for mean and local thermal diffusion coefficients are solved by-the
network method. This reduces to-evaluating -the Fourier conduction equation in the
Uqurd 1/2

L 43895-65

SHCHUKIN) Viktor Konstantinovich; GELIFER, Ya.,k'., red.
Neat transfer in nature and techn-ologyl T-eploob!:en
prirocle i tekhnike. Mosk-va, Nauka, 1965. 120 p.
(MIRA 18:7)

L 0WIr I'd 'i " Tel
"E,,ff ~jlj Y m) --o/ET9A
I/ _~~ff~)=;'/EWA (d) /T/ETc 6 ljp(c)
ACC NR, Al'-.' )010034 ','1'6/DJ SOUFRCE CODE: UR/0170/66/ol(/003/0357/0%2
AUI~1101i: Shchukin, V. K.
OIRG: Aviation Institute, Kazant (Aviatsionnyy institut)
TIM:
rotati
The effect of the temperature field on the stability of liquid flow betveen
:cvlinders -
SOURCE: Inzhenerno-fizicheskiy zhurnal, v. 10, no. 3, 1966, 357-362
TOPIC TAGS: liquid flow, temperature dependence, heat effect, fuel thermal stability,
steady flow, thermal stress
A-11.13TRACT: On the basis of the Rayleigh method, formulas were obtained for estimating
the effect of the value and direction of the heat flux on the stability,of liqui. IV I
between rotating cylinders. It was shown that this effect may be described by the
dimcnsionless parameter K, formula K= -~r,b r1q, where K r2c is a
dr A
I'lie radjoLs o--:' the outside cylinder, and q is Une heat
col:molex, r2 is
The vc-lue cnd direction olL +-he 1~eat flux which deter:%ine the rnimber K affects,
- I . ,-lie
~211S(~'!~-~Jl% i-ht7~ of thr~, ~,te;Ay C)L' tlie liquid. Tolien
-"(-,w re-g-tors. 7i'licn the
i:('-% 'S~L!d tl'19 `:ec-07ez; jn~vrrow~r. Orig.
r,3, aWthorlq dbstrazt)
2. :~zvl L ase" oi
Card UDC: 532.5

.. " -~ C. .-~)
: ACC NR: fAi-,6oI(-)034
I CTT-- "01:7. 1-1 n. I
- - - . . - - - - -- - --- ---- ----
19 ;
J~~,
~!TMVI T)V "i- '-N9 -TI 1 n 69 / ORT(7- =', ! ool-! CrM =P ! 003

AC~ NR. AP6030333 SOURCE CODE: IJIL:I.rlC)170/66/011/002/01711ln7~"6
AUTHOR: Shchukin, V. K.
ORG: Kazan' Aviation Institute (Aviatsionnyy institut)
TITLE: Correlation of experimental data on hydraulic resistance in tubei; with
band-type turbulence generators
SOURCE: Inzhenerno-fizicheskiy zhurnal, v. 11, no. 2, 1966, 171-176
TOPIC TAGS: hydraulic resistance, laminar flow, turbulence generator
ABSTRACT: The mechanisms of a fluid flow in a tube with a band-type turbulence.
generator, and in a coil are similar. This similarity yields a dimensionless equa-
tion for the correlation of experimental data on hydraulic resistance in tubes with
band-type turbulence generators in a laminar flow with macrovortices and in. a
turbulent flow. The channel between the turbulizer and the wall of the tube is a
coil with a semicircular cross section. The curvature of the channel depends on
the pitch of the turbulence generator. Orig. art. has: 3 figures and 9 formulas.
[Author's abstract]
SUB CODE: 20/SUBM DATE: 23Mar66/ORIG REF: 002/OTH REF: 005/
Card 1 /1 UDC: 532. 5+ 532. 503. 2

ACC NR- A~66:~6865-
surface being Insulated; and 3) a duct with heat transfer through both
surfaces. The obtained results indicate that the'maggnit-ude and direa-
tion of heat flux, and the point of heat addition or removal do affeat
!-LIhe loca~'Gion and size of the flow stability zones in a curvilinear d=t.R.
.and, consquently,.the flow regime, heat transfer conditions, and
:hydraulic.resistance. Orig.art. has: 3 figures and 21 formulas.
!S'U-B CODE: 21/ SUBM DATE: 28jun65/ ORIG MP: '003/ OTK---REF: 002'
212
Cord.

vi GbQhUkI
FA PID 14Z66, FO F( AH&LMIS CF PUT FCR AS& ii, Val
'c From. Peat, Ind Moac
M-art Uri IfMok govit 19-14i t=W*'
Zb,' Each
-Mzt.-; (Ref. -J. Chem.,- ho=GW
956i 13),
Poxes In caloinine.a to rj'5 9-
~-~WWWP -~U' _a,=Uiodo .-The ShchukIn metWd consists
laIn a.'st6d*aLby-pan, 85-1.00'm. In d
f 0: at 800
qonsistain, vat
_i6~:Jn'PCIIW
td~ 5)bcft The Storchak 66thod
heat
Uln beats on an elecitrio riot plate bLaWnIng-with a.
a matboqa are intaWad as quick abacks for -peat prodwers
K;~ or users, and give'resuits within .0.5 of Ahe standard method.

BOBRIYEVICH, A.P., sotrudnik; BONBARENKO, M.N., sotrudnik; GNEVUSHE:V, M.A..
sotructnik; KIND, N.D.. sotrudnik; KORASHKOV. B.Ya., sotrudnik;
KURYLEVA, N.A., aotrudnik; NRYEDOVA, Z.D., sotruclnik; POPUGAYEVA,
L.A., sotrudnik; POPOVA, Ye.E.. sotrudnik; SKULISKIY. V.D.,
sotrudnik; SMIRNOV, G.I., sotrudnik; YURKEVICH, R.K.. sotrudnik;
FAYNSBTEYN, G.Xh., sotrudnik, SHCHUXIN, V.N., sotrudnik; BUROV.
A.P., nauchnyy redaktor; SOBOI%f."Y.'-�.-,"n'a'ii~'tnyy redaktor;
VERSTAK, G.V., redaktor izdatellstva; KRYNOCHKINA, K.V.. tekhni-
cheskiy redaktor
[Diamonds of Siberia] Almazy Sibiri. [Moskva] Gos.nauchno-tekhn.
izd-vo lit-ry po geol. i okhrene nedr, 1957. 157 P. KRA 10.'7)
1. Russia (1923- U.S.S.R.) Ministerstvo geologii i okhrany nedr.
2. Amakinakaya ekspeditsiya Glavuralsibgeologii Ministeratva geolo-
gii t okhrany nedr SSSR (for Bobriyevich, Boadareako. Gnevushev.
Kind, Koreshkov. Kuryleva, Nefedova, Popugayeva, Popova, Skullskiy.
Smirnov, Yurkevich. Faynshteyn, Shchukin)
(Siberia--Diamonds)

25(5) PHASE I BOOK EXPLOITATION SOV/2393
Leningrad. Politekhnicheskiy institut
Mashinostroyeniye; ekonomika, organizatsiya i planirovaniye
proizvodstva (Machinery Manufacturing; Economics, Organization
and Planning of Production) Moscow, Mashgiz, 1958. 110 p.
(Series: Its: Trudy, Nr 200) Errata slip inserted. 2,800.
copies printed.
Sponsoring Agency: USSR,Ministerstvo vysshego obrazovaniya.
Resp. Ed.: V.S. Smirnov, Doctor of Technical Sciences, Professor;
Eds.: Ye. M. Karlik, Candidate' of Economic Sciences, Docent;
and S.A. Sokolitsyn, Candidate of Technical Sciences, Docent;
Tech. Ed.: R.G. Pollskaya.
PURPOSE: This collection of articles is intended for engineering
and technical personn~--l of machine-manufacturing establishments.
COVERAGE: This collection covers the theoretical aspects of the
Card 1/4

Machinery Manufacturing; (Cont.) SOV/2393
economics, organization, and planning or produc:;-on a the
actual operation of machine-manufacturing e9tablishments.
The first five articles deal with problems of classifying
production lines for lot production, variations of the -flow
Of lots Of Darts, and duration of the machining cycle, etc.
The remaining articles are devoted to the economic efficiency
of new technology, problems of quality control, and to the
question of specialization and cooperation. No personalities
are mentioned. References are given at the end of several
articles.
TABLE OF CONTENTS:
Foreword
3
OlIkhov, G.A. Classification of Continous Machining Lines for
Lot Production 7
Klimov, A.N. Data on the Organization of Line Production of
Small Steam Boilers 16
Card 2/ 4

Machinery Manvfacturing; (Cont.) SOV/2393
Tsuprov, Ye. K. Duration of the Machining Cycle on Production
Lines Employing Multispindle Automatic Machine Tools of the
"Parallel" Type 31
Tsuprov, Ye. K. Schedule Chart for Manufacturing Automobile
Pistons at the AutomatiA Plant (A2-1) and Methods for Calculating
the Manufacturing Cycle 34
Sokolitsyn, S.A. Variations of the Flow of Batches of Parts in
Lot Production 38
Rudkovskiy, S.S. Effect of Standardization of Labor Input in
the Production of Parts in Machine Shops 48
ShchqukKjinn,_V-.X- Problewof Determining the Economic Efficiency
of Machine Tools in Connection With Planning Technological -
Processes 61
Rayerman, A.I. Economic Analysis in the Selection and Use of
Assembling and Welding Equipment 74
Card 3/4

'17
SOV/119-59-4-10/2

MT
Ffoducin~7 bpa~re Prarts for DileasurJn-- Dev;ces and In-
r~
~j
F,"rumier"F (V-pi~ska-,,~7 z-apasnrye detalli k ilzme-ritell-
. j j

ume n am.
nym. pribora-m i illStr

RInDICAL
r T Cr-' ~- ,~ f r, -
khnika, -1 950 . lir u 16 ,USSR)
to
-

AB6TLI'L.,~CT: T7 e D
author stat-es that a nu-ber cf ins.-u, nt -!ants
-GdUCe any snare paz's -'.cr -ran4d wear n
nC'~ P
-
ca -,iper,7. uroduce,
:ion-ons bv

t sl, i 411 a
I ---i n,-, na I

e Th- tha-
-nc-r e,-;. an

C,ari 1,.., 1

SRCHUKIN. V.9.
Problems of repairinf meaaur1n._- equipment have been set aside. Izm.
tekh. no.3:56 Mr 60. (MIRA 13:6)
(Measuring instruments-Maintenance and repair)

ZVFJZR, L.N., SUMMIN, VA.
Nature of faultB in the Daaldnyskii kimberlite region. Geol. i
geofiz. no.6:132-134 160. 04114 13:9)
1. Vostocbno-Sibirskiy geologicheakiy institut Sibirskogo otdeleniya
,KN SSSR.
(Siberia-limberlite)

BOBRIYEVICH, A.P.; KRYATOV, B.N.; SHCHUXIN, V.N.
Some data on the.geology and petrography of Siberian kimbeerlites.
Trudy IAFAII SSSR. Ser.geol. no.6:24-36 161. (MIRA 14:9)
(Daldyn Valley-Kimberlite)

SHCHUKIN, V.I!.; KRYATOV, B.M.; VOLOTOVSKIY, A.G.
-F 13 ~
Relationship between kimberlites and traps. Trudy T~ Aft SI.--_P,.
Ser.geol. no.6:45-48 61. OMIHA 14:9)
(Siberian P-latform--Kimberlite)
(Siberian Platform--Rocks, Ipreous)

KOZILOV, I.T.; SHC,;UFdN, U.N.
lgea-,hering surface on trap rocks Ln the cen--~raj Dert of -the
Siberian Platform. Geol. j gecf-z. no.2-.~37-ILO 164'. (.VJF-A 18:,4)
1. Amakinskaya ekspeditsiya, poselck N~,-urba.

ShCHUIN, V.N. __
Repair of dial indicat-orso lzm.tekh. no.3213-14 Mr 163.
(MIRA 16;4)
(Raccir-cing instruments)

L 41684-0 WT(a) Peb DIAAP
ACMSS MR: ATS003176 S/3065/62/000/041/0045/00W
AUTHOR: Shchukin, V. F.
TITLE: Design of laboratory buildings for work with radioactive skiterials
SOURCE: Moscow. lnzhenern.o-stroitel'nyy Inatitut. Sborulk no. 41, -1962.
Kafedra stroitel'stva yadqnykh ustanovoko Proyektirovantye i strottalstvo
yadernykh ustanovok (Department for the construction of nuclearensineering inA
stallotions. Design and construction of nuclear engineering installations); 45-
63
TOPIC TAGS: laboratory architecturei radioactive-material process nuclear.
laboratory design, isotope laboratory design, radiation shielding, laboratory
personnel safety
ABSTRACT: The author is concerned with planning,considerations and architectural
approaches to radioactive materials installations. He1egins:byze-viewing- the-
conditions which lead to problems. in architectural planning of buildings for
-radioactive research and praciisLng, and points out that the humm operator can
F
be exposed to nuclear radiations either by penetrating radiation fic the outslder-
(mainly gamms radiation) or by direct contact betwem radiamietive, =MwWa and :i
COrd 1/3
-7 77:
7 77

L 41684-65
ACCESSION NR: AT50103176
huma,n organs, such as the skin, blood etc.., as: in the'case.of:t~ugestion.: Attena~._~__.
tion is directed to the basic hazard of inadequately* sealed tAdioactive
any
material, because of possible evaporation, travel as dust,.and a4saiription onto
various surfaces. By-any one of these processes,,the premises can become con,6,
taminated and present a continuing danger. The shielding of personnel and sea-
sitive instruments and the prevention of contamination thus become the two basic
safety problems to a nuclear laboratory. Requirements for building design are
then listed as conditioned by: safety rules, -the branch. of, science involved,
laboritory mission and programs,equipment and specific 'Architectural.
considerations dictate balancing of constructional and-operational constraints.
An example is presented involving the mutual positioning of hot chambers, e.g.
between "clean" and "dirty", zones, which enables then to beoperated from thei.
clean zone, while repairing and maintaining them.from the dirty.zone. An Impor-
tant structural consideration Lathe provision of appropriate floor strength'to,
support the heavy protective containers carrying radioactive materials within the.
I Installation. Pointers on architectural planaLfig, construction elements and-in-~
terior finishing are given* The subject of hot chamber locatioti.and so"
Card 2/3
_77

t 41684-6.5
ACCESSION MR: ATSW3176
architectural toiutions ar'e reviewed. Conditions favoring separafe hot chambers..
within each individual building versus the provision of a separate-hat chamber
building within the installation, are discussed. Constructional Integration of
I hotchambers is discussed, with the alternatives of.embedding the primary strue-
tural membe a in the chamber walls or of designing the chambers themselves as primary
structural members. Flexibility lit the architectural approach, with adjustmert
to the specific needs of the installation, is advocated. Orig. art,has.* 11
i figures.
ASSOCIATION: Kafedra strottellstva
,yadernykh uitanovok Haskovokly.inzhenertio
0 q tion of Nuclear L ring
stroitel'nyy institut, (Department for the Con tr*q, Eng nee
Installations, Moscow Engineering and Construction Institute)
ENCL: SUB CODE4. NP
SUEHITTED: 00
No REY S010~- 006 OTM:. 004
'oo)xf
'Ccwd 3/3.
7
77

SHCHUKIN, V.R., inzhoner.
..W. ~,-
L Shortcomings of the multiple firing method. Bezop.truda v
prom. 1 no.8:8-10 Ag '57. (MLFLA 10:8)
l.Nachal'nik upravleniya Stalinskoge okruga Gotgortekhnadzora
SSSR.
(Donate Basin--Coal mines and mining)

SlIGIMIN, V.R., lnzh.
Evabiating the safety, of roof control methods at Donets Basin mines.
Bezop.truda v prom. 2 no.9:6-8 S '58. (MIRA 11:9)
l.Upravleni3re Stalinskogo okruga Gostorgtekhnadzora USSR.
(Donate Basin--Coal mines and mining--Safety measures)

SHCHUKIN, V.R., inzh.
Brigades of Communist labor in Donets Basin mines. Bezop. truds, v
prom. 3 no.6:1-2 Je '59. (MIU 12:10)
l.Nachallnik upravleni7a Stalinskogo okruga, Gosgortekhnadzora USSR.
(Donets Basin--Efficienc7, Industrial)

SHCIRMIN, V.R., inzh.
Improving technical mine inspection. Bezop. truda v prom. 3 no.11:
26-29 N '59- (MIRA 13:3)
1.Nachal'nik upravleniya Stalinskogo okruga Gosgortekhnadzora,
USSR.
(Mine inspection)

SHCHUKIN,_V._R,.inzh.; BERDNIKOV, M.D., inzh.
Over-all inupection of caol mines of the Stalino Economic Council..
Bezop.truda v'prom. 4 no.6:27-28 Je 160. (MIRA 14;3)
1. Upravleniye Stalinskogo okruga Gosgortekhnadzora USSR.
__ (9-ta-lino Province-Mine inspection)

SHCHUKIN, V.R.
Safety neasure3 in b.:-ring coal intercalations. Bezop.truda v prom.
5 no.6-3-5 Je 161. (MIRA 14:6)
1. Nachallnik upravleniya Stalinskogo okruga Gosgortekhnadzora USSR.
(Coal mines and mining--Safety measures)

SHCHUKINY V.R., inzh.
Improving work safety in mining. Bezop.truda v prom. 5
no.7:35-36 J1 161. (MIRA 14:6)
1. Nachallnik upravleniya Stalinskogo okruga Gosgortekhnadzora
USSR.
(Coal mines and mining--Safety measures)

V R
Efficiency methods for the control of sudden outbursts. Ugoll
Ukr. no.11:41-43 N 61. (MIRA 14:11)
1. Machallnik upravleniya Stalinskogo okruga Gosgortekhnadzora
USSR.
(Mine gases) (Coal inines and min;np--Safety measures)

SHEVYAKOV, L.D., akademik; IVANOV, A.M.; BUBYftrI V.A., gornyy inzh.;
f-UNIN, M.I., gornyy inzh.; NEKRASOVSKIY, Ya.E., doktor tekhn.-
nauk; SHC'.JTT!~Tlli, V.R.
Readers' response to A.A.Shamin, A.M..Belenlkii, and A.V.Galkinfs
article "Pillar systems of mining flat seams without undermining
the wall rock in the development operations." Ugoll Ukr. 6
no.9:43-47 S 162. (MIRA 15:9)
1. Upravlyayushchiy trestom Rutchenkovugoll (for Ivanov).
2. Gosudarstvennyy In.3titut po proyektirovaniyu shakhtnogo
stroitel'stva v yuzhnykh rayonakh SSSR (for Bubirl, Monin).
3. Dnepropetrovskiy gornyy institut:(for Nekrasovskiy)-.
4. Nachallnik upravleniya Donetskogo okruga Komiteta po nadzoru
za bezopasnym vedeniyem rabot v promyshlennosti i gornomu.
nadzoru pri Sovete Miriistrov UkrSSR (for Shchukin).
(Shamin, A.A.) (Belenlkii, A.M.) (Galkin, A.V.)

KHODOT, V.V., doktor tucklm. Paul-, red.; BOBROV, I.V,, kand. tel:hn.
nauk., red.; HUD'-".HEI;KG, red.5 TAB~'dCV, A.G.y red.;
SECHUhIll, V..-*. , ---ed. ; HI'LIE.CV, A.F., red.; Y.51. y
otv. red.; SFJIT-'L-KCjv) F.D. otv. i-ed.; FO~IATC,.- V Iotv
Y . .)
red.; Yu,S., otv, red.j VII:CG.--,',DC-V G.V., red.
izd-v.-; IL'E'SKjVYA, G.E., 'Vehhn. red.; DCILDYIT~EVA, Z.A., te-khr.
red.
[Control of sudden outbui-st~7 in coal r.ines; proceedings of the
--cientific and technical conference held in -,onets in December
1960JBor'bL s vnezapNnnd irybrosani v ugol'nyl-h shak-htak-h; sbor-
nik trudov nauchno-tekhnicheckogo soveshchaniia, sostoiavshe-
aosia v i,-or. Donetske v de*vabre 1c)60 C. Eosk-va, Gosgortekhiz-
0
d,,t. 1c,62. 602 p. (I-MR-4 15:9)
I I
1. In:~titut gornogo ~:ela imeri A.A. Sk-ochinskogo (for Khodot).
2. Kombinat "Donetsk-ugol"I (for Hudchenko). 3. Gosudarstven-
nyy komitet pri Sovete I'inistrov Ukrainskoy SER po nEdzoru za
bezopv-snym veder-iyer. Tabot v p-formychlennosti i Cornoim nadzorus
Donetskiy ok:t-ug (for Shchukin).
(Coal mines and mining.-Safety r.;r-aaures)

-nzh.
lImprove mining control. Bezop. tnuda v prom. 7 no.12:
-2 D 63. 18:7)
i challnik ~~rxwrleniya Donetskogo ok-ruga Gosudarstvennogo komiteta
N
L
1-r- ~~ovcte ,1~114s~rov Uk- po iiadzc-.-u za hezopa5n~-, vedeniyem rabot
gc-ncrmu nai.[?~omi.

EtATTS, Nmmanuil Genrikhovich, kand.tekhn.nanak; TSEITILIN, Shalom Tudovich,
kand.tekhn.nauk: MASARSKIT, Aba Solomonovich; SH --V kt-, 7
_-=124 1 Q- -
SemenovIc'-, starshly inzh.; UKRAINCHIK, N.M., inzh., red.
[Large prestressed coterets *Double TO slabs for roofs of buildings)
Predvaritellno napriazhenuye zhelezobetonnye krupnya P#fiL$li
Ildvoinoe TO dlia pokrytii zdanil; iz opyta NIIZHelezobetona i
savoda No.22 Glaymospromstroimaterialow. Moskva, Gos,,izd-vo lit-ry
po stroit., arkhit. I stroit.materialara, 1960. 27 p.
WRA '14:12)
1. Akademlya stroltellstva i arkhitektury SSSR. Institut organi-
zatsii, mekhanizatsii i tekhnicheskoy pomoshchi stroitellatvu.
B7uro tekhnich6skoy informatsil. 2. Zaveduyushchiv 2aboratoriyey
sbornykh sholesobatonnvkh konstruktal~r Nauchno-iseledovatellskogo
inBtituta zbelezobatonnykh Izdeliy i nerudnykh materialov (for Ratts).
3. Zavaduyushchiy sektorom luzhenernykh konstruktsiy Na-dchno-isaledo.-
rate!Oskogo instituta zhaletobstonnykh izdeliy i neruduykb note-
rialov (for TSeytlin). 4. GlavW7 iuzh. zavoda No.22"Glarmosprow-
stroymateriala7 (for Nasarskiy). 5. Nauchno-issledovatel'skiy
institut zhelezobatouuykh izdeliy i nerudrykh materialov (for
Shchukin).
kFrecast concrete construction)
(Roofing, Concrete)

USOV, Nikolay Iv-~lnovich; ISTIMIKZ Valentin Timofeyevich; G-UiFE~JI~7
S.Yu., nauchnyy red.; UD~'.LITSOV , O.A. '(~r-DZj:TYEjIA
A.N..? tekhr . red,
[Even in days of peace there is room for heroic deeds] I v
r.irnye ~ni est' mesto podvigain. Leningrad, Ob-vo no raspro--
str.neniiu polit, i nauchn. znanii -PSFILP,, 1962,. 50 P.
(DMA 15:10)
(Labor and laboring clnsses)

I
0

AKIMOT, N.I.; YOLKOT, S.F.; KONOYALOVA, N.A.; OSINOTSKATA, R.I.; PLISKO,
Tu.Tu.; S3TMOT, H.N.; STEPANOT, L.A.; SHCHUXINoi T.Ta.; VORONI-
ClDff, M.P., red.; TSARKUKO, A.P., red.; YBRINA, G.P., tekhn.red.
(International railroad transportation] Mezhdunarodnye zhelezno-
dorozhnys soobshcheniia. Pod red. M.P.Voronicheva. Koskvag Gos.
tranap.zhel-dor.izd-vo, 1959. 242 p. (MIRA 13:2)
(RaJ!roads)

SHCHUKIN, V.Ya.
International transportation organizations and the part
played in them by the railroads of the U.S.S.R. Zhel. dor.
transp. 41 no.5:78-84 My 159. (MIRA 12:7)
1.Zamostitell nachallnika upravleni3ra mezhdunarodnykh soobahchaniy,
Ninictorstva putoy ooobahchaniya.
(Railroads)

5F!CHI)NIN, 11.1,.Ya.
~;ooperation of socialist countries in t!-.e field of transportation.
Zhel. dor.transp. 43 no.!C:E3-P-7 0 . (M-IRA 24:9)
1. Zamestitel' nachal'nika Upravleniya mezhdun-srodnykh -
so3bshcheniy MinisterFtva putey soobshcYeniya.
(Raillroads-International cooperation)

PA lit I KFvFVy "; . H, y I n;-,"h . , ";H~' I ill KIN Y- , I r, L, Ih .
-
Fo ri -. on t a 1 .',) r z e I n te -r ac -!, I -:~ r o f nu-n n 4 n. = w n ~- e I s - ~ ~- ~- t --~- -- -! ~- -
cranes. Vest. mash~Jnos tr. 45 no. -- , 331-J4 17 E., I ;:~ c .
3
J;~ %)
~ - .

SKHUKIN, Ya.A.; :,ELESHKO, I.S.
Changing the d~!aign of supporting walls of sliding pipes in a
continuous furnace. Sbor.rats.predl.vnedr.v proizv. no.5:34-35
,6o. (MMA 14:8)
1. Magnitogorskiy metallurgicheskiy kombinat.
(k"Vrnaces, Heating)

FEDORMOY N.; SHCHUXIN, Ye., kand. ekonom. nauk
Production of synthetic materials should have a stable raw
material base. NTO 5 no.3.*43-44 Mr 163. (MIRA 16--4)
1. Chlen-korrespondent AN SSSR, predsedatell ekonomicheskay
sektsii TSentrallnogo pravleniya Vaesoyuznogo khimicheskogo
obshchestva imeni Mendele3reva (for Fedorenko).
(SYnthetic products)

SHCHUKIN, V.ya.
- ---- -
Expansion of international communications Is an important f.actor
ror the strengthening of economic and cultural relations. Zhel.
dor.transp. 42 no-9:37-40 S 6o. (MIRA 13:9)
1. Zamestitel' nachallnika Upravleniya mezhdunarodnykh
soobahcheniy Ministerstva putey soobshcheniya.
(Railroads--Internation cooperation)

MOUS"Y, Nazim; PAVIOV, M.M. [translator]; SHCMKIN, Ye.A.. redaktor;
SHA.POVAWV, V.I., tekhnicheskiy re&Wto'_r. *
[The water problem i--, Syria] Vodnaia problema v Sirii. Perevod a
frantsuzakogo K.M.Paviova. Predial. A.P.Oreshnikova. Redaktor
E.A.'Shchukin. Moskva, Izd-vo inostrannoi lit-ry, 1954. 283 P.
(MIJU 8:2)
(Syria--Water supply) (Syria--Hydraulic engineering)