SCIENTIFIC ABSTRACT STOROZHUK, YA.P. - STOTIK, A.M.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001653410018-2
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 3, 2016
• Document Release Date: August 26, 2000
• Sequence Number: 18
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

A. il.
of Stll~, r lf~ c tr ic
tlm* rospirrAor"r f A C~,t. zt,~Ir. 49
:1145-1352)
1. L.Io.-Acriyu flziolc~j-lli Inctitilt-a f"ZiolrizIl
Jr.q.:11 A.A.

SILRULN11K, V.M.
N the 44~ Iked - !~tentlsl of the -eribvtj cortex w1th Initial
nqgHtIvity. Fizial.thu.-. 50 no.lz2O-25 Ja 064.
(MIRA 1841)
1. Laborst-orlya elski,rcCiziologii Irst4.tA4,A fiziologli Im6ni A.A.
Bwr,aol1'.9a AN Ukr.,~-, Kiyev.

V
J. Lo (1)"ont)i Cbervyakova, X. 1. (Candidate of bioloi;ical
V4n ;'yt (Ampirant)i ValyavskAirs. M. T*. (Fn4lnear); raushanskaj%,
5torothuk. V. 1. (&gIAo*r)j 'serlstakaya. 1. A. (MCIns'
(Ln4imor)
non.]
3oircri for now op"ratihC conditions In sterilItAtion of ~&AnW goods
for
pra_'~-cted continuously operative equip"nt
Mnistorstyo vywshov-o i smlnoro spetsUllnogo *br&&*v&nIya.
promyshlonnosLI, no- 31 1~~. 10)-112
74'ZI food to
chnoloj-y, food proearvation. fload storilitAtioA. applied
food product machinory. processed plAnt product
';-w oporative conditions for starilittr#4 0-or-ato 4uloo In " Oderas factory
'.'Orcol oitt. at the 016s#4 Uchnalogic*1 Inatitutp for the Food &M Refri4oration
-try, b4swi on a continuous operation (see IFIr4re 1) with successive best
Ing
cooll.n.: of 0.5 and 0.2 litor battles fUled with juice at 80-83 C and Imersod in
of various temperatures. Dig atariUzation tem;eraturte tested varo too, 95,
nessurod with
thors"OUPU. Dig
C. -Ptaparaturoe
bottle *enter
wer*
a
in the
ar.1 92
Card

ACC NA A-,1;02'/l ~6
.. ~VA,
Figure 1. Schematic representation of continuous sterilization
dalvi w,)re mthanatic*111 processed according to naueenbamm, a. 1, (P%sbchev&ya
tek~nolozly.-- 3. 1959). Zarlier studios on survIT&I of x1croorganisma In tomato
war* also conoldored. Ike formulas arrived at were exp*rUwntAUy tested. Ike
general foruula applAod, was
A (KA. + ICA. + KA. + + KA.~'
Lc-,,i

C foc
~t, T is tho t1r.- int-rvail wi
r i-% r--M-I ~1~e I-nrnxW1z1n*, rop,'flc~.-nt. ",n valet of w.s
.-I .:- 1',,'Ator fo; storthrAtion. r,
!-"-~rn -i 2S P%Ln for 90 C or 1-2~ ?%.r. f'-r
ir
vr-'(,7t coul-I b" ohtatr^-1 :6': f4zt~?- A,. :Z,~ C
--jj
'n,' 0.2 'bott'Aw 4'. L)"O sano t"j-r4turo. ior 'Ln-P
'I:,aros uaro empArAble to or hl.-.1hor than the 21der orms.
0' -ho stnrilir-ition fornulAs ul*.h luice Infoctwl viuh Panicillium
,is niz"r. yeasts and Bac. rAsontftricus ruber. then sterilized
AAM kept at roam tonporstura for 3 months or at hl.~hor
k-01 dAyl. r4VO SAtisrse.-tory rowsults. 2io forAulAs vorkod out or*
A~',l W C Poml for the 2 #Ito* of %,ottlkas. 'Zius for 0.2 liter bottles
00 C. uh-re the first fliuro IhJkCAtO* that the
;,rf.--ess peo;~-tr is starting. the soconl gives the storIlIt4tion period.
&r.1 fifth give sto;wdisa coolln* In water betho of 60. 60
tnat the formulas found he
o- I goon proved reliable in
t,)sts. Orig. art. hast 10 fl4uros and 8 tomulos.
(ZW SUM DA-M rArw/ ORM RVI 0041 am Wo 001

STOR)MUK, U.P., kitnd. tnkhn. nnuk; "IM,75KIT, Z.H., krinl. toik-hn. nai&
Himning, fuel oil in the convyustion chamber of gati-turbine
Installations. Unnrgomashinnstro4nis 4 no.10:24-28 0 158.
Was turbinam) (MIRA 11:11)

s/ii4/62/000/003/001/005
A(;T,'IuR; Candidate of Technical Sciences
T IT LE The operation of multi-swirler gas-turbine
combumtion chambers burning liquid fuel
PL-1110DICAL: Energomashinoi%troyeniye, no-3s 196"", 3-7
TLXT: As combuAtion tube diameters increase, the effective-
ness of single swirlers falls off and combustion efficiency is
it:paired; accordingly multiplo swirlers are being used with
large combustion chambers. The TsKT1 has tested three
geometrically similar combustion chambers with flame tube
diameters of 640. 510 and 4oo mm. The tubes were made of steel
1 1,1 IT (EYaIT), and the tube head carried five cylindrical
swirlers with profiled blades installed at an angle of 6o0.
Below the head came five conical shells which overlapped with
gaps between to admit cooling air. Air from the compressor
liaving passed through the air heater is delivered to the bottom
of the chamber outside the flame tube. lt enters the tube
partially through a mixer located below the conical shells. partly
Card 1/4

The operation of multi-swirler ...
E194/E155
through the gaps between the conical shells and partly through
t1he head. To Improve cooling, the top two shells were ribbed and
then firing rates of about 30 x 106 kcal/m3 hour.atm could be
achieved with satisfactory combustion. Wien necessary the primary
and secondary air supplies could be kept separate. The
temperature distribution was measured and gas samples were
tests were run on diesel fuel with excena-air
analysed. The
factors between 1 and 2, with an Inlet air temperature of 100 to
300 OC at an inlet Pressure of 1.25 to 3.8 atm, with a fuel
CODSUnIjition of 136 to 490 kX/hour and an exhaust gas temperature
of 6do to 700 OC. Single-stage centrifugal nozzles were used.
Thr process of fuel combustion was practically identical In all
three chambers over a wide range of gas flows. To assess the
effect of pressure, tests were run in which the pressure alone
was varied, usually between 1.5 and 3 atm, and within this range
the nature of combustion was identical for all the chambers
te5ted. In multi-swirler combustion chambers the fuel is well
mixed with primary air; combustion is complete near the burner
throat and the flame temperature is high. The main factora that
Card 2/4

'ne oi~eriition Uf multi-swirler s/114/621/000/003/001/005
E194/EI35
limit t!ie rate of f iring are the chanber diameter and the rate or
'Sir f lour at discharge. from the swirlers, which governs the
titz-bit lence. The smaller the chamber diameter (and naturally,
therefore, the diameter) the greater the maximum possible
r.ttc of' firing for a given rate of gas flow. The combu3tion
efricleticy can be re-presetited in terms of the same parameters an
those used by %.G. Woodward (Ref.2: Sixth Symposium on Combustion,
Re in' provided that they are written in
I
~iold lub. Corp., 1957),
terms or thp rate of riow of air (by weight) at discharge from
the swirlers. The distribution of air between different parts of
the combustion chamber is disciassed. As the ratio of the air
inlet to the discharge temperature alters, the air distribution
alters because of' differential. expansion of the chamber body and
the fire tubes. The cooling air was not uniformly distributed
,Ijnojlg the slots between the conical shells; and because the
expansion is greatest where the metal is hotter, the parts that
require most air receive least. This point should be allowed for
in desisn. The flow structure was identical in different
,coractrically similar combustion chambers. The axial velocity
Card 3/1,

The uiwration of rmilti-swirler S/114/62/000/003/001/005
E194/EI55
,listribut ion is practically
sectiun. The tests provide
processes or mixing of individual
with pulverized fuel and so
influence on the process of
multi-swirler chambers.
There are 7 figures.
symmetrical acrosts the chamber
a qualitative assessment of the
layers of gas-air mixture
make it possible to assess their
combustion stabilisation in
Card 4/4

o f
al'a 1; aO
Oo

on
t; U

6111--li-42'1000100410C 1 '008
E 114 /!;,L 54
No,
prit-I error
r: Cq
w, AI W d C;I~.
o o r, v v~,, vy n~; J T) thl~' rZ3,31
L ~Icl
;.-i0oth o-com nt
1; o r.-A t empe, ra ture
f; i on there was
Of ca r. temperature
It).- 0 f '-,-14.,.
".I t jcon.,.O.'aal., ;~,crmai loading,
~I;kce~;j ~-mEl Inlet a.'r witli -al,e,;noldls number in
ik.-~uLjr FyAp weLve left to vary with presoure.
Although
~Lj-y of' C0014n-- aj- -re
increa6ed wit'a pressjxe, 4-1
q,j j r
of the burner hv~.-acx and the fIrs"11 segmento which
*Wkulile ODD03ite the zones of incomplete comba.,;Z;io.,i rose
("a rd 3? 41

i -,,~A 2/C,00/004/001/008
X. -114 514
6 011 f r 0 MA 0 0 6
p 0i, of 3000C
0 U IA ILo X'L 10 norirest the
o thr.- cold
:4 uloi* `ro~i uiv jl,ii,U; exposed
un ;oo
The
~r~~a ly x-, uenced by
I;Onv;~(;t.lon on Li.~! S-ku~,* bY LIVI I),'10.-;iA e 0 Vr
'I;.; i u b ecoc~lino improved
by tlie (;I1111',Aon oAr ,,o*6 'maseS by coolin.; air t ough
I hr
L A..!: ~ 17 1'31 fle,~ A,; rl,~ 1; 0 wall
I A
from
'C"; Ion wa: Nu 0.03
Conv, I Re where
th--~ effe-ot;ive Rf!yno'd.-; nwaber. J%
nomogram is given to
tz,e maxiiau;a ;eza.pera Lure of 'VeAe flamu tube segments.
Card 4/4

STUPI)ZHUK, Yrt,P., K rind. ts4, hn. nni.~r . ANP'NC'q'SKIT~ V I , 'Anzh.
I wammmmm~-
Methorim for c,%I'(-,ulottAnv ~hp mnximum temperature of the flues of
the comblisticn chamlerp of gma turbine ayst,~np opornting on 11pid ,
fu,pl . Fnergomashinn5tr..-4~naf~ 1) r,,.,. 1-47-44, J'I '63. (?rARA 16:),)
(Gns turbines)

ACCESSION NRa AP4007443 S/0096/641000/001/0039/0063
A777!07: _.S_i~9r.qzhuk,_Ya. P. (Candidate of technical sciences)
Aioskov, V. A. (Engineer)
TITLZ, Problem of approximate modeling of the combustion processes
in a GTU (Can turbine unit) combustion chamber
SOURCE: Teploenergettka, no. 1, 1964, 59-63
LoriC. TAGSt gas turbine, combustion chamber, combustion process,
combustion process modeling, liquid fuel combustion
A35TRACT: SI-ilitudc laws for ncaling-up gas turbine combustion
chamber models to full-scale units are analyzed on the basis of a
generalized relationship for the combustion efficiency in terms of
fuel droplet residence time in the combustion zone; full combustion
time; evaporation, mixing, and burning times; Reynolds, Karman, Mach,
and Prandtl numbers; fuel and air temperatures; air excess factor,
and activation energy. From a previously derived relationship for
the evaporation time (Yu. Kh. Shaulov, H, 0. Lerner. Goreniyc v
zhidkostny*kh reaktivny*kh dvigately4kh, Oborongiz, 1961) the
"~,-d 1/4
1

ACCESSION M AP4007443
following criterion for the complete evaporation was derived:
Wev a 9
where C Is Y273/SDRO(tk + 273), dk Is the characteristic droplet
d I ar! !ter , Lf i is t e f lame-tube length , tk is the vapor temperature ,
y is the specific weight of fuel, D., is the diffusion coefficient
at O'C and 1 atn, and wav is the average gas flow velocity. The
Invariance of the ratio of mixing time to residence time with respect
to Pe, Fa, H, and Pr is examined, and sclf-modeling regions of Re
and Ka are defined. It is concluded that for modeling of a diffuSiOnAl
conbu5tion process in chamberi operating under self-moldeling regimes
wtth :espect to Re and Ka# the following conditions must be fulfilledi
1) the nodel and the full-scale unit must be geometrically similar;
2) the fuel must be of the same type and have the same temperature;
-ind 3) the fuel-air ratios, the temperatures of air and combustion
productm, and the evaporAcion crtterLan wev inuat he tdontLVAls Thp
Card 2 /14

ACCESSION N'R: AP4007443
results are illustrated by data obtained previously (Yao Pe Storexhuko
"ner,-onashinostroyentye, No. 3, 1962) by the combustion of atornized
solar oil in high-output combustion chamber models 0.61, 0.51, and
0.4 m in diameter. The graphs (see Fig. I of Enclosure) show that
the combustion process was almost identical in all three chambers
when the specified modeling conditions were fulfilled. Orig. art.
has: 17 formulas, 3 figures, and 2 tables.
ASSOCIAi1OXi Tsentral'ny*y kotloturbinny*y institut (Central Boiler-
Turbine Institute)
SUBMITTED3 00 DATE ACQ: 23Jan64 ENCL: 01
SU3 CODE: PR NO REF SOV: 003 OTHERt 000
Ca,d 3/4

5/0W6/6h/oW/00~'0039/0042
;!0:1 ;Q-1i AP4012339
A'o-M'0iZi Storozhuk, Ya, P. (C"idate of ttechnJcal sciences); Antonovsklys V. I#
(aiginoar)
A, attidy of Uio onis3ivo pruportio3 of a flamo in a single dapper combus-
tion cliarrboo of a Cai turbine
SOORCEo Tej)looncrj-,ot1kn, no, Z, 196hp 39-U
!A6.-jj flamo omisnionp combustion chanber, air pressurej excess air
COO:ficlanb, amisslon diotributionj flue coolinG, platimim platinum rhodium
Liioriwcouplo, vacuum radiation thermal element, thermal radiation flux,, gas
blacknoss, Infrared radiat ion
ABS' =Ti Ono of tho problore uldch arose with the construction of the experl-
menW gas turbino combustion chamber was the cooling of the fluo motal. The
development of a reliable mothod for calculatine the wa1l temperature was hxqe6d
by the absonce or experimental data on the emission characteristics of f1wa.
Experiments ware conducted varrizw, several paranoters (principsUr the air pressure
and tho coefficient of excess air)* The chamber. had a divided air nTply ror
1A

ACCESSIO14 M AA012339
I independent control of primary and secondary air. Two types of flues were studied.,
both 364 mi in diameter and joined to a transition cone. One flue was continuousi
the other in 3 sections,, with a 4-m annular Cap between sections. For experimen-
tal purposes 2 dampers with a 450 and 520 tUt were available. Diesel fuel was
sprayed from a centrifugal single-staGo Jet with a 750 flame. The variables of ths~
air and fuel, the flame temperature, the normal total thermal raiiation and gas
com,osition wore measured. The latter three were taken at the same cross section
at t points along the flue, The flame toq)orature was measured with a auction
platimtm jilatinum-rhodium thermocouple, The rross flame radiation (luminous
brir;htnoss) wazi measured with a vacuu;4 radiation thermal element (RTE) Vith 2
sensitive elements, one of which was used for comparison of the surrounding temper-.;
aturo, It was sonsitivo"to inrrars.-d radiation in the band 0*18-11 tA vldch vas
suitable according to the stantards of D. 1. Weeks and Os A, Saunders (Journal
of the Inst, of Fuel,, No. 209., 1958). The proscribed normal operating conditions
6
wore: volumotric thermal stress; 4 8 x 10 largo calories/m%hr atmosphere,
excess coefficient or primary air cK 1,15-1,8, air flow rate up to 5500 kc/firs
air toiVoraturo at chamber inlot ti) 60~200C, pressure in Uio chamber p a 1.05-
2.0) atriospheron, and temperature of exhaust eamos tOx 500-740C. The exporizon.
.al installation permitted variation of each parameters The firat studies varied
21%

'S 1 ON UR
ti,o a,ir coafficiont. Tho radiation incroasod to a Creator extent. In the
stNatlnjiD of the fluo atyl with lower air (;.,I'- - 1.2-1,5),, An increa3o in
4Ai,j iiitako air teq)eratiro lod to a docroano in ti-j.) radiation at the measuring
v-, a rest0t, of tho rhiftir4; of the active (:,) 17!f3tion zones to the flano
roo". The next -.tudy (corKlAict(Y.1 only on the spi:monted fluo) varied the charb(T
The radiation charply increazod with an increase in prossuro at the
firsL 2 meanurAng pointap ejpocially with 4 snaU 0 0,90
M
posterior
4
7,5 0.4 t
4.3 0.41 I
>ONO &23j-0.6;
A
403=0.64 O.SO
Com
,
aupragtIca
I
d
orsa a
-~
Con tro I o 3 S.13-4.43 7.33-:-0.73