TECHNICAL SPECIFICATIONS OF THE SOVIET AI-20 TURBOPROP ENGINE

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80T00246A069600020001-7
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 22
• Document Creation Date: December 23, 2016
• Document Release Date: September 4, 2013
• Sequence Number: 1
• Publication Date: February 24, 1964
• Content Type: REPORT

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CENTRAL INTELLIGENCE AGENCY
tains Liformation affecting the National Defense of the United States within the meaning if the Espionage Laws, Title
793 and 794, the transmission or revelation of which in any manner to an unauthorized person is prohibited by law,
S-E-C-R-E-T
NO FOREIGN DISSEM
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COUNTRY USSR
REPORT
SUBJECT
Technical Specifications of
the Soviet AI-20 Turboprop
DATE DISTR.
0,29 February
1964
Engine
NO. PAGES 1
REFDCAIrC
DATE OF
INFO.
PLACE &
DATE ACQ
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THIS IS UNEVALUATED INFORMATION. SOURCE GRADINGS ARE DEFINITIVE. APPRAISAL OF CONTENT IS TENTATIVE.
S-E-C-R-E-T
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GROUP I 1
Excluded from automatic
downgrading and i
declassification
STATE I MA I ARMY I NAVY I AM
A IR/FTD
ARMY/ VST C
(Note: Field distribution indicated by "#".)
I NSA
XEt) NIC I OCR SAC
00/FDD
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No Foreign Dissem
?
SOME TECHNICAL SPECIFICATIONS FOR THE SOVIET
AI-20 TURBOPROP ENGINE
(FROM A RUSSIAN-LANGUAGE PAMPHLET)
e
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bRON 1
Eattiode tom Witt
docirldieg?
' ? tIsc11ca1les
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[Note: x-x-x means word or symbol illegible in document.
Underlined word or symbol means guess because of near-
.
[Page 7]
I. ENGINE BASIC DATA
Designation AI-20
2.
Type
turboprop
3.
Rotation (of prop and rotor
looking from exhaust nozzle)
left
4.
Compressor
?
type
axial
stages ?10
pressure rise, nominal mode.
(H = 8000 at V 175 m/secY
calculated 8.5
5. Combustion chamber annular, ten burners
6. Turbine
type
stages
7. Exhaust nozzle
type
exit cross-section, m2
axial
3
fixed
0.225
8. Reduction gearing
type planetary
radio 0.08732
9. Prop pitch control
type
x-x-x power measured by
torque meter hp
S-E-C-R-E-T
hydraulic
46.Rikm (oil pressure in
meter cylinders, kg/cm2)
.0/
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10. Roor rpm
idling
all operating modes, ground
and air
11. Fuel consumption idling
12. Max Perm. gas temp. At start
(fire up)
13. Max perm. measured gas temp
after turbine, all modes and
altitudes
14. Engine permissible continuous
operation
take-off mode
pominal and cruise modes
15. Transition time from idling
to takeoff power, during e.
pick-up
16. Fuel (running and starting)
1
[unnumbered
? Fuel system units
a) booster fuel .pump
designation ?
type
trans. ratio
rotatIon .
b) main fuel pump
designation
type
trans. ratio
rotation ?
v) fuel nozzles
designation
'type
number
10,000.+ 200
12300+90
380 kg/hr, max
7500C (recommended use of
partial cut fuel to avoid
exceeding)
520?C
15 min (max
unlimited
15 sec (max)
T=1, GOST 4138-49
Ts-1, GOST 7149-54
T-2, MNPTU 535/55
page -- 8?)
707 I
rotary
0.1854
right
348 I
piston
0.3937
right
FR-20
centrifugal
2-duct
10
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? b-r.;-?3.-rt-b-w
No lbreign Liss= 50X1
takeoff mode fuel pressure
before nozzles
18. Oil grade
19. Oil consumption
20.? Lubrication system
21. Oil pumping through
engine on nominal mode
a) oil entry temp 80?C
22. Heat transfer to Oil on nominal
,a) oil entry temp 80?c
23. Oil temp. on sustained modes
a) on entry into engine '
min permissible
max permissible, not
more, than 15 minutes
continuous op'.n
recommended
b) on exit from engine, max
permissible
2. Lubrication system units
a). main oil pump
designation
type
trans ratio
rotation
output (at 12,300 rpm,
70-80?C oil temp
74 kg/cm2 (max)
oil mixture 75% transformer
(GOST-98256)
25% MK22 or MS 20 (GOST 101349)
1.5 kg/hr (max)
pressure circulation
135 lit/min (max)
850 kcal/mih (max)
40DC
90o0
70-80?C
115?C
GMN-20
piston
2-section
0.4821
left
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1) delivery stage Under
input preAsure 0.6-
0.8 kg/cm and back
pressure 4 0.5 kg/cm2
2/ scave4ing stage undeg
back pressure 2 kg/cm'
aux oil feed pump
designation
type
trans ratio
rotation
output 0.121,00 rpm
0.6-0.8 kg/cm' back pressure
oil temp 70-80?C
v) air separator
designation
type
trans. ratio
rotation
g)
240 lit/Min (min)
275 lit/min (min)
MNP-20
piston
0.5509
right
x-x-x
[page 9] .
pump for scavenging oil
from oil line of combustion
chamber housing
designation .
type
trans. ratio
rotation
output at rotor speed,
12,300 rpm, 0.5 kg/cm'
back pressure and oil
temp 90-100?C
IKM oil pump (torque meter)
designatiOn
type
trans. ratio
rotation '
output at 12,300 rpm,
80 kg/cm2
back pressure
VO-20
centrifugal
0.5509
left
MNO-20
piston, 2-section
0.5509
left
80 lit/min min)
MIKM-20
piston
0.3097
right
15 lit/min (min) -
- -
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r0
/ -
ye) centrifugal vent
type
trans. ratio
rotation
zh oil filters
type
number
25,. Oil pressure, main line
all modes on ground
idling
2?). Control system elements
a) auto 4uel.control unit
designation
type
trans. ratio
rotation
auto control range
b) prop rpm control
designation
type
trans. ratio
rotatiOn
27. Propeller
designation
type
diameter
28. Auto feathering sensor
type
29. Starting system elements
a) starter-generatoi..
designation
b) ignition.
1) coils
designation
number
drive
0.92
right
gauze strainer
2
4-4.5 kg/cm?
3.0 kg/cm2 (min)
KTA-5
hydraulic
0.4265
len
? 1000-13100 rpm
R-68 I
hydr-centrifugal
0.4602
left
AV-68 I
front,'four-bladel
? feathering.
4.5 m
electro-hydr
STG -12 TM
UN-
2
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[page 10]
plugs
designation.
number
v) starting rpzzles
type
number
fuel pressure before
nozzles
? start fuel feed valve
.type
starter-generator
cut out during starting
designation
tYPe
engine rpm at starter
cutoff
. system elements
a) icing indicator signal
.designation
type .
eleCtr control of by pass
Air for heating compressor
guide vanes
designation
31. Equipment for engine and aircraft
operation
,a) start4r-generators
designation
number
trans. ratio
rotation ?
permissible drive power
generator mode voltage
current .
starter mode average current
voltage
SPN-14.
? centrifugal
2
2-3 -kg/cm2
electromagnetic
VE-2S
electrohydraulic
4500-6500
SO-12 AM
pneum-electr
N2-5
STG-12 TM
2
0.5396
left
40 hp (max)
30
400'a
450 a (max)
214/48
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b) generator
designation SGO-8U
type ac
trans. ratio 0.3305
rotation right ?
permissible drive power 15 hp (max)
v) hydraulic pump
designation 435 IT
type plunger
trans. ratio 0.1673
rotation right
permissible drive power 15 hp (max)
g)
,
engine rotor rpm indicator
pickup
designation DTE-2
type elect
trans. ratio 0.194
rotation. right
r
fuel lever position
indicator
pickup
designation
type
UPRT-2
electromechanical
'ye parking brake w/control
mechanism
control mechanism designa-
tion MZKL2 .
brake type friction-disk
trans. ratio 0.4602 ' ?
rotation , right
[unnumbered page 11?]
32. Engine dimensions, mm
length 3096 5
width 842 +-5
height 11807? 5
33. Engine dry wt, kg 1075 2%
34. Guaranteed service life to
initial overhaul 200 hrs
-0
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Notes:
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.4
I. Air bleedff behind engine compressor is permitted;
a) routine: - on modes from 0.2 nominal t?akeoff inclusive,
at all altItudes for pressure boost, ventilation and
pressurizes cabin heating -- 0.18 kg/sec.
in takeoff mode on the ground -- 100 kg/hr
b) extra: - periodically, for deicing other
equipment -- 0.12 kg/sec
II. Engine power and economy may not match specifications here
with on-board equipment under load and air bleed-off operating.
Directions of rotation are in accord with GOST .153o-46.
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page 16]
The engine automatic system includes positive and automatic feathering
of prop blades. Automatic input to the feathering mechanism is controlled
by an automatic feathering sensor installed on the forward engine housing
and operating off -91e pressure of the oil in the torque meter. The prop
is automatically feathered only on modes greater than 0.9 nominal and
only when the prop power in these modes drops to 450-350 hp or torque
meter oil pressure drops to 8 11' 2 kg/cm2.
? 1
To prevent prop and rotor windmilling when parked, the engine is
eqllipped with a friction brake for the prop; the prop brake is applied
.and released by an MZK-2 electrical mechanism.
For suspension on aircraft the engine has four trunnions, two
forward ones in the horizontal plane on the housing and two rearward
on the butt flange of the compressor and combustion chamber housings
set at 70 downward from horizontal. Figure 5 is the engine suspension
diagram.
e'
On the forward housing and combustion chamber housing are nipples
designed for feeding fire-extinguishing compound "3.5" into the engine
oil lines. The nipple on the forward housing feeds compound to the
line there and, the reduction gearing, and one on the combustion chamber.
feeds to that oil line.
The nipples have check valves to prevent the oil lines from opening
to the outside. These open at 0.5 - 0.2 kg/cm2 excess pressure of the
fire-extinguishing compound.
On the engine are the following units serving for engine operation
and providing necessary facilities for the aircraft:
1. Two STG-12 TM starter generators
2. One R-68 I propeller rpm regulator
3. One KTA-5 automatic fuel control unit
4. One high-pressure fuel pump - 348 I unit
5. One booster fuel pump - 707 I unit
6. Ten FR-20 fuel nozzles
7. Two igniters w/centrifugal nozzles and SPN-4 spark plugs..
8. Two KPN-4 starting coils
9. One starting fuel electric stop valve
10. One GM-2O main oil pump
11. One VO-20 centrifugal air separator
12. One MNP-20 auxiliary oil-feed pump
13. One MNO-20 oil pump for scavenging oil from the beartng
line in the combustion chaMber housing
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.1 One oil pump for the NI-2O torque meter-
15 Qhe centrifuge], vent ?
.16. One sensor ;or automati1c pro?eathering:.
Onei$0-12 AM icing signal'.
18 One VF-2S starter generator hSrdr,:.Cut,q);:,, ?
19. :Engine Parking brake with MIK-2 electrfo-ileCiatiSm
? ?
20., One., SGO-8U, a 76 'generator ? ???,., ?
? 21.: One' 435. .hyAraulic ? pump.
.22 ..? ' ?DTE-2 'engine, rpm pi ckoff
Et-1.4-ee unnUirabered pages document
containing ;1 ? -
.-Figur 14. 0.1egend
, (alOng?:drive center-line)
-Cutaway of AI-.-20 Engine .Showing,? Lubrication and Venting Schemes
? .two sheets.. ,/. ?
. ?
.
-1. Fluid feed tO,,centrifugal-vent ?
. ? .
2. Airyleadexhaust.mozzle
3. .0iI'leaetrom.fOrward housing to ai*separator
14. Air and feeditooil Yeservoir. .
'5.,!..:::011'feed',trom'reservoir to auxiliarYHOil-pUmp:
60,1ean.:,011 output:.from:airseparator.to.thil cooler ?
7 Oil flow rOrn qU)4,15.ary..oil,pump
8 Oil flow from oil tooler
,9.0i1_,;e0:ductfor,lubriCating.-redUction gearing parts
? 10,::::01.1:;eed:quct fOr.:engine?parta lubrication and oil supply'
? ?
II Oil feed
scavenging stage o; for,heating..ribs
. , .
0: .forwar.d
hou4i.r.ig
12., OjJJ.f?to HTA-5,. ?
13 Air bleed-off for.qabyrinth seal
14.? 0i14?eed to:turbine:And Compressor bearings:
,
, ' ?
- 11.
? 8-3-C-R-E-T ? '
)breign DiMICCM
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At the end of Ihe inner ring there are eleven ' Apertures; under'
? - the piny'T which 6e screwed, into the forward housing Thebe: serve
' to fasten the .1:nner-ring.,and.,locking :tab... 4.
. r t? .? ? ? r :"
The inner ring by check . .
the f orward:, housings
8 ylai:cf.1 is PreSeedAnto
The locking tah i? inade of 313' KhA steel, holds. the 'guide,' vanes and
fixes them a -Set .direction relative to the .comliressor. axia.
. .
14"
- 1
?
So libreiga Dias=
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