ACTIVITIES AT ZAVOD NO. 2, KUYBYSHEV

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP80-00810A000600030010-1
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 34
• Document Creation Date: December 22, 2016
• Document Release Date: May 27, 2010
• Sequence Number: 10
• Publication Date: May 11, 1953
• Content Type: REPORT

Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
. ti
CENTRAL INTELLIGENCE AGEN,>CY
INFORMATION REPORT
SECRET
SECURITY INFORMATION
COUNTRY USSR (Kuybyshev; Oblast)
SUBJECT Activities at Tavod No. 2,
Kuybyshev
PLACE ACQUIRED
This Document contains Information affecting the Na-
tional Defense of the United States, within the mean-
ing of Title 18, Sections 793 and 784, of the U.S. Code, as
amended. its transmission or revelation of its contenye
to or receipt by an unputhorieed person is prohibited
by law. The reproduction of this form is prohibited.
REPORT
DATE DISTR. 11 May 1953
NO. OF PAGES 3$`
.REQUIREMENT NO. RD
REFERENCES
THE SOURCE EVALUATIONS IN THIS REPORT ARE DEFINITIVE.
THE APPRAISAL Of CONTENT IS TENTATIVE.
(FOR KEY SEE REVERSE)
ARMY
NAVY
L
(Note: Washington Distribution Indicated By "X"; field Distribution By "#".)
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
Next 5 Page(s) In Document Denied
Iq
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
JMO 022 TURBINE (For overall Sketch See Diagram 1
Summarized Explanation to the Repirt about JUMO 022 Turbine.
The calculation and the design of the.turbine had been charged to a
group of engineers whose original working field had been exclusively
the. design of the Junkers propeller, and whose professional training
was more in flow technique and wing theory than in thermodynamic
turbine theory.
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
or T e ore the scheduled state test run. Eight to ten teat
power plants, previous to the state test run unit, had not achieved
a satisfactory result in respect to either the full performance of
the power plant and turbine or the specific fuel consumption.
The, " " f the third stage
resulted in a remarkable in-
crease or the rs me- o the shaft performance, to Na
^ 500o,,f'Sa
with a specific fuel consumption tr; A 300 g/P8Q.h. The pressure be-
fore the turbine increased only immateriallf, which can be explained
from the critical flows, over large parts of..the,..guide vane ring,blade
length (first and second stage).
With a new rotor blade setting of the third stage rotated the
022 power plant was released for the state test run.
Instead of now calculating and designing a blading without mistakes
after a new method, test guide vane rings with blades turning on
pins were ordered for all stages. At the same time a test arrange-
ment of the 14-stage compressor with adjustable guide blades was
drdered. That the power plant was improved by the ez erime tal
twisti of all c
The ezperillents
w1in ezo ages a gu o no rings I, II, and III with 4 - 22 and`
25 were a failure.)
25X1
25X1
25X1
2. The 022 Power Plant Turbine Bladingo
As ordered, the layout for power plant
a propeller performance
airflow
compressor ratio
and turbine was to be for,
No =:5000 PSe
4+ ? 30.0kg/sec.
- p1 1
specific fuel consumption b A 30ag/PSeh
.fort ground conditions (operation on the test stand)
SECRET
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
- 10 -
ho considerable participation of the thrust in the effective per-
formance,.complete removal of pressure in the turbine (eventually to
subpressure for increase of the turbine flow diffuser-intermittent
propulsive duct) (outlet velocity, flying velocity).
Discussed and used as basis for the design were:
Adiabatic compressor efficiency degree '~~~ ? 0.65
Combustion chamber .- combustion efficiency': dwgree
Combustion chamber - pressure decline A P& - 4% of the
compressor-pressure head.
Attempted at first was an adiabatic turbine efficiency 'degree of
.0.85.
Based on: previous research of constructed combustion chambers an in-
take velocity of the gasses of combustion to the turbine was arranged
with
C4 . 105 + 110 a/sec
With the above data, only starting-'and end-points of
for the energy conversion in the turbine were fixed.
2'D-TD
an adiabatic rate of 8 : s 110 cal/kg corresponded to the non
nti power at the above-sent.' oned data.) As auxiliary aid for .'th4
turbine design only a very inaccurate h-s existed at first. Liter
an..eipeoially calculated improved h-s diagram, was, ..available with
specific heats Cp and Ov after Justi, and R - 29.36 for ,A - 4?'
In ihe.turbine calculation and design a provisional lofting (contour)
of the turbine was first des gned,w on the above-described inlet
and outlet conditions, with 0.5+,0.61 The number of blades was
sleeted with consideration 'sufficient blade overlapping. (Ar-
rcingea nt of the exit-nossle tot with its influence on jet course
and mutual periodical oscillation). In selection of the blade thick-
nose in the exit, plane the process. in blade', fabrication was taken
into consideration. Therefore, the free axial channel flow cross-
sectio*s were fined along the wean channel tube:parallel to the
turb,ifle axis.(later even under consideration of the heat expansion).
Of. the ,relations
ample use. was made in fixing..
the blade angles.
This above adiabatic incline wars now drafted into-the h-s diagram,
under utilisation of the total-eaergy points T1T, Pi , TI . and
Pz, Tx, Tz and with the efficieney degree
RLd
? , ? ?.05 (see Diagram #2).
SSCRIT
A 11 i5p;
7111
25X1
25X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
from the turbine are calculated and
ad ?a %tics.? That is:
Tjk 2 m~
t" T -I K
P 4 LT4J
SECRET
The flow velocities 010 to and
superimposed on-the corresponding
T10-Tx-01.02
2 g
Cpm 410
? Tx ' I -
p l0 CT10
These are the static (true) conditions in the beginning and end of the.
expansion.
3. Description of the Graphical Calculation Method with the l-`$-Diagram
f r the Design of the 022 Turbines #1-.10;
_(.Be* Diagram
inning of the turbine expaneion,,and
at the be
g
v
The points P49p, T , 'Plot T f Ti(~ MA thi and of the turbine expansion, ,were connected' by
t.e exp nsi~5g;g, trope. This static total drop was arbitrarily divided
into three equal stage drops and the latter again, according to a
reaction degree H rOtor.-wheel/H stator wheel " 1, divided into two
equal part drops ! r"rotor wheel.hd stater wheel.
It was tacitly assumed that they ;.,.values, as being dependent
generally on the deflection angle and ' is ease of the rotor .b]rades--in.
a known way, as by Stadler--in addition on the head slot round flow
(also the second and third guide vane ring permit a flow around the
inner guide ring),. could be achieved in conformity with,.,,the presumed
turbine-efficiency degree L?and were also preserved). (Verbatim trans-
lation,unable to decipher,
In determining the blade-exit angle the following 'system was used for
all vane ringsi . .($de Diagram 3.;)
assuming:
Wax
]PAL W
? 100 200 300
X x g
Polytrepic expansion V0123-
assumed on the true
(ptatio) polytropio
state t
?4123" ~T
appertaining speed
from the diagram:
H " r .
VIF ',e s360~ H
. sin
s
kgm-3
Gal
(This angle has to be determ1.ned.)
But now the performance share for each stage oorreAponding to the expan-
sion has to be transmitted on the rotor wheel. ,(Pe Diagram #4,tl The
directions of the absolute exit velccities from the rotor wheel's were'
assumed to be parallel to the axis. Therefore, a further conditional
equation Wass
25X1
25X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
- 12 -
V, J1 coed
- n R Tl 1- lg) ~i-.
n-1 P
In this way it would have been possible. as sketched in Diagram #3,)
to interpolate on the pertinent W n sin & - G sind in a procedure
similar to the 12-method with various assumed W D, to the polytrope
transmitted WI A and from the polytrope read off V -- 1
2g t
During the .layout calculations every blade length was subdivided
four times along the blade length for determining the necessary twists
for the condition: d.a - 6onstant
wA donstant
This and the following circumstance made the calculations nearly un-
controllable,
The first teat-power plants were far below the rated performance of
p'e' 5000PS , with very high specific fuel oonsu-ption. For this reason
a new blad!ng design was laid out for better turbine efficiency degrees.
It was based on the very courageous assumption that the course of the
preselected polytrope (very sti;'ip and nearly falling in line with the
adiabatio) would have to follow the static change of condition, if the
bla4e'*ngles and nozzle cross sections had been rated correspondingly.
by this method the turbines could perform warnA rs+hwr
The definition of the flow loss faotorj'?v+7 ?.and the definition of the
l
ffi
nozz
e e
ciency degree
According to this relation Y" both increase with increasing
~ao -V'`oC - fri
flow velocity-- until the limiting value of critical flow-and approach
a limiting valuejP -f - i. (But an impulse or constant pressure
turbine with 47-01. does'not exist.)
It is a well-known fact that lesser losses appear by curvature flow, if
the gas expands at the same time in the flow channel and avoids de-
.taohment of the flow from the channel wall (front the curved wing).
The above-mentioned definition of the efficiency degree contradicts this
simple fact in the beginning,
The sketched h-s diagrams a(in Diagram #4 which generally.can be applied
to all six turbine blade nozzel channels, are designed for critical
flow at the temperature T5 with
Wky g x R T5
25X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
...
,SECRET,
with fricton more accurately , n-1 R T
kv V9 x-1 ( .) 5
for each of the three. h-s diagrams equal, equal "f{" from
also equal IV?0 supposed (equal x - f (T) , of course.)
IY1 I I111 n
Then also ~4 - V --~-+l ZLO 2:
are equal critical
p 4 ' ~ 7 (n
p~j
pressure ratios.
But is not a critical pressure ratio.
P5
.Since the gas flows critically also in point "T 5;.. p5; Q5
Then g 2
p5 m+l
should b4&'me a critical pressure ratio.
This can be achieved, thrlugh `"ritroduotion of a new definitionf,ft*ffia-
lobq degxge 00 ;L L-Z = 41- m-1
Awfi~
EGA + 0 '1.
4 e-l m+l
and through introduction of & ,,new polytropical,exponent. "m".
But one cannot imagine one and the same process of polytropio expansion
at the same.time .with . two different polytropio exponents and, effioienoy
and seoondlyt with an,arbitrai!ily created
This analysis: of the oritioal flow behavior and the analysis of "tie',
efficiency degrees at, the ourvation flow; point to the mistakes which,
have been made,-but still do not touch the.main.reason.
The. essential point is a misunderstanding and.theowrong use of the h-
diagram in go noral,, when with it static changes of conditions of a
gas are handled. The heat content of static gases:, is u and not he
he prooee of treatment of o,ondi:ticrn changes. of static gases,,i n
h-s diagrfi% is a mistakes the can only be, followed by means of a
p-v, or also a T-e diagrams a h-s diagram is made for adiabatic
expansion (and compression) for entering and leaving flowing gas.
(Each polytropio expansion between two intentional pressures of a
gas results in greater work as the adiabatic.) The total energy
.content in flowing gas consists of the 'sub-amounts.
degreesi First with
IT $02 - L (channel
loo and m.. . .
- v' + p.v + 02.x..
2g
These amounts cannot be kept separated in the h-s diagram.
of the total energy drop 4h,IotaI - & . +'~pv +':042 g can be gained
With ,a practical ?p, which gives evidence that only a part 08` 2g
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
14
in the expansion in the turbine blade channel (the data for $p,."~J 25X1
depending on the deviation angle, the channel form and the tip alo
are widely spread in technical
the blade channel
nozzle cross sea one and therewith the blade angles were determined.
The Turbine Bearings
The turbine bearing reached very high temperatures during operation,
whereby its rotating qualities and lifetime performance were unfavorably
influenced. Furthermore, considerable quantities of lubricating oil
infiltrated from the storeroom (p2'S p outside) into the cooling air
storage (Pk & P )e Since several bearings failed during test opera-
tions, and all i'earings-showed bad oartographics, changes 1iad to be
made. A new development for the bearing had to be found. (See Diagram
#6, Sketches 1 and 2,)
In the case of the turbine bearing con
structional errors and deficiencie pro uoe .e unsatisfactory bearing
performance: r
SECRET
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
15
Wrong return-furthering thread!
right hand thread
Improvement
left hand thread
Direction of_Rotation Direction of
Rotation
b, Second mistake: Every rapidly turning bearing has a strong
pumping effect.
his area
was open toward the outside only by a slot, through which oil should
not flow. Furthermore, no flow channel for the intended cooling air
stream existed (except the above-mentioned sealing slot).'
o. -Third mistakes The solidity of the shaft was very doubtful
because the omission of the fillet in the transition from the shaft
to the flange.
d. Fourth mistake: According to the above, the lubrication as
intended by the chiefs was very questionable in respect to improvement
of the cooling, and therewith improvement of the operational quality
and packing.
Sketch 1 (of Diagram #7) is significant because of large channels for
relief of the area back of the rollers and for passage of the cooling
air (from inside and from outside). This bearing was installed in
the turbines for the state test run.
Sketch 2 (of. Diagram ,7) is a further improved designs It
provided a splash ring constructed as a.rotor for amply supplying
cooling air and therewith safe lubrication supply for the bearing.
.Also the splash ring would insure that the lubricating oil, which'
was blown off the rollers, was directed',into the slot. The mounti
of the whole roller bearing in a closed casing should exclude dam&gr
ing the bearing at the assembly of the shaft* anOt cr
drawing (Diagram. '#8) is an additional 601612 of-the S&*iflgs
and their relation'with the turbine assembly.
D._ THE TER=, T. NQ ZLE
According to orders.-the relative share of thrust on the effective total
performance of the 022 power plant should be as small as possible
That meant the exit velocity of of the gas from the thrust nozzle
should, be as low as possible. The turbine gases should be reduced
to the energy level of the outside pressure of a motionless power'
plant on the test, ,stand. Under consideration of flight condition,
all - 200 m/s was selected.
Only a short diffuser for the thrust nozzle could be contemplated
because of the prescribed measurements of the inlet cross section
of the thrust nozzle.
Stan
25X1
25X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
However, the construction office delivered a contracted nozzle which
was even more converging than planned. It had not been taken into
consideration that the smallest flow cross section is still oonsid-
erably smaller than the axial free cross section. For this reason
this thrust nozzle was officially changed (as shown in Sketch 1 of
Diagram #9).
SECRET
After a short time in operation the inner covering broke at the. holes
for the support arms.(,Sketch 1).
Despite removal of the throttle points in the thrust nozzle, the brake
horsepower from the turbine remained far below the rated values in the
beginning.
0O2- HTIV I- I VOW-1
Pressures : " 4.5 4.8 5 5.3 5.5 6 log cm- 2
NAT NFL - Feb, - 3200 --**--'$- 5000 PSe
T ' . o achieve the highest possible performance on the shaft, the tempera-
ture TI was raised but this also made the exit temperature and the
thrust undersirably high..
As a countermeasure all later test runs'for approximately two years
were performed without. thrust nozzles. The gas escaped from the back
of the turbine.
Dr Cordes thought that a hood screwed to the last turbine wheel and
rotating with it could hot be realized as a substitute for a nozzle.
,Such a rotating body in the desired proportions could not be built
solidly enough ~~ - f v2 ' 25 Xg mm -2
g
Shortly before the 022 state test run deadline the thrust nozzle
(rather the diffuser) was designed (according to Sketch 2 in Dia ram.
.9). Here a version of the 012 thrust nozzle
was adopted because the originally selected 022 oonstri;d t on proved
not to be 'breakproof.
v0 M
SEO RET
in the relational
"(Mare at the positive diffuser
Fo, Po, To n .
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
-16-.
,~, cOH_ Ox AS
', .The ? various parts of the combustion chamber of the Jumo 022 ( s shown
in Diagram #10)' are as follows:
Part #i: 12 pieces, combustion chamber head: parabolic hollow object,
passing into a circular ring sector. Approximately three mm slot
between the single sectors. The 12 heads were welded to a closed
ring.
Part #2: 12 pieces; preheating chamber for combustion air; welded
within oombustion chamber head.
Part #3: 12. pieces; turbulence rose, welded within Part #24 A slide
fit was provided for the fuel nozzles.
Part #4:. 12 pieces; stiffening metal with "hee.rt shaped hole".
Combustion chambers without this stiffening metal piece tested pre-
.vtously always ripped between the heads. With the stiffening metal
pieces added; the flow-through the air slots was impaired. Addition
of the heart-shaped holes permitted air masses to'flow into the corn-
bust'ion Chambers.
Part #5: 1 piece: cylindric outer envelope
Pa*t #61 Approximately 140 pieces; outer secondary air mixers
Part #7s 1 piece; conic inner envelope
.Part #8s Approximately 140 pieces; inner secondary air mixers
Matsris ll for part 5, 6, 7 and 8 wereAIT with a shest mental, thickness
of 1 mm at first and later increased to 1.5 mm.
Part #9s 1 piece; outer stiffening ring
Part #10s 1 piece; inner stiffening ring
Part #11: 12 pieces; socket piece for glow plugs
All parts were carefully welded using the best equipment. The sheet
metal thickness was raised from one mm to 1.5 mm.by an annealing
operation in aluminum powder (filings ) by a diffusion process. In
this way parts touched by flame could be largely protected. However,
is the best but resistance also raised by this procedure?
Nevertheless, dents and breaks which reduced the life.of the chambers
always appeared on the combustion chambers.
According to the opinion of the experts these repeating breaks were
solely caused by the oscillations of the thin sheet metal body.
SECRET
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
17
_ deformation by bending moments conditioned 25X1
by the general layout of the combustion chamber largely contributed to
the dents and breaks of the metal. The hollow body, which was orig-
inally supported only in the planes X and Y ,(see Diagram #11) and
oantilevered between the planes Y and Z,.was very soft and subject to
vibration. During the development,the,turbulence rose was built in
for combustion reasons. The bore of this turbulence rose with the
pin of the fuel nozzle connection formed a third bearing in the
plane "Z" and a "straightening" of the combustion chamber head in
oonoentrio-conic axis.
If the hollow body were supported only in the planes X and Z, then the
forced moments M were avoided, but the general bending moment be
nnn.~? ff-P&Mi:.r 19Ain and the danger of vibration breaks increases.
A stator ring after the compressor r
would be very desirable for two reasons. One was the consideration
for a more oven flow. The second was for support of the bearing
cantilevered from the first turbine stator stage.
But all these considerations were above the "horizon" of the present
?psoialists. The first designs and construction forms of the oem
bustion chamber suffered due to the fact that the technical designers
had previously worked on construction of formers or were auxiliary
draftsmen nearly their whole lives.
The layout of the BMW-024 annular combustion chamber could have boon
a good guide.
25X1
^kstah ,(Diagram #11) shows the original construction form of the
annular oumbustion chamber consisting oft
Part #11 1 piece; cylindric metal casing, thickness of
with outer secondary air mixers.
Part #2a 1 piece p inner conic metal casing,
secondary air, mixers.
1 mm,,
? 1 am with inner
Part #31 12 pieces) parabolic combustion chamber head,;,.o.onioallY
arranged and penetrating each,other at "A" connected to "#l and
#2 at "B"" and "0" (coupled).. The overlapping edge "A" was welded
and gave a fairly good flow profile for the mixed air flowing.
SEORET
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
3EORET
near the heads. The intake nozzles into the heads were simply bent.
Staggered-arranged ram tubes "B" guided the combustion air into the
combustion area "R". The whole. roll sow body was supported by "X"'
at the outlet of the oI' amber in the turbine stator first stage and
by the screw of the glow plug at "Y". The bores "Z" were later
.installed for improvement of the combustion. This original con-
struction. was in no way satisfactory. The combustion efficiency.
was very bad,. After a short test run oz l.y an unrecognitably dented
and torn metal. body was left.
But the contours given. in this thoughtless unprofessional design
were also later binding for the now construction to achieve better
combustion and longer life Better combustion was achieved through
the addition of an. expansion nozzle in the combustion chamber
head (creation of a pre-heating chamber for the combustion air)
and by superimposing of a turbulence throttle - both taken.from. an
excellent description of single combustion chambers in British-
American power plants with 99.7% combustion efficiency.
Because of the conically arranged nozzles - their pins should sup-
port the combustion chamber on the heads - the combustion chambers
were still always dented and torn despite all sorts of stiffenings,
which in all probability
do not chic with the eel ua.. measure .
As a sample for an exemplary, solid construction in' regard to the
support of the combustion chamber, drawings and parts of the BMW-024
power plant were available. Acoordin..to this model the 022 combustion
chamber should have been laid out (,shown in Diagram
Part At 6 pieces; supporting profile arms between every second.cenbus-
tion chamber head.
Part B: 1 piece; inner support cone, welded at "0" with "A".
Part D: 1 piece rotating nose ring, welded on sup ort arms "A";
between the combustion chamber heads added to the (rotating) profile
ring "B".
Part P:' 6 pieces; oombust:fon chamber heads "F", mounted into the
profile ring "Br". The rear end of the hands welded into two concentric
circular strips ~ "P" and "H".
On these circular strips (R O" or "H") are:
Part Is 1. piece; outer Oasing with outer secondary air mixers.
Part K: 1 piece; inner ca:s1ng with inner secondary air mixers.
Part La 12 pieces; intake. nossslee, welded to the nose ring and shapes.
. The sketch shows, for the sake of completeness, the Weotor assembly
with the injection nossles and the so-called disks for mixing in the
BMW construction.
The whole construction is overloaded and heavy and cannot be recommended
because the radially located side walls of the ring sectors' warped
SB0P3 T
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
-19-
ends of the parabolic combustion chamber heads are parallel to the
support profiles "A".
The following construction form can be regarded as the best solution.
Fuel injection nozzles arranged with support pine parallel to the power
plant axis. This demands a slightly changed construction of the
turbine casing.
P. ; .i AXIAL OF,01 'R_ESSOR
The folloein parts are identified in~sketch of the axial.oompressor 25X1
(see Diagram 13);
Part 1a: 1 piece, compressor casing:
Divided in horizontal axis (parallel to axis) consisting of$
Part 1: 1 piece; outer casing metal, 1.5 mm thick
Part 2: 4 pieces; longitudinal flange
Part 3: 2 pieces; flange
Part 4: 13 pieces; -ring
Part 5: 13 pieces; stator ring
Part 2a: 13 pieces; stator ring, complete consisting of:
Part 7: 1 piece; outer stator ring
Part 8: 1 piece; inner stator ring Steel welded gas welding
Part 9: stator blades
Part 3a: 1 piece; compressor rotor, complete, consisting of:
Part 10: 14 pieces; wheel disk, new construction form without hollow
shaft and flange (see Diagram #1).
Part 11: various; light metal blades,., with dovetail foot strip.
Material: alloy, hammered in die, afterward worked over
and recently also finished in die (pressure die casting?).
.Single wheel disk, statically balanced:
Part 12: 13 pieces; plug adapter (structural element of the hollow
shaft with flanges), only in new construction form of
rotor ,(sae Diagram #,I).
Part 14: 1 piece; front flange shaft
Part 15: 1 piece; rear flange shaft
Part 16: 1 piece; labyrinth split gasket (GL+ - 1.5 kg/sec)
Complete compressor rotor statically and dynamically balanced
G COUNTER ROTATING.PROPELLER_MAIN GEARING
1. Constructed gears:
A sketch Diagram #1O shows essentially the construction of the
propeller reduction gear, scaled M - 1:5 in full power flying operation
with
SECRET
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET
20
nl = + 6004 min and N1 = 5000 PSc
.front prop n2 + 1000 min and N2 = 2500 PSg
rear prop n3 - 1000 min -1 and N3 = 2500 PSa
The drive-sun gear I is driven with nl from the front end of the com-
pressor shaft T~ver drive shaft 1. The planetary gear II, rotating with
Na .F 5660 min , drives
a. the wib 6 through its axis 5 and the shaft 2 with nl - + 1000
min and
b. the hollow shaft 3 by meshing with the inner toothed central
gear #III:.
Parts 7 and 8 on the secondary drive shafts carry the heavy control- .1
Table-pitch propeller hub bodies. The propeller control gears (geared
oil, motors with planetary gears) (see Diagram #15) are mounted within
the hub.
A geared oil pump regulated by the speed governor supplies the Servo
motors in the propeller control gears V through a piping system
Inside the hollow shafts. This way the number of revolutions of the
counter-rotating propellers is regulated to n2 = + 1000 and
n = 1000 min +-1 a
3
By the selection of the gear ratioeappropriate deviating numbers of
revolutions are;
A. front Lrol? .e11er: n2 - + 1000 and n2' - 900 min
rear propeller: n3" ,. 860; n3 1140 min-1
b. rear per lr: n =1100; n3 - 900 mind
front propeller; m2 = 928; n'x = 1072 mind
If the feathering is applied completely to the front propeller, n2 - 0,
the rear propeller with n 1 ? 6000 min-1, would build up to n3 - 2400
min -l. If the feathering is applied completely to the rear propeller
u3 0 then at nl 6000 min-1, the front propeller would build to
n = 1720 minl. This takes place providing the performance equilib,-
riium between turbine and propeller perfromanos permits the. number of
'revolutions.
The fluctuations from a synchronized run which were frequently observed
in test operations on the test stand were considered as a serious
malfunction,
A turning moment lid - 596 mkg was transmitted to the power plant
from the gear box 1hich could be used to, measure the performance.
The operation of the gearing was safe as far as solidity and life were
concerned. Additional oil cooling provided by bores "0" was required
at the central sun gear I, because of frictional heating.
2 .Designs;
SECRET
the design of a gear for the
25X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
,.SECRET
21 -
012 propeller power plant. .(The construction of such a gearing is 25X1
shown in Diagram 16.)
The transmissions
02
ni/n2 - +6000 4+6:l and
nl/n3 - +6000 ;-- 6:1
-1000
and the performance distribution are 'here compulsory. Everything.
else concerning such a gearing is mentioned in Diagram #16.
DIAGRAM
DIAGRAM
DIAGRAM
DIAGRAM
DIAGRAM
DIAGRAM (6)
DIAGRAM
DIAGRAM
Y<
DIAGRAM 9)
DIAGRAM 10
DIAGRAM 11
DIAGRAM (12)
D;AGRAM 13
DIAGRAM 14
DIAGRAM 15
DIAGRAM 16
Turboprop Power Plant
H S Diagrams
Determination of Blade Exit Angles
H - S Diagrams for 3 Turbine Stages
Shoot #1 - Turbine Flow Channel
Sheet #2 - Turbine Flow Channel showing Blade Positions
along the mean Flow
Turbine Bearing Installations as Designed by Turbine
Department
New Designs for Turbine Bearing Installations
Turbine Arrangement (Bearings and their relation to
Turbine Assy)
Jumo 022 Thrust Nozzle
Annular Combustion Chamber
Combustion Chamber and Turbine Casing Development
(First Form
Combustion hambsr and Turbine Casing Development
(Not Constructed)
Axial Compressor Design
Counter Rotating Propeller Main Gear (sumo 022)
Propeller Control Gears
Propeller Gearing for Jumo 012
SECRET
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 `'5X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET.--$LrcU fcT V d FO A Tl0
o1,4'dx14M (i
$ECRET.t U /Ty INFOR ATION
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1
StCRe1-SECURITY W'FORMATI OW
--SECRET
14-S OIAORl~1~l1~
ADetermind by standard calc~lctiora -
procedures with the once-ted values
o r d 7 for everg slr-gta "stcige
rTata.I Energy nvertinq 6a anee
'
'Tad /1
-Curve of the Static Course of the
Pressure bg Or to . it was assumed,.
that the "tru.e" gas conditions wowed..
40ttow +his Potytrope; accord.in9l
-the siv le "Wet were meucuwed..
Did ram of the 'D*L ser
1 1 r st :IJ o~,z~1e.
for entargemeNt of 44 a>1
I Turbine fro oM dejre&ce 0+
1
W 1 ~; 16 -+he - EK%t tosses got
. accornpI %ie4. 1i +6e N cN Aaveto
mevt b Lkso:
p
-Median eFFicieKcq degree, aster the
def~nrtloh-of _Dr, -Cor.&es
at jL~
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1-X1
5 CRF-1 SCCUR1TY.IMPORMAT1OW
Q'~TCRMINA?tOt . of 'g1. a ~sct-r~ p,~1Gt.~.S
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1
 95X1
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
SECRET- S.ECL)P tTY tN3RORMATtvr t
aI~ C
eowwev. of i& eiV1,4446V c/cv-see, aocter-
o, relx6p' n Ay Pe. Cornet ~l > co, ~` :.. ,L t z
klrah~ y
e ie./6; - User 4r more Mom ir"YAe,-r 1-4 814do des
--Cwe ?
A&I WA tot;
A ,a
? 'Dt k'Gt .AA.A, -for T" 2S,r. ?TU t.3 t t, S S-t NG M S.
D t A-G $.A M (q-)
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1 25X1
5ECRAT-S'EcUI@my 4NPAP-MA-TtoNJ
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-0081 OA000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1
W:12C-T '- SeC URITY-. I.MF69MATto,1.
_ %Kea wr FLOW C AWQ L. S .A,Ovi i ..t31.AIDIL.. .
POSlT1oOS ALo 3 T14Ec MMACN
~i ACS2ihM C5~ Sheet *'~ ~
-22.7-
Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1
 Sanitized Copy Approved for Release 2010/05/27: CIA-RDP80-00810A000600030010-1 25X1
S.ECRLT-cLcURITY iNFO(.MATLONJ
"28-
TUR'3tNE bEARt1 G IN%-cALLATIO~JS
Shows Me 7Z ,-4,ne ,8earihy as des9ne.~ by
%e jur3J de/Caar~f,,~H.t,
DIAGMAM (6)
Fa4/Es r
?A/? PesfKte. re%asQ ih k o
,8edr4 q . A/a p.~ ss- t r rc .