SCIENTIFIC ABSTRACT MOLCHANOV, YE. I. - MOLCHANOV, YU. S.

• Document Type: CREST
• Collection: Scientific Abstracts
• Document Number (FOIA) /ESDN (CREST): CIA-RDP86-00513R001135010013-6
• Release Decision: RIF
• Original Classification: S
• Document Page Count: 100
• Document Creation Date: November 2, 2016
• Sequence Number: 13
• Publication Date: December 31, 1967
• Content Type: SCIENTIFIC ABSTRACT

K()L(;ffAuOV,, re. I.,, Cand Tech Sci -- (diss) feStudy of
wu@,*
tgAftw cc riditions of tat onary 5 tarbine iAtataLlatIons.tv
mos 1958, 13 PP. (Min of Power USSR.. All-Union
k
Order of Labor Red Oanne Heat @T s Inst im
F.E. Dzepzhinskiy) 120 couies (KL, 21-58, 90)
- 33 -

KOLGIEAWT, To. 1.
stigs ting starting conditions of stationary gag-turbine =its.
katharcs abstract of the dissertation for tfte scientific degree of
a Candidato of TachnologF] lasledovarLie uslovii puoka atatsiona=ykh
gazoturbinnykh ustanovok. Avtoreforat dissertataii na soiskanie
achenoi, stepeni kandidata teklmicheakikh nauk. ffalmahuyi rukovodi-
telt - G.I.Mmvalov. Nock-ra. Tase.ordena Trudovogo.lraenogo Znameni
teplotakhn.nauchno-issl.iu-t im. Y.N.D7erzhinskogo, 1958. 12 p.
(KIRA 12:10)
((ks turbines)

S/123/60/000/022/012/013
AOO5/AOO1
61 012 /-2 0
Translation from: Referativnyy zhurnal, Mashinostroyeniye, 1960, No. 22, po 3488
# 1230
AUTHOR: Molchanov, Ye.l.
TITLE: The Problom of Substantiation of the Starting Conditions of Gas
Turbine Units
PERIODICAL: V sb.: Usoversh. konstruktsiy I ekspluat. turbin. ustanovok. Moscow-
Leningrad, dosenergoizdat, 1959, PP. 255-261
TM: A method is expounded of the substantiation of the startingcondi-
tions of gas turbine units according to which the starting instant is dethrmined
by the stresses arising in the turbine impeller. Calculations showed that the
thermal flux preheating the Impeller is directed along the radius and the problem
of determining the temperature drops can be reduced to the,one-dimensional problem.
A formula and graphs are presented for determining the temperature drop between
the center and the peripher7 of the Impeller, as well as a formula of the thermal
stresses In the latter. It Is noted that thermal stresses are smaller in an
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A005/AOOI
The Problem of Substantiation of the Starting Conditions of Gas Turbine Units
impeller produced from steel-of the perlite class. The st@esses in the impeller
of the gas turbine unit FT Zoo-i-5 (aT-6oo-1-5) during the starting process were
equal to 5,100-5,800 kg/cW which are near the rated stress, The calculation
method proposed can be recommended for determining, to a first approximation, the
stresses in turbine drum impellers at starting of jas turbine units.
Translatorts note: This is the full translation of the original Russian abstract.
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SOV/96-59-3-6/21
JXTHOR: Molchanov Ye.I.. Candidate of Technical Sciences
TITLE: Temperature Distribution in a Gas-Turbine Rotor
(0 raspredelenii temperatury v rotore gazovoy turbiny)
ITERIODICAL:Teploenergetika2 19599 Nr 31 pp 30-31 (USSR)
ABSTRACT: The 1500-kW gas turbine on which the measurements were
made is installed in the Heat and Electric Power Station
of the All-Union Themo-technical, Institute. The initial
gas temperature was 60000. A longitudinal cross-section
through the set is given in Fig.l. The five-stage gas
turbine drives an axial compressor and also a generator
through a reduction gear. The turbine rotor is of the
soli(I-forged drum type and has an internal bore 50 mm,
diameter. It is made of austenitic steel. The turbine
speed is 5,000 rpm. Temperature measurements were taken
in the bore of the rotor by means of chromel-alumel
ther-mo-couples installed at various points as illustrated
diagrammaticallZ 1 Measurements were made every
:a F@g.2.
five minutes whilst the rotor was being heated up;
thereafter longer time intervals were used. Temperature
changes at various parts of the rotor bore as a function
Card 1/2 of time are plotted in Fig-3 which also notes the inlet

SOV/96-59-3-6/21
Temperature Distributioa in a Gas-Turbiae Rotor
and outlet gas temperatures. A graph of the temperature
distribution in the rotor bore during steady thermal
conditions is gi-vea in Fig-4. Equilibrium is reached
some four hours after starting. The results show that
the rotor is quite strongly heated and that temperature
gradients appear., Thermal expansion of the rotor is
considerable but is less than the expansion of the
turbine casing. Axial expansion of the casing is in
fact about 12 mm whereas under steady conditions the
expansion of the rotor is about 4 ma. There are 4 figures.
ASSOCIATION: Vsesoyuza3ry Teplot-ekbnicheski-y Instuitut (All-Union
Thermo-Technical Institute)
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AUTROkc
TITLEt
5/17(Y/60/003/04/16/027
ROOT/BI02
MoIchanov, To. 1.
A Method of Approximate Calculation of Temperature Fields in Cooled
Disk Rotorwof Gas Turbines
PERIODICALt Inshinerno-fizicheskiy shurnal, 19060, Vol. 3, Ko. 4, RP-95-102
TEXT: A number of experiments with -cooled rotors with air conveyance to the
front of the disk were made in order to facilitate the calculations of temper-
ature gradients and of the maximum temperature in the disk rotors of gas
turbines. Basing on these experiments, a simple method of determining the
mentioned parameters with an accuracy sufficient for technical calcu)Lations@ was
worked out. The experiments were carried out 'at the tqdraulic integrator designed ty-
V. S. Luklyanov. The experimental conditions are mentioned. Altogether 228
problems were solved, 152 of them under nonsteady and 96 under stabilize&
thermal conditions. Evaluation of the results from calculatiou showed thst the
radial temperature gradients under nonsteady thermal conditions as well " the
teaperature in the various points of the disk under stabilized thermal
-onditions depend linearly on the temperature at the frqnt of the disk.
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W8T
A Method of Approximate Calculation of Temperature
Fields in Cooled Disk Rotors of Gas Turbines
S/ITO/60/003/04/16/02T
BOO'T/R1Q2
Formula (2) for calculating the radial maximum temperature gradient in the disk
in the case of quick starting is written down. The coefficients occurring in
this formula; are determined from the graphs given in Pigs, I and 2. The
diagrams were plotted for various values of the Biot number on the Ylindric
@surface , n a
Besides, these coefficients depend on, the simplex R/R a d o
the Biot number at the front face (cc frontR/A,). R denotes the outer radius of
the disk, H half the thickness of the disk inTestigated, ot: the coefficient of
heat exchange'on the cylindric disk surface and O'-front the coefficient of heat
exchange on, the disk front on the radius. X denotes the heat aonductivity
coefficient. Formula (3) for calculation of the maximum aid minimus temperature
in the cooled disk on stabilized thermal conditions ia'written down* In the
case of air conveyance to the front side the minimum temperature occurs in the
middle of the disk. The gradient in radial direction can be calculated when
maximum and minimum temperature are known. Comparison of the results obtained
from formulas (2) and (3) with the respective solutions of the problems by the
hydraulic integrator showed that these formulas are quite'useful for technical
calculations. Maximum divergence is about 51C,. Finally, formula (4) for the
calculation of the distribution of the temperature gradient along the radius is
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802aT
i Method of Lpproximate Calculation of Temperature 5/170V60/003/04/16/027
Fields in Cooled Disk Rotors of Gas Turbines BOOT/ @,102
written down. Hosting of the cooling air and coaling air conaumption (on the
condition that the cooling air is conveyed to the center of the disk) can be
estimated when the temperature distribution along the radius is known. The power a
of the relative radius 9 - r/rL (r denotes the variable radius) occurring in
formula Whas.a. considerable influence on the distribution of the tensions
and their magnitude. Fig- 4 shows a graph for the determination of n for the
case in which formula (4) is used in the calculation of the thermal tensions
in the disk on non-stabilized and steady thermal conditions. There are
4 figures.
ASSOCIATIONt Vassoyuznyy toplotakhnicheakiy institut, 9, Moskva (All-Union
Rest Engineering rustitute City of Moscow
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AUTHORt -Molchanov, Ye.l., Candidate of Technical Sciences
TITLEt An Investigation of Temperature Distribution in a
Cooled Gas-Turbine Rotor
PERIODICALtTeploenergetika. 0, Nr It, PP 53-56AUSSR)
AUSTRACTt This article gives the results of temperature
distribution calculations in the rotor of a gas turbine
with various methods of cooling. The calculations
referred to the rotor of a two-stage high-pressure gas
turbine type QT-700-4..?oThe rotor is an austenitic disc
fitted to the end o a pearlitic, steel shaft, as shown
diagrammatically in Fig 1. The disc was cooled by
applying air to its faces and also to the rim between
the first- and second-stage blades. The temperature
distributions were calculated an a hydraulic
Integrator by a procedure which has been described by
Molchanov in Teploenergetika, 1956, Nr I and elsewhere.
.The boundary conditions for which the calculations were
made are tabulated. The first;stage gas temperature was
6600C and the second-stage 616 C; other temperature
Card 1/4 conditions are stated. It was found that the heat-transfer

68840
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E194/E455
An Investigation. of Temperature Distribution in a Cooled Gas-
Turbine Rotor
coefficient from the faces of the disc is a function
of the radius, as will be seen from the graph in Fig 2.
The changes with time of the temperature difference
between the outside edge and the centre of the disc are
plotted in Fig 3. A histogram of maximum temperature
drops across the radius of the disc for various values
of the heat-transfer coefficient in the blading is given
in Fig 4. A similar diagram comparing the maximum
temperature drops across the radius of the disc with
various values of heat-transfer coefficients from the
disc faces is given in Fig 5. Changes in the maximum
temperature drop as a function of the method of cooling
and temperature of the cooling medium are plotted in
Fig 6. Isotherms of temperature distribution in the
gas turbine rotor under steady-state conditions, seen
In Fig 7, relate to three sets of boundary conditions,
which are given in the Table. These isotherms may be
used in thermal stress and strength calculations under
Card 2/4 various conditions. Thus a qualitative picture was

68840
s/o96/60/000/04/011/021
E194/E455
An Investigation of Temperature Distribution in a Cooled Gas-
Turbine Rotor
obtained of the temperature distributions with various
types of cooling, and the influence of boundary
conditions on the temperature d1stributlon and
temperature drops was determined. it was found that
changes in the heat-transfer coefficients from the
blading and from the disc faces have little effect
upon the maximum radial temperature-drop. It was also
found that, with the two-stage construction, the
application of cooling air to the disc rim between the
two stages combined with cooling of the disc faces
greatly reduced the radial temperature-drop, both during
heating-up and during steady-state running. If only the
disc faces are cooled, there is some reduction in the
maximum radial temperature-drop during heating-up but
a considerably greater drop during steady-state running.
It is evidently necessary when designing the cooling
systems to investigate the temperature distribution, to
Card 3/4 avoid dangerous stress c onditions. There are 7 figures,

68940
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E194/E455
An Investigation of Temperature Distribution in a Cooled Qas-
Turbine Rotor
I table and 4 Soviet references.
ASSOCIATION: Vsesoyuznyy teplotekhnicheakiy institut
(All-Union Thermo-Technical Institute)
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s/114/60/000/010/003/007
.2 E194/E494
AUTHOR: Molchanov, Ye.I., Candidate of Technical Sciences
TITLE: Calculation of Temperature Distribution and Stress in
the Rotor Bladdin of a Gas Turbine
7-10
PERIODICALt Energamashinostroyeniye, 1960, No.10, pp.19-21
TEXTs In addition to being subject to centrifugal and bending
forces, gas turbine blades are subject to thermal stresses;
to evaluate these it is necessary to calculate temperature fields
under various conditions. Calculations of this kind were made
using a hydraulic integrator designed by V.S.Luklyanov. The
calculations were based on the assumption that the blade is of
constant section and that the temperature and heat transfer
coefficients are constant both along the length of the blade and
across the section. The method of dividing up blades for the
examination is illustrated in Fig.l. For the study of temperature
distribution, the blade was divided up into seventeen areas, the
investigations corresponded to four temperature conditions
equivalent to rapid start, maximum cooling, ignition of combustion
chamber and extinction of combustion chamber at full loadwith
maximum temperatures of 600*C and minimum of 20*C. Fig.2 shows a
temperature time curve for the bottom part of the blade and the
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s/ii4/60/000/010/003/007
E194/S484
Calculation of Temperature Distribution and Stress in the Rotor
Blading of a Gas Turbine
fir-tree root. It is found that even under favourable
conditions there is a temperature drop in the blade proper only
immediately near the root and so the temperature distribution may
be considered as a plane problem. FigA shows temperature/time
curves at,various points in the blade section for two values of
heat-transfer coefficient. It will be seen that the value of the
heat-transfer coefficient has an important influence on the
temperature gradient across the blade section. Blade stresses are,
of course, caused by temperature drops and the process of
temperature drop formation is illustrated in Fig-5 which gives
graphs of the difference between the temperature at the inlet and
central parts of the blade section as functions of time. Blade
Isotherms at the instant of maximum temperature drop are plotted
in Fig.6. A procedure for calculating thermal stresses in gas /C
tftrbine blades has been described elsewhere and the procedure is
briefly recalled here. The method was used to calculate the
thermal stresses occurring in a blade section and the corresponding
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s/ii4/6o/ooo/olo/coVoW
E194/E484
Calculation of Temperature Distribution and Stress in the Rotor
Blading of a Gas Turbine
stress diagrams are plotted in Fig.7. It will be seen that
tensile stresses of 2000 kg/cm2 are set up on the convex inlet
face of the blade and 'at the discharge edge. These thermal
stresses are of a temporary nature and form a kind of shock!load.
Data published by the American General Electric Company hasishown
that thermal shook loads may be an important cause of blade
failure.' There are 7 figures and 4 references: 3 Soviet and
I English.
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MOLCHANOV, Ye.I.; ATENKOV, S.t tekhn. red.
[Using the hydraulic analogy-method for studying temperature
fields in gas turbine units; Conference on Heat and FAss
Transfer, Minsk,, January-23-27, 19611 Prizenenis metoda gid-
ravlicheskoi anitI gii dlia issledo,vaniia, temperaturuykIL'pGlei v
elewntakh gazavfIch turbin; soveabpbAnie po teplo- i massoob-
menu,, go Minakr 2,31-27 ianvaria IcI61 go Minsk, 1961. 17 p.
(KM 15:2)
(Ifydraul.ic madels) (Gas tarbines)

ROLCHANOV, Ye. I.
"Applicatioa of
lavestigatioas.
Elements."
theffy&raulic Analogy Methoi to
of Temperature Fields in Gas Turbine
Report submitted for the Conference oa Heat and Kass Transfer,
Minsk,. BSSR.. juze 1961.

h2oi5
S/262/@2/000/022/002/007
I C9 kAV9 E073/E435
AUTHOR: Molchanov, Ye.l.
TITLE: On the problem, of thermal fatigue
PERIODICAL: Referativnyy zhurnal. Otdellnyy vypusk. Silovyye
ustanovki, no.22, 1962, 21, abstract 42.22.i4o.
(In collection: Teplovyye napryazheniya v
elementakh turbomashin. No.l. Kiyev, AN UkrSSR, 1961,
156-159)
TEXT: A number of authors in the USSR and abroad carried out
therittal-fatigue experiments on specimens for the purpose of a
qualitative evaluation of the resistance-to-failure under the
effect of a cyclically fluctuating temper4ture, as well as
quantitative evaluation of stresses and strains. The author
mentions the work of Coffin, who obtained the clearest relatiah
between the number of cycles to faLlure and the magnitude of
plastic deformation. The investigations were made on hollow,
cylindrical specimens, held in rigid clamps. Periodic passage
of a current through the specimen produced in it tensile-
compressive stresses. The author made experiments on
cylindrical austenitic steel specimens 100 x 100 mm with an
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s/262/62/000/022/002/007
On the problem of thermal fatigue E073/r,'435
internal bore of 10 inm diameter. Eight specimens were tested
for three values of radial temperature gradients, which corresponded
to three levels of stresses and strains. The frequency was
1/360 cps. The test results are presented in the form of a
dependence of the number of cycles and deformations on the bore.
The magnitude of the deformation was calculated from formulae
which are valid for an infinite cylinder on the assumption that
the deformation of the material is elastic. The Poisson
coefficient was assumed at 0.5. Photographs are also included
of failures of specimens which showthat the cracks are generated
on the internal bore and have a typically fatigue character.
[Abstractor's note: Complete translation
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25665
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o26. o2la 4 E194/Eil-55
AUTHOR: Molchanov, Ye.l., Candidate of Technical Sciences
TITLEt Calculation of temperature distribution in gas
turbine discs cooled through erection holes in the
blade root joints
PERIODICAL% Teploenergetika, 1961, No.9, pp. 65-68
TEXT: This article describes an investigation of the
temperature distribution in a disc cooled by passing air through
erection holes in the blade root joints. A sketch of the disc is
shown in Fig.l. the motion of the cooling air being indicated by
arrows. At the disc face the flow of air divides, part moving
across the face and cooling it before passing through the blade
roots, and the remainder passing through the disc to cool the next
stage. The air that has passed through the blade root channels
also serves to cool the far face of the disc. Investigations of
temperature distribution in the disc during steady-state and
transient thermal conditions were made on a hydraulic integrators
using a procedure described by the present author in Teplo-
energetika No.1, 1956 (Ref.2). The blade and disc were made of
austenitic steel. The experimental conditions are described in
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some detail; 43 variants of boundary conditions were used, in
order to determine as fully as possible the temperature distribu
tion during steady-state thermal conditions. Certain transient
conditions were also studied. The greatest calculated temperature
rise of the cooling air was 67 OC, corresponding to high values of
heat transfer coefficient in the slots both to the blade proper
and to the face of the disc. Heating of the cooling air is most
affected by the heat transfer coefficient in the blade root slots
and the temperature of the mediuat on the far side of the disc.
From the results quoted it is found that the greatest radial
temperature-drop occurs in the blade, mostly in the root and in the
neighbouring part of the blade proper. When the cooling air passes
through the ducts in the blade root and is then used to cool the
far face of the disc, the axial temperature drop is small and does
not seriously affect the disc. A study of transient conditions
shows that the axial temperature drop is established very quickly
and does not alter much with time. To minimise this temperature
drop the temperature of the medium should as far as possible be
maintained the same on the two sides of the disc, and cooling air
should be passed through the ducts in the blade roots.
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E194/E155
This measure also greatly reduces the radial temperature-drop in
the disc under both steady-state and transient conditions. It is
found that at the instant when the radial temperature difference
in the disc is at a maximum, the temperature distribution in the
disc is very complicated and there are considerable temperature
gradients in the blade root. These radial temperature
differences can cause thermal stresses in the disc which are
superimposed on the stresses due to centrifugal force and so are
very undesirable. The instant at which the greatest radial
temperature-drop occurs depends on heat exchange in the ducts of
the root joints. Thus when cooling air is not passed through the
ducts, in the case considered the maximum temperature drop occurred
some 4 - 8 minutes after the start of heating. In this case, there
were considerable radial temperature-drops in both steady-state and
transient conditions. When the ducts were air cooled the maximum
temperature drop occurred after I - 1.5 minutes and was much
smaller than in the previous case. It is concluded that since
the most intensive extraction of heat passing from the blade
proper to the disc occurs in the upper ducts of the blade root
these ducts should be made as wide as possible. It is found that
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E194/E155
delivery of cooling air to only one face of the disc can lead to
considerable axial temperature-drop, causing buckling of the disc
even if the air is later passed through ducts in the blade roots.
There are 6 figures, I table and 2 Soviet references.
ASSOCIATION: Vsesoyuznyy teplotekhnicheskiy institut
(All-Union Heat Engineering institute)
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34340
S/170/62/005/003/OOAI/0)2
Im BIOS/B104
AUTHORS. Molchanov, Ye. I., Khenven, A. R.
41"
TITLEi Calculation of temperature fields in a vane of a gas turbint-
cooled through mounting apertures
PERIODICALs Inzhenerno-fizicheskiy zhurnal, v. 5, no. 5, 1962, 45 - 50
TEXTz The temperature field of a gas turbine vane cooled through holes
at its root was calculated on a hydraulic integrator (design from
V. S. Lukfyanov). The vane was one of 80 from the first stage of a two-
stage gas turbine working at a gas temperature of 7600C. The fields both
along and across the vane were calculated for steady as well as for non-
steady conditions at different heat transfer coefficients and cooling air
temperatures. The calculations were made for a section over which the
radial flow of heat need not be considered. It is stated that in ex-
perimental study the cooling air should have a temperature as low as
possible since then estimates of the coefficients of heat transfer in the
different parts of the vane will be the most accurate. There are 4 fig.,
ures, I table, and 3 Soviet references.
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X_%
S/ 1 7o/62/005,/CO. 3/co/c, 12
Calculation of temperature... BIOBIBI04
ASSOCIATIONt Vsesoyuznyy teplotekhnicheskiy institut imeni
F. E. Dzerzhinskogog g. Moskva (All-Union Institute of Heat
Engineering imeni F. E. Dzerzhinskiy, Moscow)
SUBMITTED: September 19, 1961
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S/032/62/028/002/019/037
13139/BI04
AUTHORS: Plotkin, Ye. P., and Molchanov, Ye. 1.
TITLE: Application of thermooolors to measure the temperature of
machine parts
PERIODICAL: Zavodskaya laboratoriya, v. 28, no. 2, 1962, 203 - 205
TEXT: The authors used thermocolors developed by the Kafedra tekhnologii
lakov i krasok Hoskovskogo, khimiko-tekhnologicheskogo instituta im.
Mendeleyeva (Department for the Technology of Varnishes and Colors of the
Moscow Institute of Chemical Technology imeni Mendeleyev) and Droduced
by the "Svobodnyy trud" Plant in Yaroslavl', to determine the temperatures
at which a change in color occurs after long-time heating. A plate 45
mm long, 0.5 mm thick and of varying width made of stainless steel and
providei with a thermocolor coating, was heated with about 100 a a-a.
The temperature field was checked by a thermocouple soldered to the
back of the plate. The boundary line of color change during long-time
heating shifted toward lower temperatures. For 30 min heating, the
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Application of thermocolors... B139/BIO4
teMDerature of color change of various colors is 50 - 1000C lower than that
for short-time heating. For a longer time of heating, the transition
temperature stabilizes and becomes practically constant when heating for
2 - 6 hra. Thermocolors age under the action of light. The majority
of thermocolors change at temperatures of uP to 400 C, two types change
their colors at 400 - 650*c, @ut at 650*c the color change from white
into pale violet is hardly noticeable. There are 2 figures and 1 Soviet
reference.
ASSOCIATION: Vsesoyuznyy teplotekhnicheskiy institut (All-Union Institute
of Heat Engineering)
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!JJ T HORS
TITLE:
14
/63/000/001/002/007
D262/D303
Candidate of Technical, Sciences,
and Plotkin, Ye.R., Engineer
Terxpera-ure and str@ss 'states of rotor rT -25-700..
WT-2.5-700) at startingrup and steady working condi-
t i o ns.
KRIODICAL: Energomashinostroyeni e, no. 1*, 19@63,-19-22
y
Ti=: Me article presents the results of an investigation
into the temperature fields and stresses in the rotor and blades of
the seven-stage air-cooled gas-turbine GT-25-700. The temperature
blade surfaces. under steady workingr
distribution on the rotor and
conditions,is calculated using the hydraulic integrator designed by
;*'V.S.'Luklyanov, and the 'thermal stress distributions on the working
blade surf-ace for various times of the load @ncrease (instantaneous,
2 min, 5 min) are evaluated and represented graphically. The air
;cooliigr, system is also analyzed. Conclusions.@ By increasing the load-
rise time thermal stresses can be lociered;considerably and 2ron. point
Gard.1/2

S/114/63/000/001/002/007
Temperature- and stress states D262/1)30a
of view,of,the rotor and bl-ade strength, this time should be 5 - 8
min. Ur t,-,pped past theiregenerator at 29000, is recon-mended for
this cooling turbine. Th4re are 7 figures and 3 tables.
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,!ACCESSION AT4010246 S13052163100010031018110192
@AUTHOR: Plotkin, Ye. R. (Moscow); Molchanov, Ye. 1. (Moscow)
TITLE: Experimental investigation of the temperature field and evaluation of the
S.tress in gas turbine blades operating at varying sp6eds
'.SOURCE: AN UkrSSR. Institut mekhaniki. Teplovy*ye,;napryazheniya v elementakh
;konstruktsiy; nauchnoye soveshchaniye. Ooklady*, no# 3, 1963, 181-19Z
TOPIC TAGS: turbine, gas turbine, turblne blade, turbine operation, turbine blade
temperature turbine blade stress
'ABSTRACr: Turbine blades were tested in a variable temperature fiel*d when starting:
@aad at varying gas turbine spe6dsi using thermocouples for measurement. Four
;stages of operation were studied: 1. Starting of the cola engine and accelera-
Ition to idling speed. 2. Increase of the load (after 7 min) for 3.min. 3. De- i
--crease of the load (14 min after starting) to idling speed in 2 min. 4. Switching'
loff the combustion chamber while the turbine Is running at Idling speed (20 Mtn 1
@after starting). Besides, the combustion chamber was switched off while running
under load. Results are shown in graphs. Analysis shows that starting or changlng@
@the load after five minutes or more does not lead to accidents, even with large
blades@, ;Orig. art..has: 9 figures.
Card

7
,-1: .2 " t
, I - .--l

ACCESS S/3052/63/000100*193/0200
iw NR: AT4010247
AUTHOR: Plotkin , Ye. R. (Moscow); Molchanov, Ye. I. (Moscow)
TITLE: Thermal stresses in a turbine blade with fluctuations in gas temperature
SOURCE: AN UkrSSR. Institut mekhaniki. Teplovy*ye napryazhenLya v elementakh
konstruktsLy; nauchnoye soveshchaniye. Dokladyk, no. 3, 1963,'193-ZOO
TOPIC TAGS: thermal stress, turbine, turbine blade, gas turbine, turbine gas
temperature, thermodyqamics
'ABSTRACT: During the operation of gas turbines, conditions of periodically
varying gas temperature are frequently encountered. Such conditions may be
caused by instability of combustion chamber work or may arise at turbine load
changes. Gas temperature oscillations with a frequency of 1.5 - 3.0 to 60
cycles/sec. and amplitudes in excess of 207. of the mean gas temperature can
be provoked by instabilities, while load changes are accompanied by lower
frequencies with a period of several seconds and even minutes and amplitudes
up to several times the difference between initial and final temperature values*
Gas temperature oscillations cause corresponding temperature oscillations La
turbine rotating and stationary (guide vaaes) blades, particularly along the
C,,,d 1/7

ACCESSION NR: A14010247
thin edges. As a result of non-uniform heating of the blades, temperature
gradients arise and, consequently, thermal stresses appear. @Tt is of great
interest to establish the influence of gas temperature oscillations on the
strength of blades working at high temperature and stress levels. A method
based on simplifying assumptions allows the investigation of transient tem-
perature distributions in order to establish the influence of various factors
such as blade profile, heat exchange conditions, physical properties of blade
-material, and the period and amplitude of gas temperature oscillations. The
i main simplifying assumption is that the basic heat flow occurs in a direction
I normal to the blade surface, but the heat flow al@@ 'skeLetline is small and
6an be neglected. Such an assumption is equivaleat to a separate consideration
of blade profile sections as plates of corresponding thickness S - Zk, as
shown La Fig. I of the Enclosure. In the differential squatioa used to express
the heat exchange, a harmonic law is assumed for the gas temperature change@.:.
It is further assumed chat ihe film coefficient at, the specific heat C and--
i the specific gravity rof the blade material,'and the temperature distribution
auefficient, are conita'nt* values,, whera
tg . to
tr - tm
Card 2/7

ACCESSION NR: AT4010247
tg - gas temperature,
tm - moan plate temperatures
ta - plate surface temperature.
The solution implies that tm follows a simple harmonic oscillation with a
phase shift against the gas temperature ascillitt"an., The relative amplitude
of plate temperature ascillatiQns and the phase shift angle depend an the par-
ameter Kr T where T is the period of gas temperature oscillations. The
analysis shows that even at a relatively high f Uim coefficient a4 - IL16 WIM2
where W stands for Watts, gas temperature oscillations with a period of less
than 0.5 see have little Influence an the blade temperature. It is concluded
that gas. temperature oscillations of high and medium frequency (10cps and more)
behind the combustion chamber do not endanger the strength of gas turbine blades.'
@_-_Low frequency (1.5 to 3 cps) gas temperature oscillations behind the combustioa
chamber siinificnatly influence the temperature @f very thin edges (approximately
0.5 mm) only, where che oscillation amplitude can reach 15% of the gas temperew
ature oscillation amplitude. Transient processes arising from load changes
have a greater influence on the blade temperat@re distribution. The edge tem-
perature practically follows the gas temperature. However, increasing the edge
thic ss considerably reduces the relative amplitude of temperature oactllationa,
Card

ACCESSION VR: AT4010247
The mean temperature of the central, thicker portion of a blade section changes
little at gas temperature oscillations, at least.at periods up to 20 seconds.
Rhen approximate solutions obtained by the above-mentioned method were com-
pared with exact solutions produced with the aid'of a hydraulic integrator,
no significant discrepancies were found. An exact solution has been obtained
for the case of a working blade of a GT - 12 - 3 turbine at gas temperature
oscillations and at film coefficientc!@- 893 W/m2 -*G. Solutions have been
obtained for the transient blade temperature field at gas temperature oscil-
lation periods of 3. 12, 30, and 120 seconds. Thermal stresses have been com-
puted for the case of gas temperature oscillations form 300 to'500C at a per-
iod T - 120 see, corresponding to real conditions at idling turbine during
1 tuning for operation. For a aaa-uniformly heated bar, the expression for thermal
stress is;
+ X
:. .
A
card 4/7

ACCESSION NR: AT4010247
where E*and (3 are modulus of elasticity and coefficient of linear thermal ex-
pansion, respectively, and x and y - coordinates of cross-section points with
respect to the main thermaelastic bending axes. The results pf stress calcu-
lacions are shown in Fig. 2 of the Encldsure es occur at the
trailing edge reaching the value d?, - 1 111;3 HH"/cmim2u.m 0antrthas basis of the comm
putations, it was concluded that colsiderable temperature and thermal-stress
oscillations can arise in the blades of a working gas turbine as a result of
gas temperature ascill*tions.' and, consequently, the blade life can be subetaa-
tially decreased. orig. art. has: 6 figures and 7 formulas.
ASSOCUTION: Tnstitut mekhaniki akademii nauk UkrSSR (Institute of Mechanics,
Academy of Sciences, UkrSSR).
SUBMUM: 00 DATE ACQ: 17Jan64 ENCL: 02
SUB CODE: PH NO REP SOV: 008 a=: 000
caid 5/7

ACCESSrON NR: AT401024Z
ENCLOSURE: 01
Fig. I - Gas turbine blade profile dividedi
in strips to the profile for
approximate thermaL anaLysia
Card 617

ACCESSIOU HR: AT4010247
f-tr
300 11 r-
20 40 60 60 W. Tcm
ENCLOSURE: 02
Fig. 2 Gas Temperature and Turbine
Blade Dimensionless Radical
Thermil Stress 5r Ggcil-
lations vs. Time
9.81 -N
cm-r-
(N Newton)
Card 7 /71

Acassi(ra ra: APW37636 s1b0q61&t100010061002310032
R. (Candidate of tedbaical sciences); Molchanov, Ye. 1.
AUMM: Platkin, Ye.
(Candidate of teckmical sciences)
TITLE: Temperature field of a gas turbine bUd& under translezr6 'conditions
SWRCE: Teplocnergetilm., no. 6, 1964,, 28-32
TOPIC T=: turbine blade, turbine blade test,, turbine blade tr4mperature,, gas
tuxlbine
Irne principal factors affecting the ecluillbriun of the temperature
field under trausiee. conditions are presented from the standpoint of theory
and experiment. Calculatim error resulting *-am apprccdmating ass=pticns
was evaluated through acmparlson with exact solutions obtained by the mathod of
hydraulic analoGy. It was founct that the error in eatimtinm, the greatest tem-
perature difference occurrinG in the blade under transient conditions Is relative-
17f Gmall.,,_and that for real va-lues ce the coefficient of heat; transfer to the
200 V/62-
'ace and the coefficient of heat coaductivity cit the blade metal
dez; A-c4o w/m-deg) this error does nat exceea. 20-y$. (kt a Im rate ce heat

AccEssicu Na: A2037636
transfer from the gas to the blade and a high heat conductivity of the metal,
the error could be largQ The assumptions permit the temperature fieM of each
sepment of the blade cross-section to be calaulated as the field of an equivalent;
plate irith a thicImess 2h, corresponding to the thickness of the given seLment,
and with corresponding boundary conditions. By examining the change in mean. tea-
perature of the plate under transient conditions.. simple relations can be obtained
for various particular cases. For instanca, for an, instantaneous change in gas
t*
i temperature fran t. t(
9
and for a gradual change of te from to to t* for the time
9
e-kr
for 4":*,
and
Card

Acassicu za.- AP1037-636
@e-k
0 vs 2. - e-k(r. for r- t ic@- (2)
k
Conclusion: The degree of iafluence off the transient duration depends on the
i",-tcnaity of the heat exchange to the surface of the blade. An increase in this
duration reduces the maximum nonunifomity of the blade temperatureo Orig. art.
has: 5 fonna,,-@Ias and, 8 figures.
ASSCCIATIal: VAesqy=ny*y teplat;ekbuicheskiy i=tittxt (All-Unial Power Engineer-
ing Ins-titute)
sum 00 DAM ACQ: 221=6@ ENCL: 00
SUB CODE: WO ZU 90 W SCU: 005 003
Card 313

PLOTUNr Ye.R.; HDLCHANOV re I
Fl*tuatlons of temperature and thermel stresses inside a
turbine, blade vith pulsating gas temperature.' rhsh.-fiz,zhur,
6 no.2;25-30 F 163. IMA 16ti)
1. Vsesoyuzny-y-teplotekbnLcheskiy institut, imeni, F.E.
Dzerzhinskogo, Moskva.
(Thermo4ynamics) (Gas turbines)

HODGHANOV, Ye.I., kand.tekhn.nauk;, PLOTKIN, Ye.R., kand.tekhn.nauk
Tqpperature distribution'in the zone of the neck connection of the
cooled blade of a gas turbine. Teploenergetika 10 no.6:58-61 Jo
,63. (MM 26:7)
1. Vsesoyuznyy toplotekhnichask institut.
%as turbines)

PLMS V.V. ; MOLCHANOV, Ye.I.; PLOTKIN, Ye.R.
Heat processes during,the solidification of ingots folloving
electric slag refinirg, Izve vyst uch,-,be zav.; chern. met. 6
no.96347 163. (ML 16:11)
1. TSentraltnyy nauchno-issledovatellskiy institut tekhnologii i
mashinostroyeniya.

th
-00- th bl is-
IM d
r ega cu .e
--d- 'w'ag-.,d .-h Ull
te BIA @ " i 4

RMW @=F__
-112
IMP
s"i
A
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FR

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7@1

Owl,
MOM

i
I'dii,
. . . . . . . . . .

dA

4-.
'bo
tv

NCY f-C W R kq Ov.IYeF- . \4
PARMOT, L.P., MOLOUNOT, Te.T.
P@I`j;@ z
Iffect of condensation field of ultra high frequency wares of
barrier properties of live tissues. Klin.med.. Noskva na.4:
84-86 AP 150. (GIn 19:31
1. Of the Department of General Phygiotherapyaad Health Resort
Therapy (goad -- Prof, A.P.Parfenov) of the Naval Medical Aaadeuq,
Leningrad.

.. yo.jr . MARTS, Z.3.; PLTROVAt G.F.; GHIMAMU L.F.; TARASMO,
MOLORMOV p M
Sixtieth birthday of Professor Aleksandr Frokhofovi,!h 'Iarfenov.
Vop. kur., fizioter, i lech. fiz. kullt. 26 no.6:563-564 11-D 161.
(FAILTENOV, ALEKSANDR FROXHOROVIGH, Igo-,T.;.) @ V41A 15:1)

NOV 'Mirge VI lqm&d2Mvrich;* CHP V.S.r red.; ONOSHKOt
- 4 RYWEVI
N.G., @gchn. red.
(Sea baths] Morskie k-upaniia. Leningrad, Medgiz, 1963. 30 p.
(MIRA 16:7)
(UTHS, SEA.)

Al 0 L C Ili 'IV Ai 0 V) yu I q,
BASS, M.GI.. inshenerf, KARAGODIN, T.L., inzhener; KOLCHANOT,,Tu.A., inshener.
KALITSKIr, S.I., tathener; MAZANOT, T.Te.-7-Ift er; USHAM7, V.S.,
Inzhener.
Collector with driven in sheet-piled walls. Gor.khoz.Kosk. 31
no.9:38-0 S 157. (KIRA 10:0
(Koscow--Sewers, Concrete)

-KARAGODIX, T.L.,
City ponde ani water recervoire. Gar.khos.Konic. 34 no-3:29-32
mr l6o. (KIU 13: 8)
(Moxcow--Ponds)

?T.
-@=HAKOV, ru.A., inzh.; CISTALML , F.P.
Advanced stnxetmva far zmanicipal onginaering instaUations.
Gor.khoz.fbak. 36 no.6.-17-19 To f62. (MM 15: 8)
(Hoocow--HU21cipal engineering)

AUTE10R: Brovehanko, V. G., ard tiolchanov,.-Yu. D, 1120-2-19/37
TITLE: A low Noise level Pre-amplifier. (Predusilitell s Maly--,
Urovnem, shi'MOV0
IIERIODICA.L: Pribory i Ifeklmika Foksperimenta, 1957, No.2,
pp. 67 - 70 (USSR).
ABSTRA.GT: A low noise pre-amplifier built for use with ionisation
chambers ard with proportional counters is described
(Refs. 1 and 2). The first stage of the amplifier is a
"casoade" using two grounded cathode 6XITT in parallel
connection and a grounded grid parallel connected dvable
triode GH15Tr. The noise level of the pie-amplifier
is determined mainly by the anode current fluctuations in
the input stage and is 214V for a pass band 50kc/s to 1-111c/s,
input capacity of about llpF and V L Of 75V. The pre-
amplifier gain is 140 with the paAs band 5MC/s to 600cps.
The further two stages of the pre-amplifier consist of a
pentode connected 6XITr and of a double tribde 61J15TT;
a heavy current feed back is applied. The anode supply
is stabilised, DC is used for the heater chain; the total
gain of the last three stages is 1?0 with feed back and
about 4000 without feed back. The whole arrangement is
Card 1/2 very stable, has a very good linearity and bas been giving

A Low Noise Level Pre-amplifier.
very good service in high precision
tion for the last three years. The
pre-amplifier is given. There are
is Slavic.
SUBMITTED: August, 21, 1956.
AVA3:jABLjij: Library of Congress.
Card 2/2
120-2-19/37
physical insturitim--ata-
circuit diagram of the
2 references, 1 of which

MCLCEkNov, @/...D. and BROVCHENKOI, V. G.
"Time Analyzer for Fast Pulse Series"
report submitted for the IAEA conf.,on Nuclear Electronics, Belgrade, Yugoslavia
J-5 --20 wy 1.961

S/12o/61/000/006/013/041
EO 3 5 IF, 4 14
AUTHORS: Brovchenko, V.G.,_.@olchanov, TuD.
TITLE: A time selector for the analysis of a train of pulses
PERIODICAL: Pribory i tekhnika eksperimenta, no.6, 1961, 74-77
TEXT-@ The selector was designed for the measurement of the time
distribution of pulses in series of pulses, Its parameters are
as followss minimum channel width 251LSec; gap between channels
-0 2.5 ji sec,@ resolving time. -3 x 10-8 11 sec@ Fig.1 and 2 show
a block diagram of the selector together with the corresponding
voltage waveforms. The time distribution is measured'with the
aid of a differentiating capacitor storage system which is
periodically discharged by pulses from the channel generator.
The time between two dtscharges is equal to the width of the
selector channel, The change in the potential acro-ss the
capacitance in the time between two discharges is proportional to
the number of pulses entering the device in this time. The curve
connecting the maxima of the latter potential represents the
desired distribution and-is photographed from the oscilloscope-
screen. The statistical accuracy of the measured distribution
Curve. 2- determined by the number of pulses recorded in the:
Card 14

S/120/61/000/006/013/041
A time selector E035/E414
selector channel. i.e. the rate of input pulses, the width of the
channels and the speed of recording the pulses. The main
advantage of the selector is the high speed of signal recording..,
and the simple circuitry employed, Detailed circuits are P
reproduced, There are 5 figures and 2 references,, I Soviet-bloc
and I non-Soviet-bloc. The reference to an English language
publication reads as follows? Ref.1% F.J.M.Farley, Rev. Scient,
Instrum., v.29, 1958, 595@
ASSOCIATION; Institut atomnoy energii AN SSSR
(Institute of Atomic Energy AS USSR)
SUBMITTED. April 25, 1961
Card 242

77
SOURM-ODDI&I-UR/0120[661000/005/0037/0035
'-AUTHORt Voratnikov, F. Ye.; Zubov, Yu# G.; jt Udod, A. A.;
Institute of Atomic ZnergyGKAZj Moscow (Institut atomnoy energii GW)
TITLE: A nanosecond-pulse ion source
ftibory L tekhrdka eksperimenta, no. 5. 1966, 37-39
Tb?IC,.TAGS: ion source, particle acceleration, ion accelecator A1tjO&SVO4'A,/0
_Rag.`is@e -,cA. e areo 3 r-4 r@&,_ 6.'C4U Q -A roe_
W%UCT:,..':Test results of a pulse ion source for an electrostacie accelerator are
'Me testing. apparatus was constructed on the basis of P. Ye. Vorotaikov
(gee Fig. I). Using a relatively low-power high-fr--juency'source
60 @aj.. and applying phase ion focusing, a very economical nurce of ion, current
Pula a.Of
....4pproximately 2 usec duration, a pulse current of ",1.5 ma, and a repeti-
I -tion ratvof approximately 4 Mc can be obtained. The ion energ,- spread was found to
coustitilt&-MO ev, and the Lou current utilization factor was a! -Ut 251. . The author
thank V'.. G. Bravaheakd4a helped in developing the measuring prc edure. Orig. art.
hast: 5 figures and Z formulas,
Card Itz UDC; 621*394.6Z

-an source
Fig. 1. Schenatic diagram of the 1,1se i
I - High-frequemmy Lou source; 2 - -.2cussing system;
3 - bunching electrode; 4- acceler..ting tube coa-
sisting of 16 conical electrodes; 5 - voltage divider;
6.-,uasuatic separator*,T Lou co2 actor.
SUB CODE: ZO/ S'UBKDATE*.*. 14act65f ORIG REFt
card 212
OCV2f (YM an 3011

ACC INR& AP6022011 SOURCE CODE: URIGIZGA6[0001003/01371@@1_3al
AUTHOR. Brovchenko, V. G.; Kolchanov. Yu, D.
ORG: Atomic Energy Institute, GKA3, Moscow (Institut atomnoy energii GXAE)
TITLE: A low noise preamplifier with a short signal rise time
SOURCE: Pribory i tekhnika eksperimenta, no.. 3, 1966, 137-138
TOPIC TAGS: preamplifier, electronic circuit, spectroscopy
ABSTRACT: A fast, low-noise stable preamplifier circuit is presented which is in-
tended for use in the spectroscopy of intensive, low-energy charged-particle fluxes
and for counting the number of rare events in the background of weak but often inter-
fering signals. The preamplifier consists of two sections with negative feedbacks.
The first section is in the form of a charge amplifier circuit. The first section
has a transmission coefficient of 1/5 pf, and the second section has a gain of 7.
A dynamic capacitance of 900 pf is at the input of the preamplifier. The signal rise
time at the output of the preamplifier depends on the capacitance of the detector at
its input. The intrinsic rise time of the preamplifier is equal to 15 nsec at a
signal amplitude level of 0.1 to 0.9, and the root-wean-square value of noise is 11
keV. Orig. art. has: 2 figures.
SUB CODE: 1 09/ SUBM DATE: 12Apr65/ ORIG REF: 001

XOCHG, V.Se, profe, doktor tekhn. nauk; ORMOVSKIT, T.I.. insh.; KOWWOTj
Yu.Yl,, insh.; PLUSHGEMO, Te.A., inzh,
-_WmPOOWW-
Keating open-heamth furnaces of 500 ton capacity with hot cokagag.
IBlul, TUXIM U0,1:11-15 958, (XMI 110)
(Open hearth furnaces)

mo c ka n ov @% I P, 130-58-2-6/21
AUTHORS: Kocho, V.S., Doctor of Technical Sciences. Professor,
"olchanov Yu. D and Pioshchenko. Ye.A.
Grankovskiy, V.I., L -_ - *
TITIE: Open-hearth Furnace Operation on High-calorific Value Low-
ressure Gas (Rabota martenovskikh pechey na -,rysokokalor-
om goryachem gaze nizkogo davleniya)
M
PERIODICAL: Nr 2j pp 9 - 12 (USSR).
Metr"lurg, 1958,
ABSTRACT: Blast-furnace gas is normally added to coke-oven gas
for firing opea-hearth furnaces to improve flame quality. The
low calgrificin f blast-furnace gas however lowers the
theoretical f luteoperature and an inv4stigatio@L has been
carried out by the imeni Voroshilova (imeni Voroshilov)
metallurgical works together with the Kiyevskiy politekhnicheskiy
institut (Kiev Polytechnical Institute) of furnace firing
without the addition. The authors mention this work in which
pure coke-oven gas was used with the addition of turbine air
into the side of the gas port and describe the adoption of
practice with reduced (halved) quantities of blast-furnace gas
which followed the comTA-
@ation of the first part of the work. On
250 and 500-ton furnac9s, the blast-furnace gas consumptions
were 3 000 and 4 500 M--'/hour, respectively, the coke-oven gas
consumptions remaining
., unchanged and the specific fuel
consumption being equivalent to the decrease in blast-furnace
Cardl/3

130-58-2-6/21
Open-hearth Furnace Operation on High-calorific Value Low-pressure
Gas
gas consumption. By increasing the poEtcross-sections, an
equally high temperature (about 1 350 C) was obtained for
gas and air checkers. The slag pockets filled less rapidly,
a higher furnace temperature and increased heat flows were
obtained with the new practice: measurements with VNIIT-designed
probes on a 500-ton furnace are shown graphically. Three
experimental heats were carried out on a 500-ton furnace without
blast-furnace gas and the averages of the main operating results
for this and ordina-Y. O-Deration are tabulated (Table 1): the
authors discuss these briefly and point out that there seems
to be an optimal gas p-re-heat tem-perature. They consider the
functioning of the gas checkers with pure coke-oven gas. A
failure of -@he lining of the gas ports on a 500-ton furnace led
to the combustion products losing enough heat to prevent over-
heating of the gas checkers and the furnace was worked on -.oke-
oven Gas continuously for 1 1/2 months. The operating results
show (Table 2) mean(boreases of 0.7 hours and 21.8 kg/ton for
tap-to-tap time and consumption of standard fuel, respectively.
The authors recommend the coke-oveng@s firing of furnaces
without blast-furnace gas, the cross-sectional area of the gas
Card2@3rts being reduced to reduce the flow of combustion Droducts

130-58-2-0/21
Open-hearth Furnace Operation on High-calorific Value Low-pressure
Gas
by 20 - 305% and high-pressure air being supplied to the sides
of the &Ls Dorts; blast-furnace gas should still be supplied
during reversals.
There are 1 figure and 2 tables
AVAILABIR: Library of Congress
Card 3/3 1. Open heae,.h furnaces-Operation 2. Coal gas-Applications

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M3001c"s 41441. 1111. we 9. pr 796-402 (u*=1
AISTPACTS P904ADIALtAem at tArAns open hearth Cura%soa rAeft a low
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4*41n As V*99moaded. There ^vs 6 fixers". a tables
am 10 referammes, a or WbIgh AV* Soviet, FAA 2 NAS3610h.
Cart 31/3

. KOCHO, T.S., doktor tekhn,.nauk; MIANIKOVSKIY, V41., kand.tekhn.nauk;
NAYDEK, V.L., inzh.; MOLCHANOV, Yu.D., in*i; PIORO, Ch.K., inzft.
Comparatiis analysis of thermal processes in 500-ton open-hearth
furnaces in two metallurgical plants. Stalt 22 no.1:23-27 J& 162.
(MIU 14:12)
(open-hearth furnaces)
(Heat-Transmission)

WON T. S.r doktw tekhn. nauk; GRM07S&U, T. I., kand. tekhn.
nauky XMIK.. T. L.v insh.- ";rl insh.;
KUDULVAn, 1. 1.2 inzh.
Neamiring the flow of combustion products in open-hearth
furnaces. Ket. i gornorud. pron. iw.1:57-62 4-T-163.
(MM 164)
1, Klyevskiy politekbnicheskLy institut (for Kocho, GrankovBkiy-,
lraydek). 2 Cherepo"takir vetallurgicheskiy zavod (for Nolebanov,
Kudryavaya5.
(Gas flow) (Openr-heaxth furnaces)

L 362C
ACC NRt
AP6022007
SOME CODS:
0120/66/000/00310121/01?-5
AUTH03: Brovchenkoj_v. G.F Molchaaov, Yu. D.; Stroganov, Ye. A.
OIRG-. Institute of Atomic Energy, GM, Mosecir (Institut atomnay energii GM)
TITLE: Measuring current im ulses magnetic belts
p r
1z
SOURCE: Pribory i tekhaika, eksperimenta, noo 3P 1966t 121-125
T
TOPIC TAGS; electric measurement, electric pulse measurement, electric measuring
instrument
ABSMCT: Two "magnetic-beltO circuits are examined: (1) With an integrating belt
w-d (2) With a differentiating belt and subsequent signal integration. The (Imagnetic-
belt(' is actual3,T a type of current transformer that measures not only the. value but
also the shape of acurrent, impulse by providing the output signal proportional
to the eaf inte0al.- Formulas for sensitivities of both the circuits are set up;
when the flat portion of a square signal is important, circuit.-2 has the advantage
because of its higher sensitivity threshold; with considerable external noise, both
circuits are equal. Formulas wore verified by some e eriments carried out with a
rectangular-cross-section (r = 1-35 cm, S = 0.325 A ferrite torus ring having
suitable windIngs."In conclusion, the authors wish to thank G'. A. Otroshchanko for
a useful disewsion and help in calculations.0 Crig. art. his: 3 figures and _
24 formulas. [031
6
SUB CODE: 09 / SMI DAT39 12APr65 / CHIG RM' 009 / OM RE?:* 003/ ATD PRESSI-4_�'@'f

MGLGHANOV, Yuriy Leanidovich; MANUKHIVI, V.L.,, nauchnyy red.;
jP re GURDZHIY37kt A.K.j, tekhn. red*
(Trade is the way to peace and.friendahip] Torgovlia - WV k
miru i druzhbe. Leningrad,. Ob-vo po rasprostranonlia polit. i
nauchn. znamii RSFSR, 1961. 58 P. NIU 15:3)
(Russia-Com rce)

IMOLCHANOV, Yu. H.
Holchanov., Tu. H. - "The influence of various temperatures of t@'-Ie te,=ering zedium or,
the machanical Properties of metals", 5bornik nauch. statqy 5tudent:m (Rost. D/D.
.in-t inzhenerov zh.-d. transporta, Issue 181, Rostov na Donu, 1949, p. 23-27.
SO: U-4110, 17 July 53, (Letopis 'Zhurnal Inykh Statey, Uo. 19, 1949).

.-ACCESSION NR: AT4Q33979 S/0000/63/OaG/000/0011/0017
AUTHOR: Prosvirin, V. I.; Molchanov Yu. It.
TITLE:. -Modification of the polycaproamide structure by heat treatment
SOURCE: Geterotsepay*ye vy*aokomolekul_varny*ye soyedinenlya (Haterochain macro-
molecular compounds); sbornik statey. Moscow, fz&vo "Nauka, 11 1963, 11-17
TOPIC TAGS: polymer, polymer structure, polycaproamide, polycaproamide structure,
heat treated polymer, heat treated polyeaproamide, quenched polymer, quenched poly@
qaproamide, polymer structural analysis
ABSTRACT: A structural analysis of polycaproamide (1) was carried out to study the
effects of heat treatment and quenching on polymer properties and structure. Cast
specimens (diam., 20 mm; heated to 24OC; slow-cooled at IC/min) were used for the
microstructural, microhardnegs and X-ray analysis and molded specimens (from grains,
160C. 100 kg/c,,m2) for thermal analysis. All test pieces were heated in a C02 at-
Imosphere. Crystallization of I tends to significant supercooling. The crystall-
Ization temperature drops by 3-4C for the range 1-15C/mia.. when the rate of cooling Is
Increased by 7C/mia. Crystallization, in a supercooled state significantly affects the
microstructure. Aa exothermic effect attributable to low-temperature crystallization fit
card 1/2

ACCESSION NR: AT4033979
view of Increased mobility of paraffin groups, Is observed when partially crystallized
I
polymer (1) is hoated (0-110C). Rapid cooling can stabilize the high temperature
structure of the polymer's crystalline lattice. Analysis of microhardness cuives points to
a markedly heterogeneous stin@oture, the pres6nce of widely varylng.local'microhardness
and the presence of various structural elements. OrIg. art. has: 4 graphs, 1jable, and
I illustratioa.
ASSOMATION: Institut avtomatild I melrhanild AN @gtvgslt (Thatitulp of Automation and
Mechanics AN Latv. SSR)
SUBMITTED: 28AprG2 ENCL: 00
SUB CODE: OC, MT NO REF SOV: 013 OTHER: 011
Card 2/2

ACCESSION XR: AT4040799 912685163/000/002/007710086
AUTHOR: MoIchanov.. Yu. M
TITLE: Effect of hydrostatic stress; on the structure of polycaprolactam.
SOURCE: AN LatSSR. Institut avtomatiki I mekhaniki. Prevrashchenlyz v splavakh I I
yzatmodeyatviye, faz, no. 2, 19631 77-86
MOPIC TAGS: polycaprolactam, polymer, polymer microhardness, polymer structure,
lydrostatic polymer prestressing, pressure level effect, prestiessing temperature, cooling
!rate, pressure related structure modification
jABSTRACT: Samples of polycaprolactam extruded at 300 kg/cmZ"and 230C were prestresAd!'
lbriefly under high pressure, then hydrostatically compressed for- 60 min. at pressures of
;5600* 10300, 16300, and 22,100 kg/cm,2 and temperatures of 20, 110, 190, and 230C. The
aterial was cooled at rates of i. 5 or 70*/min. Measurements of microhardness and micro-
Structural analysts Indicated that hydrostatic compressloa Increases microhardness sub-
stantially, tho peak Increase (from average levels to 30 kg/mmZ) occurring for 60 min. at
=2 and 1. 6"/min. It was noted that spherufftes in the material break down:
jinto thin fibrillic strands as temperature or pressure Increases and that further increases In
;these factors cause breakdown of these fibrillia atructuris., Orig. art. has: 13 graphs and
photomicrographs.
Card

ACCESSION NR-. AT4040900 9/2685/63/000/002/009710006
AUTHOR: Malchanov, Yu. K.; ftolint Th. K*
TITLE: Effect of wctrusion conditions on the properties of a graphite plastic
SOURCE: AN LatSSR. Institut aytomatiki I mekhaaiki. Prevrashchenlya, v splavakh i
vzaimodeystiiye faz, no. 2, 1963, 87-95
TOPIC TAGS: graphite containing 'plastle, plastic resistivity; plastic wear characterisga.
plastic hardness,, plastic permanent set, eKtruslon pr6sgure effect, ad-rusion, temperature
phenalformaldehyde resin
effect, pressure Preheating effect, plastic extrusion, graphite,
ABSTRACT: Effects of pressure and temperature conditions during edruslon were analyzed
by testing samples of a graphite plastic used for spacers in the current collectors of electric
tMIleys. The composition included 85% graphite dust, 13% phenolfdrmaldehyde resin jF 16
and 2% technical urotropine. The mWare was kept for 30 min. at 1800, then wdruded at
that temperature under pressures ranging from 300 to 1600 kg/cnA . Preheating was under
pressure, but the material was cooled in an unstressed state. Peak Brinell hardness of
16 kgJmm2 was obtained when extruding at 700 WcmZ. Minfroal permanent set and specific
Ila

F T
. , I
- I
. %k - . . -

KOLCHAN"t lu4sof iazho
Mrine reactors with various types of coolants. Sudostroenie 27
no-4-.64-69 AP t6l- 041RA 24:3)
(Nuclear reactors) (Atomic ships)

NOWHAM, Yu.S.. inzh.
Imestigating turbine stage operations writh weet steam (frem
'Escher Visa. Mittelung," no.l,, 2,, 3; 1960; uSchweizerische
Bauzeitung,".no.22, 1959). Sudostroanie 28 no.7:73-.76 Jl 162,
(MIRL 15;8)
(Steam turbines, Marine)