Wide-range ramjet as a part of combined propulsion for ...files.mai.ru/site/conf/aeroweek/3....

MOSCOW AVIATION INSTITUTE

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Scientific research group "Experimental Study of Combustion"

Wide-range ramjet as a part of combined

propulsion for space transport system

Mr. Mescheryakov Denis

chief lector


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CONCEPTUAL MODEL OF DEMONSTRATOR

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THE CONCEPT OF THE WIDE RANGE COMBUSTION CHAMBER, FUEL – CH4+H2

The variable geometry combustion chamber

Thermal throat

Mobile cowl

Mobile flameholder

Fuel injectors


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FRANCE-RUSSIA COOPERATION UNDER THE LEA PROGRAM

MBDA, ONERA (France) - MAI, CIAM, design bureau RADUGA (Russia)

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Mf=2 Mf=7 Mf=4-5

MAIN STAGES OF WORK UNDER THE LEA PROGRAM


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Комплекс стендового оборудования, позволяющий проводить испытания как

отдельных элементов, так и РПД в целом.THE TEST-BENCH FOR THE LEA PROGRAM WIDE-RANGE SCRAMJET

INVESTIGATION


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Комплекс стендового оборудования, позволяющий проводить испытания как

отдельных элементов, так и РПД в целом.


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LEA COMBUSTION CHAMBER MODEL TESTS, NOZZLE EXIT VIEW


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0.0

0.5

1.0

0 2 4 6 8 10 12 14

X/De

Pw

_i/P

o

ER = 0.00

ER = 0.76

ER = 0.83

ER = 0.87

ER = 0.88

ER = 0.89

0.00

0.05

0.10

0 2 4 6 8 10 12 14X/De

Pw

_i/P

o

ER = 0.00

ER = 0.36

ER = 0.42

ER = 0.48

ER = 0.61

ER = 0.62

0.00

0.10

0.20

0 2 4 6 8 10 12 14X/De

Pw

_i /P

o

ER = 0.00

ER = 0.41

ER = 0.65

ER = 0.76

ER = 0.83

ER = 0.90

a)

b)

c)

STATIC PRESSURE DISTRIBUTION IN LEA COMBUSTION CHAMBER MODEL


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Т0= 400K,

Мп = 2

Т0= 1200K,

Мп = 5

Т0= 2100K,

Мп = 7

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MEASUREMENT OF TEMPERATURE DISTRIBUTION IN JET AT THE COMBUSTION

CHAMBER EXIT

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0

1

2

3

4

5

6

800 900 1000 1100 1200 1300 1400 1500 1600 1700

Temperature, C

To=1400 C

To=1000 C

To=1700 C


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CONCLUSION

This concept of combustion chamber with mechanical

stabilization allows to work both in the subsonic mode (Mf=2-3),

transonic mode (Mf=4-5) and in the supersonic mode (Mf=6-7).

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• The development of single-mode and wide-range ramjet combustion chambers Mock-up according to the Concept design of Customer ( from technical documentation up to

hot tests at our test bench); • Experimental work and testing of the Customer combustion chambers to determine the

parameters of the working process and optimization, with subsonic and supersonic combustion. Our test bench allows to simulate the parameters at the combustion chamber inlet, which corresponds to flight Mach numbers 2 - 7.5. The fuel: kerosene, methane, hydrogen, etc.;

• The testing of high-temperature materials, heat-resistant coating and structural members, heat-stressed components of the combustion chambers and flight vehicles in conditions of subsonic or supersonic flow with high temperature up to 25000K. Testing of structural elements is possible using heated up to 6000C fuel, supplied to the internal channels of the cooling jacket of the test samples;

• The development and tests of flame heaters fueled by gasoline, kerosene, methane, ,

etc. (carrying out tests at the MAI test bench and then export the equipment to the Customer, if necessary);

• The development and manufacturing of devices for measuring the high-velocity high-temperature flow parameters (at the customer's specification) - cooled Pitot tubes grids, grids with ceramic sticks for infrared measurements;

• The measurements of physical parameters, acoustic and of pulsating characteristics of

the high-temperature high-velocity flows inside the model burners, furnaces, combustion chambers and in the open jets ( for example, for verification of the mathematical models ).


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Thank you for attention

Wide-range ramjet as a part of combined propulsion for ...files.mai.ru/site/conf/aeroweek/3....

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