MOSCOW AVIATION INSTITUTE [email protected] 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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MOSCOW AVIATION INSTITUTE
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
MOSCOW AVIATION INSTITUTE
Scientific research group "Experimental Study of Combustion"
CONCEPTUAL MODEL OF DEMONSTRATOR
2
THE CONCEPT OF THE WIDE RANGE COMBUSTION CHAMBER, FUEL – CH4+H2
The variable geometry combustion chamber
Thermal throat
Mobile cowl
Mobile flameholder
Fuel injectors
MOSCOW AVIATION INSTITUTE
Scientific research group "Experimental Study of Combustion"
FRANCE-RUSSIA COOPERATION UNDER THE LEA PROGRAM
MBDA, ONERA (France) - MAI, CIAM, design bureau RADUGA (Russia)
3
Mf=2 Mf=7 Mf=4-5
MAIN STAGES OF WORK UNDER THE LEA PROGRAM
MOSCOW AVIATION INSTITUTE
Scientific research group "Experimental Study of Combustion"
4
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
MOSCOW AVIATION INSTITUTE
Комплекс стендового оборудования, позволяющий проводить испытания как
отдельных элементов, так и РПД в целом.
Scientific research group "Experimental Study of Combustion"
5
LEA COMBUSTION CHAMBER MODEL TESTS, NOZZLE EXIT VIEW
Scientific research group "Experimental Study of Combustion"
MOSCOW AVIATION INSTITUTE
6
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
Scientific research group "Experimental Study of Combustion"
MOSCOW AVIATION INSTITUTE
Т0= 400K,
Мп = 2
Т0= 1200K,
Мп = 5
Т0= 2100K,
Мп = 7
7
Scientific research group "Experimental Study of Combustion"
MOSCOW AVIATION INSTITUTE
MEASUREMENT OF TEMPERATURE DISTRIBUTION IN JET AT THE COMBUSTION
CHAMBER EXIT
8
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
Scientific research group "Experimental Study of Combustion"
MOSCOW AVIATION INSTITUTE
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).
9
Scientific research group "Experimental Study of Combustion"
MOSCOW AVIATION INSTITUTE
• 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 ).
Scientific research group "Experimental Study of Combustion"
MOSCOW AVIATION INSTITUTE
Thank you for attention
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