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Experimental and Numerical Simulation of Flameholders in a Ramjet Combustor

Author: XuJunMin
Tutor: ZhuMinBo；GeLiHu
School: Xi'an University of Electronic Science and Technology
Course: Mechanical Engineering
Keywords: Asian scramjet Flame stabilizer Simulation test Numerical Simulation
CLC: V235.21
Type: Master's thesis
Year: 2007
Downloads: 55
Quote: 0
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Abstract


In Asia scramjet combustion chamber , the flame stabilizer is the key component . Through comparative analysis , chose evaporative flameholder V-shaped groove , the structural parameters of design calculations. According to kinetic similarity principle , combined with the actual capacity of bench tests to determine the test program and test parameters . Interception as the actual structure of the stabilizer local test pieces , using isothermal, Mach number , buck simulation test program to determine the test control parameters. Theoretical analysis and numerical simulation show that the test conditions and the actual working conditions and dynamics of movement similar to the similar degree of approximation developed to meet the engineering requirements . Simulation test by the stabilizer , the stabilizer determined cold resistance coefficient and thermal coefficient simulation proved fitting empirical formula is reasonable. Combustion testing to determine the stability boundary of the stabilizer , lean boundary α ≈ 40, much larger than the engine requirements ; oil-rich border a ≈ 2, this is the cross-sectional average coefficient of residual gas , stabilizers should be less than one nearby . Evaporator tube is not stable oil supply , the test to determine the stability boundary 2.5 ≤ α ≤ 5. For the expansion of the oil-rich border , there is an optimal amount of oil stabilizer , namely the need to ensure cruising evaporation tube gas-oil ratio of about 0.4 , the point of attack need to ensure that this value is about 0.6 . It was found that the gas chamber I coefficient , chamber pressure , fuel injection means greater impact on efficiency . Maximum combustion efficiency coefficient of residual gas in the region between 2-4 . Studies have shown that the stability of the structure is able to meet the requirements of ramjet combustor , testing and analysis can provide important reference for engine development work .

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Air jet engine > Compressor engine > Ramjet engine
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