Scaling study of the combustion performance of gas–gas rocket injectors

doi:10.1088/1674-1056/20/10/104701

Abstract To obtain the key subelements that may influence the scaling of gas-gas injector combustor performance, the combustion performance subelements in a liquid propellant rocket engine combustor are initially analysed based on the results of a previous study on the scaling of a gas-gas combustion flowfield. Analysis indicates that inner wall friction loss and heat-flux loss are two key issues in gaining the scaling criterion of the combustion performance. The similarity conditions of the inner wall friction loss and heat-flux loss in a gas-gas combustion chamber are obtained by theoretical analyses. Then the theoretical scaling criterion was obtained for the combustion performance, but it proved to be impractical. The criterion conditions, the wall friction and the heat flux are further analysed in detail to obtain the specific engineering scaling criterion of the combustion performance. The results indicate that when the inner flowfields in the combustors are similar, the combustor wall shear stress will have similar distributions qualitatively and will be directly proportional to p_c^0.8 d_t^-0.2 quantitatively. In addition, the combustion peformance will remain unchanged. Furthermore, multi-element injector chambers with different geometric sizes and at different pressures are numerically simulated and the wall shear stress and combustion efficiencies are solved and compared with each other. A multi-element injector chamber is designed and hot-fire tested at several chamber pressures and the combustion performances are measured in a total of nine hot-fire tests. The numerical and experimental results verified the similarities among combustor wall shear stress and combustion performances at different chamber pressures and geometries, with the criterion applied.

Keywords: scaling combustion performance subscale combustor wall friction gas-gas combustion

Received: 16 March 2011
Revised: 16 May 2011
Accepted manuscript online:

PACS:	47.70.-n	(Reactive and radiative flows)
	84.60.Bk	(Performance characteristics of energy conversion systems; figure of merit)
	62.40.+i	(Anelasticity, internal friction, stress relaxation, and mechanical resonances)
	28.50.Ky	(Propulsion reactors)

Fund: Project supported by the National High Technology Research and Development Program of China (Grant No. 2009AA702*) and the Innovation Foundation of Beijing University of Aeronautics and Astronautics for PhD Graduates (Grant No. 430569).

Cite this article:

Wang Xiao-Wei(汪小卫), Cai Guo-Biao(蔡国飙), and Jin Ping(金平) Scaling study of the combustion performance of gas–gas rocket injectors 2011 Chin. Phys. B 20 104701

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Scaling study of the combustion performance of gas–gas rocket injectors

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