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《Journal of Aerospace Power》 2009-05
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Comparative analysis of computational methods of supersonic combustor flowfield

WANG Cheng-peng,YANG Yong-yang,LIU Chen,WANG Jiang-feng,CHENG Ke-ming,WU Yi-zhao(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)  
The calculation of H2/air supersonic combustion flowfield in a typical combustor with "a constant-area section + an expansion section" was carried out with three methods: quasi-one-dimensional flow model,axisymmetric and three-dimensional Reynolds-averaged Navier-Stokes Solver.The hydrogen/air mechanism of 13 species and 32 reactions was used.The study shows that the quasi-one-dimensional flow model and three-dimensional Navier-Stokes Solver are effective for predicting the distribution of the parameters in the supersonic combustor.Good agreement is achieved between the calculated and experimental static pressure data except the precombustion shock train region.The quasi-one-dimensional flow model coupled with the finite-rate chemistry equations provides a rapid methodology with strong adoptability for performance prediction.The three-dimensional numerical simulation could depict the detailed information in the flow,but it will take up a great deal of time.Given different advantages,these two models would be used in different design phases of supersonic combustor.
【Fund】: 国家自然科学基金(1070202990716013);; 航空科学基金(2006ZB52013)
【CateGory Index】: V231.2
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