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突变型进气畸变对某型发动机稳定性的影响 被引量：4

EFFECT OF ABRUPT INLET DISTORTION ON ENGINE STABILITY
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摘要 The unsteady response of a compressor to abrupt change of inlet temperature has been calculated by numerical integration with the“actuator-volume”and the second order delay models.The calculated results are compared with flight test data favourably.The unsteady response of the compressor to abrupt change of inlet pressure(or combined with inlet temperature)has also been calculated in the same manner.The calculated results show that the effects of the abrupt inlet pressure on compressor stability cannot be ignored. The unsteady response of a compressor to abrupt change of inlet temperature has been calculated by numerical integration with the“actuator-volume”and the second order delay models.The calculated results are compared with flight test data favourably.The unsteady response of the compressor to abrupt change of inlet pressure(or combined with inlet temperature)has also been calculated in the same manner.The calculated results show that the effects of the abrupt inlet pressure on compressor stability cannot be ignored.
作者 王小峰 王乃行
机构地区 飞行试验研究院 西北工业大学
出处 《航空动力学报》 EI CAS CSCD 北大核心 1991年第2期167-169,共3页 Journal of Aerospace Power
关键词 航空发动机 进气畸变 稳定性
分类号 V231.1 [航空宇航科学与技术—航空宇航推进理论与工程]
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参考文献3

  • 1王小峰，1990年
  • 2左汉中，1988年
  • 3蔡元虎，1985年

同被引文献27

  • 1吴虎,廉小纯,崔建勇.跨音多级轴流压气机对突变型扰动的动态响应[J].推进技术,1997,18(3):56-58. 被引量：4
  • 2魏玲.跨声速压气机转子三维流场Navier-Stokes方程数值模拟[D].南京:南京航空航天大学,2005.
  • 3Mei Y, Guha A. Implicit Numerical Simulation of Tran- sonic Flow Through Turbine Cascades on Unstructured Grids [ J]. Journal of Power and Energy, 2005, 219 (1) :35-47.
  • 4Xu Da, Deng Qinghua, Feng Zhenping. Numerical Inves- tigation on Rotor Tip Leakage Control by Casing Air Injec- tion for a Radial Inflow Turbine [ R]. ASME 2011-GT- 46123.
  • 5Toro E F. Riemann Solvers and Numerical Methods forFluid Dynamics, a Practical Introduction, the Third Edi- tion [ M]. London: Springer, 2009.
  • 6Jung S K, Myong R S, Cho T H. Development of Euleri- an Droplets Impingement Model Using HLLC Riemann Solver and POD-Based Reduced Order Method [ R]. AIAA 2011-3907.
  • 7Berthon C, Charrier P, Dubroca B. An HLLC Scheme to Solve the Ml Model of Radiative Transfer in Two Space Dimensions [J]. Journal of Scientific Computing, 2007, 31(3) : 347-389.
  • 8Gurski K F. An HLLC-Type Approximate Riemann Solver for Ideal Magneto Hydrodynamics [ J]. SIAM Journal of Science Computation, 2004, 25 (6): 2165-2187.
  • 9Mignone A, Bodo G. An HLLC Riemann Solver for Rela- tivistic Flows - II. Magnetohydrodynamics [ J]. Monthly Notices of the Royal Astronomical Society, 2006, 368 (3) : 1040-1054.
  • 10Wenzel L M. Experimental Investigation of the Effects ofPulse Pressure Distortions Imposed on the Inlet of a Tur- bofan Engine [ R]. NASA TM X-1928, 1969.

引证文献4

二级引证文献3

航空动力学报
1991年 第2期

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