摘要
航空发动机向大幅度提高推重比和降低油耗的方向发展。涡轮进口温度在不断的提高。随着叶片热负荷的加大,冷却用气量也不断加大,最多已占到涡轮进口流量的 2 0 %左右。冷却气的喷射对高压涡轮级的三元流场会产生不可忽略的影响。在多叶片排三元N S方程并行解的基础上,采用冷却气射流源项模型。
Aeroengine is developing to perform higher thrust-weight ratio and lower fuel consumption by means of increasing turbine inlet temperature. The increase of the blade thermal load needs more cooling air to protect the blade's safety. The mass flow of cooling air has arrived to twentypercent of the turbine inlet flow at maximum. The influenceof the cooling air injection will not be neglected in the 3D flow field in high pressure turbine. Based on the parallel solution of multistage 3D Navier-stokes equation, this paper uses a source term model describing the cooling air injection, and the characteristic of the flow field and temperature field in one stage high pressure turbine considering the effect of cooling air mixing was evaluated.
出处
《中国科学院研究生院学报》
CAS
CSCD
2003年第2期155-159,共5页
Journal of the Graduate School of the Chinese Academy of Sciences
关键词
高压涡轮级
三元流场
冷气掺混
high pressure turbine stage,3D flow structure , cooling air mixing
