燃烧室和涡轮相互作用下高压涡轮级气热性能研究进展

现代燃烧室由于富油燃烧-快速焠熄-贫油燃烧技术和贫油预混燃烧技术导致其出口具有非均匀温度（热斑）分布、强旋流和高湍流度的流动特征，显著影响燃烧室下游高压涡轮级的气热性能。先进高压涡轮级气热性能分析和冷却设计越发依赖于燃烧室和涡轮相互作用下交界面的气热参数非均匀分布特征。论文阐述了燃烧室和涡轮相互作用机理。介绍了燃烧室和涡轮相互作用下高压涡轮级气热性能研究的代表性实验台和数值方法。分别综述了燃烧室和涡轮相互作用下热斑、热斑和旋流、旋流和湍流度对高压涡轮级气热性能的影响特性。给出了燃烧室和涡轮相互作用下高压涡轮级的气热性能分析及不确定性量化的研究现状。总结了燃烧室和涡轮相互作用下高压涡轮级气热性能的研究成果。展望了非均匀气热参数分布条件下高压涡轮级气热性能可靠性分析和鲁棒性设计需要更加深入研究的方向，为适应先进航空发动机的燃烧室和涡轮一体化设计需求提供参考。

Aerothermal performance of high pressure turbine stage with combustor-turbine interactions: Review

The combustor exit flow field is characterized by non-uniformity temperature profile (hot streaks), large swirl flow and high turbulence intensity due to the rich burn-quick quench-lean burn and lean burn premix technologies applied in modern combustors. This flow behavior significantly impacts on the aerothermal performance of the high pressure turbine stage downstream from the combustor. The aerothermal performance analysis and cooling design of the advanced high pressure turbine stage have become increasingly dependent on the non-uniformity aerothermal parameter distribution conditions at the interface between the combustor-turbine interactions. This paper elaborates the combustor-turbine interaction mechanism, introduces the representative experimental test rigs and numerical methodologies of aerothermal performance investigations of the high pressure turbine stage with combustor-turbine interactions, and respectively reviews the effects of the hot streaks, hot streaks and swirl flow, as well as swirl flow and turbulence resulted from combustor-turbine interactions on the aerothermal performance of the high pressure turbine stage. The current states and progress of aerothermal performance analysis and uncertainty qualification of the high pressure turbine stage considering combustor-turbine interactions are presented. The research achievements of aerothermal performance of the high pressure turbine stage with combustor-turbine interactions are summarized. The need for more in-depth research topics of the reliability analysis and robustness design of aerothermal performance for the high pressure turbine stage with the inlet non-uniformity aerothermal parameter distribution conditions are prospected. This paper provides reference for high performance combustor and turbine integrated design suitable for research and development requirements of advanced aeroengines.