燃烧室和涡轮相互作用下高压涡轮级气热性能研究进展

doi:10.7527/S1000-6893.2020.24111

Abstract

Abstract: 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.

Key words: combustor, turbine, high pressure turbine stage, aerothermal performance, experimental measurement

CLC Number:

V434

LI Jun, LI Zhiyu, LI Zhigang, ZHANG Kaiyuan, SONG Liming. Aerothermal performance of high pressure turbine stage with combustor-turbine interactions: Review[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 24111-024111.

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

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