Review on high-pressure turbine aero-thermal mechanisms and design under effects of combustor exit flow

With the development of turbine aero-thermal design technology for aircraft engines/gas turbines and the continuous increment of requirements for turbine aero-thermal performance， the high-pressure turbine aero-thermal mechanisms and design issues under the effects of non-uniform temperature and flow fields at the combustor exit have attracted wide spread attention. Firstly， the key characteristics of temperature profiles and flow fields at different combustor exits and their characterization methods were introduced. Secondly， the influence mechanisms of the combustor exit hot streak， total pressure profile， and swirling profile on the high-pressure turbine aero-thermal characteristics were discussed. The aerodynamic performance， flow field structures， heat transfer， and film cooling characteristics of the turbine were analyzed. The current research status and existing problems regarding combustor-turbine integrated numerical simulations and experiments， and the uncertainty quantification of turbine aero-thermal performance were also discussed. Additionally， the design schemes of high-pressure turbine aerodynamic and cooling structures considering the influences of combustor exit flow， as well as the combustor-turbine integrated design schemes were analyzed. Finally， the current research status is reviewed， and future research should be focused on the measurement of turbine aero-thermal performance at combustor-turbine integrated condition， the combustor-turbine integrated numerical simulation methods and their validation， optimization of turbine cooling structures and robust design， as well as combustor-turbine integrated design method.