Nonlinear uncertainty impact of geometric variations on aerodynamic performance of low-pressure turbine blades with ultra-high loading under extreme operational conditions  

作　　者：Xiaojing WANG Zhengping ZOU Chao FU Pengcheng DU 

机构地区：[1]School of Energy and Power Engineering,Beihang University,Beijing 100191,China [2]National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,Beihang University,Beijing 100191,China [3]Research Institute of Aero-Engine,Beihang University,Beijing 100191,China

出　　处：《Chinese Journal of Aeronautics》2024年第5期281-300,共20页中国航空学报（英文版）

基　　金：This study was supported by the National Science and Technology Major Project,China(No.J2019-II-0012-0032),which is gratefully acknowledged.

摘　　要：Uncertainty impact of random geometric variations on the aerodynamic performance of low-pressure turbine blades is considerable,which is further amplified by the current ultra-high-lift design trend for weight reduction.Therefore,this uncertainty impact on ultra-highly loaded blades under extreme operational conditions near the margins with potential large-scale open separation is focused on in this study.It is demonstrated that this impact is significant,unfavourable,and nonlinear,which is clearly severer under extreme conditions.In addition to the overall attenuation and notable scattering of specific performance,the operational margins with open separation are also notably scattered with great risk of significant reduction.This scattering and nonlinearity are dominated by the variations in leading-edge thickness.The thinning of leading edge triggers local transition,enhancing downstream friction and reducing resistance to open separation,which is further exacerbated by operational deterioration.However,the opposite thickening yields less benefit,implying nonlinearity.This unfavourable impact highlights the need for robust aerodynamic design,where both a safer operational condition and a more robust blade are indispensable,i.e.,a compromise among performance,weight,and robustness.Besides the necessary limitation of loading levels,a mid-loaded design is recommended to reduce adverse pressure gradients in both the leading edge and rear region of the suction side,which helps to decrease the susceptibility of the transition and open separation to random perturbations.Similar improvements can also be achieved by appropriately thickening the leading edge.

关 键 词：Ultra-highly loaded turbine blade Geometric variations Uncertainty analysis Operational margins Robust aerodynamic design NONLINEARITY 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]