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作 者:Shenghui ZHANG Shuiting DING Peng LIU Tian QIU
机构地区:[1]National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 100191,China [2]Research Institute of Aero-Engine,Beihang University,Beijing 100191,China
出 处:《Chinese Journal of Aeronautics》2023年第5期250-267,共18页中国航空学报(英文版)
基 金:funded by the National Science Foundation of China(No.61890923);the National Science and Technology Major Project,China(No.J2019-VIII-0001-0162).
摘 要:Advanced civil aero-engines tend to adopt lean burn combustors to meet emission requirements.The exit of a lean burn combustor experiences highly non-uniformities in both temperature(Hot Streak,HS)and flow(swirl).This paper presents a numerical investigation on the behaviors of a High-Pressure(HP)turbine under a combined effect of swirl and hot streak.The investigation was conducted on a GE-E3 HP turbine with unsteady numerical simulations,which considered the realistic clocking position of the HP Nozzle Guide Vane(NGV)relative to the combustor.The influences of swirl orientations on the HS migration and thermal performances on the blade surface were examined.Results indicate that,inside the NGV passage,the swirl’s induced incidence angle effect dominates the HS radial migration.The transversal movement of HS follows the cross flow and thus makes itself approach the Suction Side(SS)and keep away from the Pressure Side(PS)as passing through the NGV,so that HS near the SS is more influenced by the incidence angle effect than that near the PS.As for the heat transfer,swirl affects the Heat Transfer Coefficient(HTC)on the NGV’s PS and SS mainly through the incidence angle effect.Different from the NGV,the inlet swirl and HS have limited effect on the HTC on the rotor blade’s PS,while on the rotor blade’s SS,the original vortex system dominates;therefore,the inlet non-uniformities merely enhance the HTC on the SS rather than alter its distribution characteristics.
关 键 词:High-pressure turbine Hot streak Thermal performances SWIRL ORIENTATIONS VORTEX
分 类 号:V231.2[航空宇航科学与技术—航空宇航推进理论与工程]
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