大涵道比风扇增压级进气畸变性能试验研究  

Experiment on inlet distortion of high bypass ratio fan and booster

作　　者：高倩 杨小贺 刘世文 GAO Qian;YANG Xiaohe;LIU Shiwen(Commercial Aircraft Engine Company Limited,Aero Engine Corporation of China,Shanghai 200241,China)

机构地区：[1]中国航发商用航空发动机有限责任公司,上海200241

出　　处：《航空动力学报》2025年第2期37-45,共9页Journal of Aerospace Power

摘　　要：针对某大涵道比涡扇发动机,开展了其风扇增压级性能进气总压畸变试验研究,以获取进气畸变对风扇增压级性能的影响。通过试验件进口安装畸变模拟网的形式模拟畸变来流条件。畸变图谱形式来源于短舱进气道风洞吹风试验,总压畸变形式为径向、周向组合畸变。结果表明:进气总压畸变会抬高风扇外涵工作点位置,从而降低外涵喘振裕度;相比均匀进气特性,进气总压畸变条件下风扇外涵换算质量流量和压比有增大趋势,0.3到0.8相对换算转速,换算质量流量增大范围为0.2%到1%;由于畸变区主要集中在外涵区域,风扇增压级内涵特性与均匀进气特性基本相当;畸变进气条件下,风扇进口畸变区静压偏低,经过风扇增压作用后静压快速抬高,支板后静压与均匀进气趋势基本一致。Based on a high bypass ratio turbofan engine,experimental investigation on the inlet total pressure distortion of the fan performance was carried out to obtain the fan-booster performance under crosswind conditions and support the engine crosswind test.The inlet total pressure distortion flow under the crosswind conditions was obtained by installing distortion simulation network.The distortion pattern was derived from the wind tunnel test of the engine nacelle.The total pressure distortion pattern included radial distortion and circumferential distortion.The results showed that the total pressure distortion raised the working point of the fan and reduced the surge margin.Compared with the fan performance of uniform flow,the corrected mass flow and total pressure ratio tended to increase,the mass flow ranged from 0.2%to 1%,while the corrected rotational speed ranged from 0.3 to 0.8.The core performance of the inlet total pressure distortion was similar with the performance of uniform flow.The static pressure of inlet total pressure distortion increased rapidly after the fan,and the static pressure behind the struts was basically consistent with that of the uniform flow.

关 键 词：大涵道比 风扇 总压畸变 畸变模拟网 喘振裕度 

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]