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Effects of Rotor-Bleeding Airflow on Aerodynamic and Structural Performances of a Single-Stage Transonic Axial Compressor
International Journal of Aeronautical and Space Sciences ( IF 1.7 ) Pub Date : 2019-12-20 , DOI: 10.1007/s42405-019-00239-5
Cong-Truong Dinh , Dinh-Quy Vu , Kwang-Yong Kim

This paper presents the effects of airflow bleed from the rotor shroud surface between leading and trailing edges on aerodynamic and structural performances of a single-stage transonic axial compressor, NASA stage 37, using three-dimensional Reynolds-averaged Navier–Stokes equations with the k–e turbulence model. A small airflow mass flow rate is bleed throughout a rotor-bleeding ejector which designed by seven parameters: bleeding angle (°) and ejection angles (°), ejection depth (D), bleeding thickness (H), bleeding position from rotor leading edge (L) in flow direction, bleeding ejection curvature (R), and bleeding width contacted on rotor shroud surface (W). The numerical results for aerodynamic performance: total pressure ratio, adiabatic efficiency, and stall margin of a transonic axial compressor were validated with a smooth casing experimental data. A parametric study of seven design parameters of rotor-bleeding ejector above combined with a small ejection mass flow rate in a single-stage transonic axial compressor for aerodynamic and structural performances was performed. The numerical results show that all aerodynamic performance increases with bleeding airflow from rotor shroud surface, the total deformation on rotor tip leading edge in spanwise direction reduces with a very small increasing in Von-Mises stress in a reference-bleeding airflow as compared to the results of smooth casing.

中文翻译:

转子排气气流对单级跨音速轴流式压缩机气动性能和结构性能的影响

本文介绍了从前缘和后缘之间的转子护罩表面排出的气流对 NASA 37 级单级跨音速轴流式压缩机的空气动力学和结构性能的影响,使用具有 k 的三维雷诺平均 Navier-Stokes 方程-e 湍流模型。一个小的气流质量流率通过七个参数设计的转子排气喷射器排气:排气角(°)和喷射角(°),喷射深度(D),排气厚度(H),从转子前缘的排气位置(L) 在流动方向上,放气喷射曲率 (R) 和接触转子护罩表面 (W) 的放气宽度。气动性能的数值结果:总压比、绝热效率、跨音速轴流压缩机的失速裕度和失速裕度通过光滑套管实验数据进行验证。对单级跨音速轴流式压缩机中的上述转子排气喷射器的七个设计参数结合小喷射质量流量进行了空气动力学和结构性能的参数研究。数值结果表明,所有气动性能随着从转子护罩表面排出气流而增加,与结果相比,在参考排出气流中,随着 Von-Mises 应力的增加非常小,翼尖前缘在翼展方向上的总变形减小光滑的外壳。对单级跨音速轴流式压缩机中的上述转子排气喷射器的七个设计参数结合小喷射质量流量进行了空气动力学和结构性能的参数研究。数值结果表明,所有空气动力性能随着转子护罩表面的放气气流而增加,与结果相比,在参考放气气流中,随着 Von-Mises 应力的增加非常小,翼尖前缘在翼展方向上的总变形减小光滑的外壳。对单级跨音速轴流式压缩机中的上述转子排气喷射器的七个设计参数结合小喷射质量流量进行了空气动力学和结构性能的参数研究。数值结果表明,所有气动性能随着从转子护罩表面排出气流而增加,与结果相比,在参考排出气流中,随着 Von-Mises 应力的增加非常小,翼尖前缘在翼展方向上的总变形减小光滑的外壳。
更新日期:2019-12-20
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