对转压气机动叶热态形变气动影响效应及冷热态叶型变换方法研究
Effects of Blade Deformation on the Aerodynamic Performance and Hot-to-Cold Transformation Method of a Counter-Rotating Compressor
王一勐 1徐强仁 2白素娟 2赵巍 3赵庆军 4徐建中3
作者信息
- 1. 中国科学院工程热物理研究所,北京 100190;中国科学院大学航空宇航学院,北京 100049
- 2. 中国科学院工程热物理研究所,北京 100190;中国科学院轻型动力创新研究院,北京 100190
- 3. 中国科学院工程热物理研究所,北京 100190;中国科学院大学航空宇航学院,北京 100049;中国科学院轻型动力创新研究院,北京 100190
- 4. 中国科学院工程热物理研究所,北京 100190;中国科学院大学航空宇航学院,北京 100049;中国科学院轻型动力创新研究院,北京 100190;中国科学院工程热物理研究所分布式冷热电联供系统北京市重点实验室,北京 100190
- 折叠
摘要
为探究高负荷对转压气机动叶形变对气动性能的影响,采用热流固耦合计算方法分析了离心、气动及热载荷作用下的叶片形变规律,探索了形变下低压转子及对转压气机的气动性能变化机理,并进一步开展了冷热态叶型变换方法研究.结果表明:在总载荷作用下,低压转子和高压转子叶片前缘分别向吸力面和压力面方向形变,导致低压转子工作点向失速边界移动,对转压气机堵塞流量降低,峰值效率下降.通过采用基于虚功原理的逆向求解计算,可以在无需变形量反向插值和迭代修正下得到动叶的冷态叶型,进而实现设计的气动性能.
Abstract
To clarify the effect of blade deformation on the aerodynamic performance of a highly loaded counter-rotating compressor,a thermal-fluid-structure interaction method is used to analyze the character of the blade deformation and the variation mechanism of aerodynamic performance under centrifugal,aerodynamic,and thermal loads.Additionally,a method for hot-to-cold trans-formation is developed.The results show that the leading edges of the low-pressure rotor deform towards the suction sides,whereas the leading edges of the high-pressure rotor deform towards the pressure sides.This leads to the operating point of the low-pressure rotor moving to the stall bound-ary,and results in the reduction of choke mass flow and peak efficiency of the compressor.By using nonlinear static analysis with inverse solving,the cold blade profile can be generated to achieve the aerodynamic performance of the design point without the need for deformation reverse interpolation and iterative correction.
关键词
对转压气机/热流固耦合/叶片形变/冷热态变换Key words
counter-rotating compressor/thermal-fluid-structure interaction/blade deformation/hot-to-cold transformation引用本文复制引用
基金项目
国家科技重大专项(J2019-Ⅱ-0016-0037)
国家科技重大专项(J2019-Ⅱ-0007-0027)
出版年
2024
NETL
NSTL
万方数据