多级跨声速轴流压气机几何参数化造型方法及增压特性分析

关柳萍; 琚亚平; 张楚华

doi:10.7652/xjtuxb202303012

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多级跨声速轴流压气机几何参数化造型方法及增压特性分析

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- 多级跨声速轴流压气机几何参数化造型方法及增压特性分析
- Geometric Parametric Modeling and Pressurization Characteristics Analysis of a Multistage Transonic Axial Compressor
- 西安交通大学学报 2023年57卷第3期页码：129-138
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
  
  : 2022-06-22。作者简介: 关柳萍(1998—),女,博士生
  琚亚平(通信作者),女,教授,博士生导师。基金项目: 国家重大科技专项资助项目(2017-II-0006-0020, J2019-II-0017-0038)。
- 基金信息：
  
  : 2022-06-22。作者简介: 关柳萍(1998—),女,博士生;琚亚平(通信作者),女,教授,博士生导师。基金项目: 国家重大科技专项资助项目(2017-II-0006-0020, J2019-II-0017-0038)。
- DOI：10.7652/xjtuxb202303012
  中图分类号： TK05
- 网络首发：2023-03-10，
  
  纸质出版：2023
- 稿件说明：
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关柳萍, 琚亚平, 张楚华. 多级跨声速轴流压气机几何参数化造型方法及增压特性分析[J]. 西安交通大学学报, 2023,57(3):129-138.

GUAN Liuping, JU Yaping, ZHANG Chuhua. Geometric Parametric Modeling and Pressurization Characteristics Analysis of a Multistage Transonic Axial Compressor[J]. 2023, 57(3): 129-138.
关柳萍, 琚亚平, 张楚华. 多级跨声速轴流压气机几何参数化造型方法及增压特性分析[J]. 西安交通大学学报, 2023,57(3):129-138. DOI： 10.7652/xjtuxb202303012.

GUAN Liuping, JU Yaping, ZHANG Chuhua. Geometric Parametric Modeling and Pressurization Characteristics Analysis of a Multistage Transonic Axial Compressor[J]. 2023, 57(3): 129-138. DOI： 10.7652/xjtuxb202303012.

摘要

为发展高性能多级跨声速压气机先进设计体系

提出了压气机多圆弧叶型、多圆弧厚度分布叶型及修正NACA 6-系列叶型造型方法

利用NASA/GE研发的高效节能发动机E

高压压气机前6.5级的准三维设计数据

建立了相应的压气机三维几何参数化模型

并通过数值模拟研究了造型压气机在多个转速下的内部流动及增压特性。结果表明:在100%设计转速近最高效率点处

造型压气机的质量流量与设计目标及与原型压气机试验结果的误差分别为0.4%和0.6%

绝热效率的误差分别为1.9%和0.9%; 造型压气机模拟及原型压气机试验所得总压比均低于设计目标; 前排跨声转子叶片气动负荷过大导致激波脱体严重是压气机的主要设计不足

改善叶片气动负荷分布、缓解叶片溢流是提升压气机气动性能尤其是设计点总压比的有效方法。研究成果对开展多级跨声速压气机设计优化具有参考价值。

Abstract

In order to develop an advanced design system for high performance multistage transonic compressors

a multi-circular arc(MCA)airfoil parametric modeling method

an MCA thickness-distribution airfoil parametric modeling method and a modified NACA 6-series airfoil parametric modeling method are proposed. The quasi-3D design results of the front 6.5 stages of the energy efficient engine(E

)high pressure compressor co-designed by NASA/GE are utilized to construct the parametric compressor model. Then the computational fluid dynamic method is used to numerically simulate th

e internal flows and pressurization characteristics of the parametric compressor under variable rotational speed conditions. The results show that compared with the design target and prototype compressor's experimental result at near peak efficiency point of 100% design speed

the errors of the mass flow rate are 0.4% and 0.6%

respectively

and the errors of adiabatic efficiency are 1.9% and 0.9%

respectively. The total pressure ratios of the parametric compressor and of the prototype compressor are both lower than the design target. The total pressure ratio deficiency is mainly accounted for the severe shock detachment caused by the excessive aerodynamic load of the front transonic rotor. By reasonably adjusting the aerodynamic load distribution and decreasing the flow spillage

the compressor aerodynamic performance especially the total pressure ratio at the design condition can be improved. The outcomes have reference values for the design optimization of multistage transonic compressors.

关键词

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references

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