Geometric Parametric Modeling and Pressurization Characteristics Analysis of a Multistage Transonic Axial Compressor

GUAN Liuping; JU Yaping; ZHANG Chuhua

doi:10.7652/xjtuxb202303012

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Geometric Parametric Modeling and Pressurization Characteristics Analysis of a Multistage Transonic Axial Compressor

更新时间：2025-07-09

- Geometric Parametric Modeling and Pressurization Characteristics Analysis of a Multistage Transonic Axial Compressor
- Vol. 57, Issue 3, Pages: 129-138(2023)
- 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：
- 基金信息：
- DOI：10.7652/xjtuxb202303012
  CLC： TK05
- Online First：10 March 2023，
  
  Published：2023
- 稿件说明：
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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：

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.

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references

LIEBLEIN S, LEWIS G W Jr, SANDERCOCK D M. Experimental investigation of an axial flow compressor inlet stage operating at transonic relative inlet Mach numbers: I Over-all performance of stage with transonic rotor and subsonic stators up to rotor relative inlet Mach number of 1.1[EB/OL].(2013-08-16)[2021-05-01]. https://ntrs.nasa.gov/search.jsp?R=19930086942.

BIOLLO R, BENINI E. Recent advances in transonic axial compressor aerodynamics [J]. Progress in Aerospace Sciences, 2013, 56: 1-18.

BROICHHAUSEN K D, ZIEGLER K U. Supersonic and transonic compressors: past, status and technology trends [C]//ASME Turbo Expo 2005: Power for Land, Sea, and Air. New York, NY, USA: ASME, 2005: 63-74.

STEARNS E M. Energy Efficient Engine core design and performance report[EB/OL].(1982-12-01)[2021-05-01]. https://ntrs.nasa.gov/citations/19900019243.

TURNER M G, MERCHANT A, BRUNA D. A turbomachinery design tool for teaching design concepts for axial-flow fans, compressors, and turbines [J]. Journal of Turbomachinery, 2011, 133(3): 031017.

SIDDAPPAJI K. Parametric 3D blade geometry modeling tool for turbomachinery systems [D]. Cincinnati, OH, USA: University of Cincinnati, 2012.

CLAUS R W, BEACH T, TURNER M, et al. Geometry and simulation results for a gas turbine representative of the energy efficient engine(EEE)[EB/OL].(2015-02-01)[2021-06-20]. https://ntrs.nasa.gov/search.jsp?R=20150002712.

李林熹. 某多级压气机气动设计方法及流场结构分析研究 [D]. 哈尔滨: 哈尔滨工业大学, 2017.

JOHN A, QIN Ning, SHAHPAR S. Using shock control bumps to improve transonic fan/compressor blade performance [J]. Journal of Turbomachinery, 2019, 141(8): 081003.

BANJAC M, PETROVIC M V. Development of method and computer program for multistage axial compressor design: part I Mean line design and example cases [C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2018: V02CT42A007.

BANJAC M, PETROVIC M V. Development of method and computer program for multistage axial compressor design: part II Two-dimensional design and validation using CFD [C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2018: V02CT42A008.

闫转运, 成金鑫, 陈江. 多级轴流压气机通流造型一体化设计研究 [J]. 工程热物理学报, 2016, 37(6): 1218-1224.

YAN Zhuanyun, CHENG Jinxin, CHEN Jiang. Integrated through-flow and blade shape design of multi-stage axial flow compressor [J]. Journal of Engineering Thermophysics, 2016, 37(6): 1218-1224.

WISLER D C, KOCH C C, SMITH L H Jr. Preliminary design study of advanced multistage axial flow core compressors [EB/OL].(1977-02-01)[2021-05-01]. https://ntrs.nasa.gov/search.jsp?R=19770013161.

HOLLOWAY P R, KNIGHT G L, KOCH C C, et al. Energy efficient engine high pressure compressor detail design report [EB/OL].(1982-05-01)[2021-05-01]. https://ntrs.nasa.gov/citations/19850002690.

CLINE S J, FESLER W, LIU H S, et al. High pressure compressor component performance report [EB/OL].(1983-09-01)[2021-05-01]. https://ntrs.nasa.gov/citations/19850025825.

DUNAVANT J C. Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts [EB/OL]. [2021-12-01]. https://ntrs.nasa.gov/citations/19930088445.

GOODHAND M N, MILLER R J. Compressor leading edge spikes: a new performance criterion [J]. Journal of Turbomachinery, 2011, 133(2): 021006.

THEODORSEN T. Theory of wing sections of arbitrary shape[EB/OL]. [2021-12-01]. https://ntrs.nasa.gov/citations/19930091485.

西安交通大学. 基于保角变换的NACA 6-系列叶型造型软件V1.0: 中国,2021SR2137767 [CP]. 2021-12-24.

DE BOOR C, HÖLLIG K, SABIN M. High accuracy geometric Hermite interpolation [J]. Computer Aided Geometric Design, 1987, 4(4): 269-278.

邱名. 高级压比轴流压气机转子通道内激波组织研究 [D]. 南京: 南京航空航天大学, 2014.

舒士甄, 朱力, 柯玄龄, 等. 叶轮机械原理 [M]. 北京: 清华大学出版社, 1991: 219-225.

LEI Fan, JU Yaping, ZHANG Chuhua. A rapid and automatic optimal design method for six-stage axial-flow industry compressor [J]. Journal of Thermal Science, 2021, 30(5): 1658-1673.

WANG Junying, HE Xiao, WANG Baotong, et al. Shapley additive explanations of multigeometrical variable coupling effect in transonic compressor [J]. Journal of Engineering for Gas Turbines and Power, 2022, 144(4): 041015.

迟志东, 楚武利, 张耀峰, 等. 缝式机匣处理对跨声速轴流压气机叶尖流场结构的非定常影响 [J]. 西安交通大学学报, 2021, 55(11): 25-33.

CHI Zhidong, CHU Wuli, ZHANG Yaofeng, et al. Unsteady effect of slot-type casing treatment on the rotor tip flow structures in a transonic axial flow compressor [J]. Journal of Xi'an Jiaotong University, 2021, 55(11): 25-33.

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