Design Method of Blade Passage for Axial Compressor by Lofting along Flow Direction

ZHAO Yibo; LI Hao; JU Yaping; ZHANG Chuhua

doi:10.7652/xjtuxb202304005

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Design Method of Blade Passage for Axial Compressor by Lofting along Flow Direction

更新时间：2025-07-09

- Design Method of Blade Passage for Axial Compressor by Lofting along Flow Direction
- Vol. 57, Issue 4, Pages: 39-48(2023)
- 作者机构：
  
  1. 西安交通大学能源与动力工程学院,西安,710049
  2. 上海交通大学机械与动力工程学院,上海,200240
  3. 西安交通大学机械结构强度与振动国家重点实验室,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202304005
  CLC： TK05
- Online First：10 April 2023，
  
  Published：2023
- 稿件说明：
移动端阅览
ZHAO Yibo, LI Hao, JU Yaping, et al. Design Method of Blade Passage for Axial Compressor by Lofting along Flow Direction[J]. 2023, 57(4): 39-48.
DOI：

ZHAO Yibo, LI Hao, JU Yaping, et al. Design Method of Blade Passage for Axial Compressor by Lofting along Flow Direction[J]. 2023, 57(4): 39-48. DOI： 10.7652/xjtuxb202304005.

摘要

针对高负荷压气机角区流动质量差、流动损失显著的问题

以NASA Rotor37为研究对象

提出了一种轴流压气机叶道几何定义与参数化建模新方法

实现了叶片、角区和端壁结构的协同设计及叶片到端壁的高阶光滑过渡

在此基础上

开展了前缘边条和叶身融合对压气机转子气动性能和内部流场影响的数值研究。结果表明

针对NASA Rotor37流道

采用该叶道设计方法对压气机转子角区改型后:绝热效率提高了0.3%

喘振裕度由11.85%增加至18.8%; 下凹端壁可以帮助稳定压气机转子通流能力并减少改型过程的流量漂移; 叶身融合结构在叶根处提供径向向上的压力梯度

将低能流体从叶片角区吹向主流区以减少角区流动损失

而近叶根处主流区流动损失略有增加。研究成果对发展轴流压气机先进设计方法应具有参考价值。

Abstract

Aiming at the problems of poor flow quality and significant flow loss at corner region of axial compressors

NASA Rotor37 axial compressor was taken as the research object to propose a new geometry definition and parameterization method for the blade passage of axial compressor

which enabled the cooperative design of blade

corner and endwall structure

and realized the high order smooth transition between blade and endwall. On this basis

the influence on the aerodynamic performance and internal flow field of hub fillet were studied. The results showed that after modifying the blade passage of NASA Rotor37

the compressor adiabatic efficiency increased by 0.3% at the design point

and surge margin increased from 11.85% to 18.8%. The concave on endwall can help stabilize the compressor flow capacity and avoid flow drift during modification. The blended blade and endwall structure can produce a transverse pressure difference

removing the low energy fluid from the corner region to the main flow to reduce corner flow separation

while the main flow losses slightly increased. The new geometry defining and parametric modeling method of the axial compressor proposed in this paper and the findings of flow improvement mechanism of the corner flow have reference value for the further development of axial compressor design system.

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references

匡也, 王志恒, 李雨润, 等. 轴流压气机进口总压畸变的端区流动响应数值研究 [J]. 西安交通大学学报, 2020, 54(5): 53-60.

KUANG Ye, WANG Zhiheng, LI Yurun, et al. Numerical investigation on the response of end-wall flow to inlet total pressure distortion in axial compressor [J]. Journal of Xi'an Jiaotong University, 2020, 54(5): 53-60.

王佳宇, 胡骏, 姜超. 压气机静子非轴对称端壁优化设计及实验 [J]. 航空动力学报, 2021, 36(10): 2157-2172.

WANG Jiayu, HU Jun, JIANG Chao. Optimization design and test of the non-axisymmetric endwall of the compressor stator [J]. Journal of Aerospace Power, 2021, 36(10): 2157-2172.

ANANTHAKRISHNAN K, GOVARDHAN M. Influence of fillet shapes on secondary flow field in a transonic axial flow turbine stage [J]. Aerospace Science and Technology, 2018, 82/83: 425-437.

傅珏, 蒋伟, 柳一鸣, 等. 叶顶间隙几何不确定性对离心叶轮气动性能的影响 [J]. 西安交通大学学报, 2018, 52(11): 51-57.

FU Jue, JIANG Wei, LIU Yi ming, et al. Influence of tip clearance geometrical uncertainties on the aerodynamic performance of centrifugal impellers [J]. Journal of Xi'an Jiaotong University, 2018, 52(11): 51-57.

ATKINS M J. Secondary losses and end-wall profiling in a turbine cascade [J]. Journal of Engineering for Gas Turbines and Power, 1987, 111(2): 900-909.

ROSE M G. Non-axisymmetric endwall profiling in the HP NGV's of an axial flow gas turbine [C]//ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. New York, NY, USA: ASME, 1994: V001T01A090.

BRENNAN G, HARVEY N W, ROSE M G, et al. Improving the efficiency of the Trent 500-HP turbine using nonaxisymmetric end walls: part Ⅰ turbine design [J]. Journal of Turbomachinery, 2003, 125(3): 497-504.

李国君, 马晓永, 李军. 非轴对称端壁成型及其对叶栅损失影响的数值研究 [J]. 西安交通大学学报, 2005, 39(11): 1169-1172.

LI Guojun, MA Xiaoyong, LI Jun. Non-axisymmetric turbine end wall profiling and numerical investigation of its effect on the turbine cascade loss [J]. Journal of Xi'an Jiaotong University, 2005, 39(11): 1169-1172.

汪传美, 李国君, 郑金, 等. 非轴对称端壁成型技术的实验研究 [J]. 西安交通大学学报, 2008, 42(9): 1086-1090, 1101.

WANG Chuanmei, LI Guojun, ZHENG Jin, et al. Experimental investigation of non-axisymmetric endwall profiling technique in cascades [J]. Journal of Xi'an Jiaotong University, 2008, 42(9): 1086-1090, 1101.

HERGT A, DORFNER C, STEINERT W, et al. Advanced nonaxisymmetric endwall contouring for axial compressors by generating an aerodynamic separator: part Ⅱ experimental and numerical cascade investigation [J]. Journal of Turbomachinery, 2011, 133(2): 021027.

REUTTER O, ROZANSKI M, HERGT A, et al. Advanced endwall contouring for loss reduction and outflow homogenization for an optimized compressor cascade [J]. International Journal of Turbomachinery, Propulsion and Power, 2017, 2(1): 1.

CHU Wuli, LI Xiangjun, WU Yanhui, et al. Reduction of end wall loss in axial compressor by using non-axisymmetric profiled end wall: a new design approach based on end wall velocity modification [J]. Aerospace Science and Technology, 2016, 55: 76-91.

DEBRUGE L L. The aerodynamic significance of fillet geometry in turbocompressor blade rows [J]. Journal of Engineering for Gas Turbines and Power, 1980, 102(4): 984-993.

GOODHAND M N, MILLER R J. The impact of real geometries on three-dimensional separations in compressors [J]. Journal of Turbomachinery, 2012, 134(2): 021007.

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

伊卫林, 李嘉宾, 季路成. 叶身/端壁融合扩压叶栅气动性能实验与数值研究 [J]. 工程热物理学报, 2017, 38(8): 1655-1664.

YI Weilin, LI Jiabin, JI Lucheng. Experimental and numerical investigation on the aerodynamic performance of a compressor cascade using blended blade and end wall [J]. Journal of Engineering Thermophysics, 2017, 38(8): 1655-1664.

YI Weilin, JI Lucheng. Experimental investigation on the performance of compressor cascade using blended-blade-end-wall contouring technology [J]. Proceedings of the Institution of Mechanical Engineers: Part G Journal of Aerospace Engineering, 2018, 232(15): 2833-2844.

LI Jiabin, JI Lucheng, ZHOU Ling. Design optimization of a blended blade and endwall in a compressor cascade [J]. Journal of Engineering for Gas Turbines and Power, 2020, 142(2): 021003.

李超俊, 余文龙. 轴流压缩机原理与气动设计 [M]. 北京: 机械工业出版社, 1987: 67-86.[20] 陈玲, 琚亚平, 张楚华. 多级轴流压气机末级静子叶片串列改型方法及流动机理研究 [J]. 西安交通大学学报, 2022, 56(10): 170-179.

CHEN Ling, JU Yaping, ZHANG Chuhua. Tandem blading and flow mechanism of last stator of multi-stage axial flow compressor [J]. Journal of Xi'an Jiaotong University, 2022, 56(10): 170-179.

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(3): 129-138.

GUAN Liuping, JU Yaping, ZHANG Chuhua. Geometric parametric modeling and pressurization characteristics analysis of a multistage transonic axial compressor [J]. Journal of Xi'an Jiaotong University, 2023(3): 129-138.

MOORE R D, REID L. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05 [EB/OL].(1980-04-01)[2022-09-01]. https://ntrs.nasa.gov/citations/ 19800012840.

SUDER K L. NASA's role in gas turbine technology development: accelerating technical progress via collaboration between academia, industry, and government agencies [J]. Journal of Turbomachinery, 2021, 143(1): 011006.

JI Lucheng, TIAN Yong, LI Weiwei, et al. Numerical studies on improving performance of rotor-67 by blended blade and endwall technique [C]//ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. New York, NY, USA: ASME, 2012: 135-145.

赵选民. 试验设计方法 [M]. 北京: 科学出版社, 2006: 169-179.

王广, 楚武利, 张皓光, 等. 端壁合成射流激励参数变化对跨声速轴流压气机性能的影响 [J]. 西安交通大学学报, 2021, 55(5): 193-202.

WANG Guang, CHU Wuli, ZHANG Haoguang, et al. Effects of the endwall synthetic jet excitation parameters on performance of transonic axial flow compressor [J]. Journal of Xi'an Jiaotong University, 2021, 55(5): 193-202.

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