Tandem Blading and Flow Mechanism of Last Stator of Multi-Stage Axial Flow Compressor

CHEN Ling; JU Yaping; ZHANG Chuhua

doi:10.7652/xjtuxb202210017

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Tandem Blading and Flow Mechanism of Last Stator of Multi-Stage Axial Flow Compressor

更新时间：2025-07-09

- Tandem Blading and Flow Mechanism of Last Stator of Multi-Stage Axial Flow Compressor
- Vol. 56, Issue 10, Pages: 170-179(2022)
- 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/xjtuxb202210017
  CLC： TK05
- Online First：10 October 2022，
  
  Published：2022
- 稿件说明：
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CHEN Ling, JU Yaping, ZHANG Chuhua. Tandem Blading and Flow Mechanism of Last Stator of Multi-Stage Axial Flow Compressor[J]. 2022, 56(10): 170-179.
DOI：

CHEN Ling, JU Yaping, ZHANG Chuhua. Tandem Blading and Flow Mechanism of Last Stator of Multi-Stage Axial Flow Compressor[J]. 2022, 56(10): 170-179. DOI： 10.7652/xjtuxb202210017.

摘要

针对多级轴流压气机末级静子叶片转折角大、角区分离严重、流动损失显著的问题

以某工业用6.5级轴流压气机末级静子为主要研究对象

提出了一种三维串列叶片几何参数化建模方法

能够实现对串列参数沿叶高分布规律、叶片弯掠等三维特征的灵活控制

以支持单列叶片向串列叶片的改型设计

并结合数值计算方法

开展了末级串列静子改型设计对压气机气动性能及内部流场的影响研究。结果表明:对6.5级轴流压气机

末级静子叶片由单列改为串列后

6.5级压气机设计工况绝热效率提高了0.965%

稳定工况范围有所拓宽; 串列叶片缝隙区射流的流动局部加速作用能够抑制角区分离的周向和径向发展; 相比机匣附近

轮毂附近串列参数的变化对压气机气动性能的影响更为显著

且周向交错度较轴向重叠度的影响更大。研究成果对多级环境下压气机三维串列叶片设计具有参考价值。

Abstract

Currently

the last stator of the multi-stage axial flow compressor is faced with such remarkable problems as large blade turning angle

severe corner separation and significant flow loss. Against this background

we propose a three-dimensional geometrical parameterization method for tandem blades using the last stator of an industrial 6.5-stage axial flow compressor as example. This method enables a flexible control of spanwise distribution of tandem parameters as well as lean and bow of blades

thus supporting the redesign of single blades into tandem blades. Using the numerical methods

we also investigate the impact of tandem blades on the aerodynamic performance and internal flow field of the whole compressor. The following results are obtained: 1)The adiabatic efficiency of the 6.5-stage axial flow compressor increased by 0.965% under the design conditions after the single-blade configuration of the last stator is redesigned into a tandem-blade one

and the operating range was also widened; 2)The local jet-like acceleration in the slit region of the tandem blade is observed to be responsible for the suppression of circumferential and radial development of the corner separation; 3)The tandem parameters at the hub have a greater impact on the aerodynamic performance of the compressor than at the tip

and the percent pitch than the axial overlap. The three-dimensional parametric modeling method for tandem blades proposed in this work and the findings of flow improvement mechanism of three-dimensional tandem blades have reference value for the design optimization of three-dimensional tandem blades.

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references

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