采用样条曲面非轴对称端壁成型的高压涡轮动叶气动优化

王杰; 王政; 欧阳玉清; 陶志; 宋立明; 李军

doi:10.7652/xjtuxb202403004

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采用样条曲面非轴对称端壁成型的高压涡轮动叶气动优化

—————————————————————— | 更新时间：2025-07-09

- 采用样条曲面非轴对称端壁成型的高压涡轮动叶气动优化
- Aerodynamic Optimization of High Pressure Turbine Rotor Using Spline Surface Non-Axisymmetric Endwall Profiling
- 西安交通大学学报 2024年58卷第3期页码：38-48
- 作者机构：
  
  1. 西安交通大学能源与动力工程学院,西安,710049
  2. 中国航发湖南动力机械研究所,湖南,株洲,412002
- 作者简介：
  
  : 2023-10-11。作者简介: 王杰(1997—),男,博士生
  宋立明(通信作者),男,教授,博士生导师。基金项目: 国家科技重大专项资助项目(2019-Ⅱ-0008-0028)。
- 基金信息：
  
  : 2023-10-11。作者简介: 王杰(1997—),男,博士生;宋立明(通信作者),男,教授,博士生导师。基金项目: 国家科技重大专项资助项目(2019-Ⅱ-0008-0028)。
- DOI：10.7652/xjtuxb202403004
  中图分类号： TK471
- 网络首发：2024-03-10，
  
  纸质出版：2024
- 稿件说明：
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王杰, 王政, 欧阳玉清, 等. 采用样条曲面非轴对称端壁成型的高压涡轮动叶气动优化[J]. 西安交通大学学报, 2024,58(3):38-48.

WANG Jie, WANG Zheng, OUYANG Yuqing, et al. Aerodynamic Optimization of High Pressure Turbine Rotor Using Spline Surface Non-Axisymmetric Endwall Profiling[J]. 2024, 58(3): 38-48.
王杰, 王政, 欧阳玉清, 等. 采用样条曲面非轴对称端壁成型的高压涡轮动叶气动优化[J]. 西安交通大学学报, 2024,58(3):38-48. DOI： 10.7652/xjtuxb202403004.

WANG Jie, WANG Zheng, OUYANG Yuqing, et al. Aerodynamic Optimization of High Pressure Turbine Rotor Using Spline Surface Non-Axisymmetric Endwall Profiling[J]. 2024, 58(3): 38-48. DOI： 10.7652/xjtuxb202403004.

摘要

为了提升高负荷涡轮级的气动效率

发展了基于样条曲面的非轴对称端壁造型方法。以该参数化造型方法为基础

结合高效智能优化算法和经过校核的数值仿真方法

建立了涡轮非轴对称端壁设计优化平台

并以某小展弦比高压涡轮级为研究对象

以效率为优化目标

以流量为约束条件

在级环境和发动机工况下开展了非轴对称端壁优化设计。结果表明:优化设计后的涡轮动叶相对于参考设计

涡轮级的总总效率提升0.26%; 非轴对称端壁造型改变了动叶下端壁附近的压力分布

动叶吸力面侧压力系数相对于参考设计显著提升

这降低了动叶叶片通道内的横向压力梯度

抑制了通道中的二次流动; 非轴对称端壁造型改变了叶片通道中的涡系结构

相对于参考设计

非轴对称端壁造型使得马蹄涡压力面分支在叶片通道内部沿着叶片压力面迁移

在靠近通道出口的位置才汇入通道涡

这削弱了通道涡的强度

进而降低了气动损失

提高了涡轮级效率。

Abstract

To enhance the aerodynamic efficiency of high-load turbine stages

a spline surface-based non-axisymmetric endwall profiling method is developed. Based on this parametric profiling method

combined with efficient intelligent optimization algorithms and validated numerical simulation techniques

an optimization framework for designing non-axisymmetric endwalls in turbines is established. Taking a high-pressure turbine stage with a low aspect ratio as the study object

with efficiency as the optimization objective and the mass flow rate as a constraint condition

the non-axisymmetric endwall optimization design is conducted under the stage environment and engine operating conditions. The results show that compared with the reference design

the total efficiency of the turbine stage is increased by 0.26% after the optimization design. The non-axisymmetric endwall changes the pressure distribution near the lower endwall of the rotor blade

and the pressure coefficient at the suction side of the rotor blade is significantly improved compared with the reference design. This reduces the lateral pressure gradient in the blade passage and suppresses the secondary flow in the passage. The non-axisymmetric endwall changes the vortex system structure in the blade passage. Compared to the reference design

the non-axisymmetric endwall causes the horseshoe vortex's pressure side leg to migrate along the pressure side in the blade passage before merging into the passage vortex near the passage outlet. This lowers the intensity of the passage vortex

which then reduces aerodynamic losses and improves turbine stage efficiency.

关键词

Keywords

references

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