多级轴流透平叶片的三维流道一维化优化设计方法

李紫旸; 戚乾刚; 曹培愉; 黄典贵

doi:10.19805/j.cnki.jcspe.2026.240800

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多级轴流透平叶片的三维流道一维化优化设计方法

动力设备与系统 | 更新时间：2026-10-10

- 多级轴流透平叶片的三维流道一维化优化设计方法
- One-dimensional Optimization Design Method of Three-dimensional Flow Channel for Multistage Axial Flow Turbine Blades
- 动力工程学报 2026年46卷第4期页码：39-49,148
- 作者机构：
- 作者简介：
  
  李紫旸(2000—),男,四川西昌人,硕士研究生,研究方向为叶轮机械,E-mail:781213328@qq.com。
- 基金信息：
  
  上海市科学技术委员会资助项目(22010503100)
- DOI：10.19805/j.cnki.jcspe.2026.240800
  中图分类号： TK14
- 纸质出版：2026
- 稿件说明：
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李紫旸, 戚乾刚, 曹培愉, 黄典贵. 多级轴流透平叶片的三维流道一维化优化设计方法[J]. 动力工程学报, 2026, 46(4): 39-49,148.
李紫旸, 戚乾刚, 曹培愉, 黄典贵. 多级轴流透平叶片的三维流道一维化优化设计方法[J]. 动力工程学报, 2026, 46(4): 39-49,148. DOI： 10.19805/j.cnki.jcspe.2026.240800.

DOI： 10.19805/j.cnki.jcspe.2026.240800

摘要

针对现有多级透平设计过程繁琐、设计周期长、经验依赖性强的缺点

基于流量守恒、实际气体模型和一维损失模型

采用内点算法寻优

结合叶型参数化方法

提出了适用于多级透平叶片的三维流道一维化优化设计方法

并搭建对应自动优化设计平台。该方法通过将叶片流道沿径向切分为多个子流道进行单独设计

再结合三维数值模拟结果修正损失模型并进行迭代优化

从而跳过准三维设计步骤并有效减少全三维设计的迭代次数

在缩短设计时间并降低对经验的依赖性的同时获得精准且气动性能优良的设计结果

最后采用某300 MW F级燃气轮机四级透平进行验证。结果表明:利用该方法得到的透平设计结果与三维数值模拟结果基本一致;相比于原型设计

其各透平级动静叶的攻角匹配更优良

叶片扭转程度小

从而显著降低二次流损失

且轮周效率提升0.66百分点

质量流量提升1.24%

轴功提升1.99%。

Abstract

Aiming at disadvantages of existing multistage turbine design

such as a complicated process

long cycle

and strong reliance on experience

a one-dimensional optimization design method suitable for the three-dimensional flow channel of multistage turbine blades was proposed based on flow conservation

a real gas model

and a one-dimensional loss model

using an interior-point algorithm and a blade profile parameterization technique. A corresponding automatic optimization design platform was also developed. The blade channel was divided into several subchannels along the radial direction

and iterative optimization was performed by combining three-dimensional numerical simulation with a modified loss model. By this approach

the quasi-three-dimensional design phase was bypassed

and the number of iterations needed for full three-dimensional design was significantly reduced. Consequently

accurate design results with excellent aerodynamic performance were obtained

while both design time and dependence on prior experience were diminished. Verification was carried out using a 300 MW F-class gas turbine with four turbine stages. The results show that the turbine design obtained with this method is in good agreement with the three-dimensional numerical simulation results. Compared with the prototype design

the angle-of-attack matching between stator and rotor blades in each stage is improved

blade twist is reduced

and secondary flow loss is significantly decreased. As a result

the circumferential efficiency increases by 0.66%

the flow rate rises by 1.24%

and the shaft power improves by 1.99%.

关键词

Keywords

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