综合考虑罩量和冷热态关系的叶片优化方法

叶文明; 陈帝云; 李世峰; 赵姝帆; 王国良; 邱名

doi:10.13224/j.cnki.jasp.20240297

综合考虑罩量和冷热态关系的叶片优化方法

doi: 10.13224/j.cnki.jasp.20240297

中国空气动力研究与发展中心空天技术研究所，四川绵阳 621011

详细信息

作者简介:
叶文明（1990-），男，助理研究员，博士，研究方向为航空发动机结构设计及分析。E-mail：892088464@qq.com

中图分类号: V232.4
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- 文章访问数: 800
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- 被引次数: 0
出版历程
- 收稿日期: 2024-05-11
- 网络出版日期: 2025-11-15

Blade optimization method considering the gravity center tilting and hot-to-cold relationship

Aerospace Technology Institute，China Aerodynamics Research and Development Center，Mianyang Sichuan 621011，China

摘要

摘要:
为解决传统罩量调整和冷热态换算方法可能会导致的冷态叶型强度储备等性能偏离设计指标的问题，提出了一种将叶片罩量调节和冷热态换算结合的优化方法。该方法包含罩量调整和冷热态叶型换算两个小循环以及一个大循环，其中，罩量调整和冷热态换算的核心思想分别为基于叶片变形规律的重心修正和基于关键数据点变形的坐标换算，此外，大外循环以冷态叶型的分析结果作为优化目标、罩量调整的结束判据作为优化变量。结合UG自动建模、ANSYS二次开发以及iSIGHT集成平台等实现了叶片罩量和冷热态换算的优化过程。某型压气机一级转子叶片的优化实例表明：采用所提出的方法进行叶片优化能够确保热态叶型与目标叶型重合，同时使冷态叶型最大应力下降47%。
- 叶片优化 /
- 罩量调节 /
- 冷热态换算 /
- 二次开发 /
- 自动建模
Abstract:
To solve the problem that the cold blade profile strength reserve and other performance deviate from the design index caused by the traditional gravity center tilting and hot-to-cold transformation methods, an optimization method combining gravity center tilting and hot-to-cold transformation was proposed. The core ideas of gravity center tilting and hot-to-cold transformation included the center of gravity correction based on the blade deformation law and the coordinate conversion based on the deformation of key data points, respectively. Combined with UG automatic modeling, ANSYS secondary development and iSIGHT integrated platform, the optimization process of gravity center tilting and hot-to-cold transformation was realized. The optimization example of a first-stage rotor blade showed that the maximum stress of the cold blade was respectively reduced 47% by the proposed method when the hot blade profile coincided with the target blade profile.
- blade optimization /
- gravity center tilting /
- hot-to-cold transformation /
- secondary development /
- automatic modeling

HTML

图 1 简化后数据建立的叶片与原始叶片对比

Figure 1. Comparison of simplified data blade and original blade

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图 2 叶片结构优化流程

Figure 2. Blade structure optimization process

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图 3 基于iSIGHT的叶片优化流程

Figure 3. Blade optimization process based on iSIGHT

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图 4 叶片气动载荷下压力分布

Figure 4. Pressure distribution of aerodynamic load

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图 5 气动设计叶片应力分布

Figure 5. Stress distribution of aerodynamic design blade

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图 6 目标叶型与初始叶型对比

Figure 6. Comparison between target blade and initial blade

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图 7 目标叶型、冷态叶型和热态叶型对比

Figure 7. Comparison of target blade, cold blade and hot blade

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图 8 冷态叶型变形后的应力分布

Figure 8. Stress distribution of deformed cold blade

下载: 全尺寸图片幻灯片

表 1 某型压气机叶片计算参数

Table 1. Calculation parameters of a certain type of compressor blade

材料弹性模量E/
10⁵ MPa 泊松比
μ 密度ρ/
10⁻³ （kg/cm³）转速ν/
（r/min）

TC11 1.16 0.33 4.48 32500

下载: 导出CSV

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