涡轮复杂气冷叶盘结构变形分析模型简化方法

申秀丽; 薛园园; 胡延青; 张野

doi:10.13224/j.cnki.jasp.2017.07.023

涡轮复杂气冷叶盘结构变形分析模型简化方法

doi: 10.13224/j.cnki.jasp.2017.07.023

1.
北京航空航天大学能源与动力工程学院，北京 100191；先进航空发动机协同创新中心，北京100191；北京航空航天大学航空发动机结构强度北京市重点实验室，北京100191
2.
雪城大学工程与计算机学院，美国锡拉丘兹市 13204
3.
中国航空发动机集团有限公司商用航空发动机有限责任公司，上海 200241

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出版历程
- 收稿日期: 2015-10-28
- 刊出日期: 2017-07-28

Simplification method of complex air cooling bladed disk structure’s deformation analysis model

摘要

摘要: 基于高压转子开展高压(HP)涡轮转子叶片叶尖变形分析可提高叶尖间隙的数值模拟精度，而高压涡轮转子叶片由于其复杂的气冷结构，有限元分析网格数量巨大；叶片和轮盘的榫接结构属于非线性分析，也需要足够的计算机时。针对该问题提出了一种复杂气冷叶片的简化方法和榫接结构接触计算简化方法，在不影响计算精度的前提下提高计算效率。采用该方法对典型结构高压涡轮转子进行了变形分析，与采用复杂气冷叶片模型和接触分析方法的变形分析结果进行比较。结果表明：涡轮叶片叶尖最大径向变形相对误差为0.47%，计算机时减少99%，证明简化方法和计算方法的有效性。
- 涡轮部件 /
- 变形分析 /
- 涡轮复杂气冷叶片 /
- 榫接接触分析 /
- 简化方法
Abstract: Tip deformation analysis of high pressure (HP) turbine rotor based on the HP rotor can improve the tip clearance numerical simulation precision. Due to the complex air cooling structure of HP turbine rotor blade, the number of finite element mesh is huge. The mortise structure analysis of HP turbine blade and disk belongs to nonlinear analysis, which also needs enough calculation time. A simplified method of complex air cooling blade model and mortise structure contact analysis model was presented, the calculation efficiency was improved under the premise of without affecting the calculation accuracy. Applying this method to an aero-engine turbine components deformation analysis, the results were compared with the deformation analysis results of the original complex blade model. The relative error of the largest turbine blade tip radial deformation was 0.47%, and the calculation time reduced 99%. Its proven that the simplified method and the calculation method are feasible.
- turbine components /
- deformation analysis /
- complex air cooling blade of turbine /
- mortise structure contact analysis /
- simply method

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