概念设计时影响涡轮转子叶片强度的关键因素

杨晓光; 胡晓安; 石多奇; 王井科; 黄佳

概念设计时影响涡轮转子叶片强度的关键因素

1.
北京航空航天大学能源与动力工程学院,北京 100191
2.
空军装备研究院装备总体论证研究所,北京 100076

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出版历程
- 收稿日期: 2012-02-12
- 刊出日期: 2012-10-28

Strength considerations for concept design of turbine blade

1.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China
2.
Equipment Demonstration and Research Institute, Air Force Equipment Academy,Beijing 100076,China

摘要

摘要: 基于总体结构参数对后期详细设计的重要性这一事实,探讨了航空发动机叶片概念设计中可能出现的强度问题,研究了涡轮叶片的 AN²值、轮缘切线速度、叶片稠度和材料性能等重要设计参数对强度和寿命的影响.结果表明:目前先进民用大涵道比涡扇发动机的 AN²值在25m²·(r/min)²以内,轮缘切线速度应当使得涡轮盘的形状因子控制在2以内,叶片稠度则应满足叶片能被榫连结构包容的要求,材料蠕变和低循环疲劳性能的限制要求高压涡轮叶片根部平均应力控制在250MPa左右.这些结果将为先进航空发动机和燃气轮机涡轮叶片的设计提供重要的参考依据.
- 概念设计 /
- 涡轮叶片 /
- 低循环疲劳 /
- 蠕变 /
- 强度和寿命 /
- 准则
Abstract: Based on the importance of overall parameters for the subsequent detailed design,the potential problems of the strength in the concept design phase was investigated,then the effects of design parameters,such as AN²,wheel speed,solidity of blade and performance of the materials,on strength and life were studied.The results show that the values of AN² for the advanced turbofan aero-engine are within 25m²·(r/min)² ,the wheel speed is related to disc shape factor which must be designed with 2,the solidity must be designed to satisfy the strength of the fir-tree,and stress at the root of the blade must be defined within 250MPa to avoid failure from LCF(low cycle fatigue) and creep.These results would be useful for the turbine blade design of advanced aircraft engines and gas turbines.
- concept design /
- turbine blade /
- low cycle fatigue /
- creep /
- strength and life /
- criterion

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参考文献(17)

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