刘国库1,尤宏德2,周丽敏2,迟庆新2.基于系统工程的高压涡轮叶片内腔渗层正向设计[J].航空发动机,2022,48(5):80-87
基于系统工程的高压涡轮叶片内腔渗层正向设计
Design of Inner Cavity Infiltration Layer of High-pressure Turbine Blade Based on System Engineering Theory
  
DOI:
中文关键词:  系统工程  热腐蚀  涡轮叶片  低周疲劳  高周疲劳  航空发动机
英文关键词:system engineering  hot corrosion  turbine blade  low cycle fatigue  high cycle fatigue  aeroengine
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作者单位E-mail
刘国库1,尤宏德2,周丽敏2,迟庆新2 1.海装沈阳局驻沈阳地区某军事代表室沈阳1100812.中国航发沈阳发动机研究所沈阳110015 24712333@qq.com 
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中文摘要:
      为了解决涡轮叶片内腔渗层设计过程中需求分析不全面、设计确认不充分、设计验证不完整等问题,提出基于系统工程 理论的方法,对舰用燃气轮机高压涡轮工作叶片内腔渗层进行正向设计研发。应用需求分析-技术方案设计-试样验证-产品实 施-产品集成-产品验证的技术路线,开展了涡轮叶片内腔渗层技术研究。通过拉伸性能试验、低周疲劳试验、高周疲劳试验、燃气 热腐蚀试验、工艺试验等对多方案进行验证,优筛选出的内腔CoAl薄渗层和纯Al薄渗层为最佳方案。结果表明:验证方案合理可 行,渗层能够满足发动机的使用需求。基于系统工程的涡轮叶片内腔渗层设计方法从整体需求出发,设计、验证具有系统性和完 整性,在叶片内腔渗层设计过程中具有重要作用。
英文摘要:
      In order to solve the problems such as incomplete requirement analysis,insufficient design validation and incomplete design verification in the design process of the inner cavity infiltration layer of turbine blades,a method based on system engineering theory was proposed to conduct forward design and development of the inner cavity infiltration layer of marine gas turbine high-pressure turbine blades. Following the technical route of requirement analysis,concept design,prototype verification,product implementation,product inte? gration and product verification,the research on the technology of turbine blade inner cavity infiltration layer was carried out. A number of alternatives were verified by tensile test,low cycle fatigue test,high cycle fatigue test,hot gas corrosion test,process test,etc. CoAl thin layer and pure Al thin layer were the best solutions. The results show that the verification process is reasonable and feasible,and engine re? quirements for the infiltration layer is satisfied. Considering the overall requirements from the beginning,the design method based on sys? tem engineering is systematic and complete,which plays an important role in the process of blade inner cavity infiltration layer design.
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