某涡扇发动机高压涡轮盘螺栓孔低循环疲劳模拟件设计

郑小梅; 孙燕涛; 杨兴宇; 肖新红; 廖学军

doi:10.13224/j.cnki.jasp.2018.10.006

某涡扇发动机高压涡轮盘螺栓孔低循环疲劳模拟件设计

doi: 10.13224/j.cnki.jasp.2018.10.006

1.
北京航空工程技术研究中心，北京 100076
2.
中国航空发动机集团有限公司湖南动力机械研究所，湖南株洲 412002

计量
- 文章访问数: 814
- HTML浏览量: 10
- PDF量: 691
- 被引次数: 0
出版历程
- 收稿日期: 2017-05-17
- 刊出日期: 2018-10-28

Design of low cycle fatigue simulating specimen for bolt holes of a turbofan engine high pressure turbine disc

摘要

摘要: 以拉伸应变能寿命预测模型为理论基础，提出了低循环疲劳模拟试验件(简称模拟件)设计的基本准则。针对某涡扇发动机高压涡轮盘螺栓孔部位进行了模拟件优化设计，设计时综合考虑了试验器能力、螺纹连接强度和所需毛坯盘数量等限制因素。优化目标为模拟件与螺栓孔虚拟裂纹0.8mm内第一主应力和第一主应变分布一致，以及最大应力点第二主应力与第一主应力比值一致。对设计结果进行了弹塑性校核。采用该模拟件构型进行了试验研究，由模拟件试验数据得到的安全寿命和轮盘试验给出的安全寿命的差距为4.48%。
- 涡扇发动机 /
- 高压涡轮盘 /
- 螺栓孔 /
- 模拟件 /
- 低循环疲劳 /
- 安全寿命
Abstract: Basic criterion of low cycle fatigue simulating specimen design was proposed based on the theory of tensile strain energy life prediction model. Simulating specimen for bolt holes of a turbofan engine high pressure turbine disc was optimized in design while comprehensively considering the ability of the test machine, thread connection strength and required number of bank disc. The optimizing objectives were as follows: the distribution of the first principal stress and strain within 0.8mm on the virtuak crack of the simulating specimen was consistent with the real bolt holes, and the ratio of the second principal stress to the first principal stress at the maximum stress point of the simulating specimen was consistent with the real bolt holes. Elastic plastic analysis was conducted to check the stress/strain consistency. The difference between safe life obtained by simulating specimen test and real turbine disc test was 4.48%.
- turbofan engine /
- high pressure turbine disc /
- bolt hole /
- simulating specimen /
- low cycle fatigue /
- safe life

HTML

参考文献(20)

[1]	陈传尧.疲劳与断裂［M］.武汉:华中科技大学出版社,2002.
[2]	姚卫星.结构疲劳寿命分析［M］.北京:国防工业出版社,2003.
[3]	谢济洲.低循环疲劳［M］.北京:能源出版社,1990.
[4]	黄致建,朱如鹏,潘升材.单向加载疲劳机上燕尾形榫联接微动损伤试验件设计［J］.航空学报,1994,15(8):1017-1023.HUANG Zhijian,ZHU Rupeng,PAN Shengcai.The design of the speciman of dovetail joint in unidirectionlly-loaded fatigue testing rig［J］.Acta Aeronautica et Astronautica Sinica,1994,15(8):1017-1023.(in Chinese)
[5]	叶彬,姚卫星.飞机结构细节疲劳寿命的应力场强法探析［J］.洪都科技，2001（4）：14-18.YE Bin,YAO Weixing.Stress field intensity method analysis on fatigue life of aircraft structure detail［J］.Hongdu Science and Technology,2001(4):14-18.(in Chinese)
[6]	赵福星,杨兴宇.发动机构件低循环疲劳模拟试验件设计方法［J］.燃气涡轮试验与研究,2003,16(2):58-62.ZHAO Fuxing,YANG Xingyu.A design method of simulation samples for aero-engine components used in low cycle fatigue test［J］.Gas Turbine Experiment and Research,2003,16(2):58-62.(in Chinese)
[7]	杨兴宇,董立伟,耿中行,等.某压气机轮盘榫槽低循环疲劳模拟件设计与试验［J］.航空动力学报,2008,23(10):1829-1834.YANG Xingyu,DONG Liwei,GENG Zhongxing,et al.Design and experimentation of simulation specimen for aero-engine compressor disk slot used in low cycle fatigue test［J］.Journal of Aerospace Power,2008,23(10):1829-1834.(in Chinese)
[8]	陆山,王春光,陈军.任意最大应力梯度路径轮盘模拟件设计方法［J］.航空动力学报,2010,25(9):2000-2005.LU Shan,WANG Chunguang,CHEN Jun.Design method of imitation specimen for engine disk with any maximum stress gradient path［J］.Journal of Aerospace Power,2010,25(9):2000-2005.(in Chinese)
[9]	闫晓军,聂景旭.涡轮叶片疲劳［M］.北京：科学出版社，2013.
[10]	李莉.榫槽模拟件优化设计的理论和方法研究［D］.沈阳:东北大学,2006.LI Li.Research on theory and method of optimal design of simulative tenon-grooves test sample［D］.Shenyang:Northeastern University,2006.(in Chinese)
[11]	RUIZ C,BODDINGTON P H B,CHEN K C.An investigation of fatigue and fretting in a dovetail joint［J］.Experimental Mechanics,1984,24(3):208-217.
[12]	Ministry of Defence.General specification for aircraft gas turbine engines：Defence Standard 00-971［S］.London:Ministry of Defence,1987.
[13]	Ministry of Defence.Design and airworthiness requirements for service aircraft:Part 11 engines:Defence Standard 00-970［S］.London:Ministry of Defence, 2006.
[14]	单辉祖.材料力学:Ⅰ［M］.北京:高等教育出版社,1999.
[15]	《工程材料实用手册》编辑委员会.工程材料实用手册:变形高温合金、铸造高温合金［M］.北京:中国标准出版社,1989.
[16]	苏清友.航空涡喷\\涡扇发动机主要零部件定寿指南［M］.北京:航空工业出版社,2004.
[17]	中国航空工业总公司.金属材料轴向加载疲劳试验方法：HB 5287-1996［S］.北京:中国航空工业总公司,1996.
[18]	中国航空工业第一集团公司.金属材料轴向等幅低循环疲劳试验方法：GB/T 15248-2008［S］.北京:中国标准出版社,2008.
[19]	高镇同,蒋新桐,熊峻江,等.疲劳性能试验设计和数据处理:直升机金属材料疲劳性能可靠性手册［M］.北京:北京航空航天大学出版社,1999.
[20]	北京航空材料研究所.航空发动机设计用材料数据手册［M］.北京:中国航空发动机总公司,1990.