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| 航空发动机真实机匣的包容性试验 | |
| 引用本文： | 范志强,高德平,覃志贤,王维,纪永汉.航空发动机真实机匣的包容性试验[J].航空动力学报,2007,22(1):18-22. |
| 作者姓名： | 范志强 高德平 覃志贤 王维 纪永汉 |
| 作者单位： | 1. 南京航空航天大学,能源与动力学院,江苏,南京,210016;中国燃气涡轮研究院,四川,成都,610500 2. 南京航空航天大学,能源与动力学院,江苏,南京,210016 3. 中国燃气涡轮研究院,四川,成都,610500 4. 空军驻成都发动机集团公司军事代表室,四川,成都,610067 |
| 摘 要： | 为了研究某发动机机匣的包容性,在旋转试验器上进行了该机匣的包容性试验.试验考虑了相邻叶片的影响,得到了叶片断裂甩出时的转速、断叶撞击机匣的应变响应和断叶撞击机匣过程的高速摄影照片.试验结果表明,断叶与机匣碰撞了两次,第2次撞击时在未断叶片作用下断叶击穿机匣,机匣的失效模式主要是剪切破坏.采用包容曲线法对机匣的包容性进行了计算,计算结果与试验结果吻合良好.研究结果对航空发动机机匣的包容性设计有一定的参考价值. |
| 关 键 词： | 航空、航天推进系统 航空发动机 机匣 叶片 包容性 应变响应 航空发动机机匣 包容性 试验器 containment real study 价值 设计 计算 曲线法 剪切破坏 失效模式 击穿 作用 断叶片 碰撞 结果 摄影照片 过程 应变响应 |
| 文章编号： | 1000-8055(2007)01-0018-05 |
| 收稿时间： | 2005/10/21 0:00:00 |
| 修稿时间： | 2005年10月21 |
Experimental study of real casing containment |
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| FAN Zhi-qiang,GAO De-ping,QIN Zhi-xian,WAN Wei and JI Yong-han.Experimental study of real casing containment[J].Journal of Aerospace Power,2007,22(1):18-22. | |
| Authors: | FAN Zhi-qiang GAO De-ping QIN Zhi-xian WAN Wei and JI Yong-han |
| Affiliation: | College of Energy and Power Engineering, Nanjing U niver sit y of Aero nautics andA st ro nautics, Nanjing 210016, China;China Gas Turbine Establishment, Chengdu 610500, China;College of Energy and Power Engineering, Nanjing U niver sit y of Aero nautics andA st ro nautics, Nanjing 210016, China;China Gas Turbine Establishment, Chengdu 610500, China;China Gas Turbine Establishment, Chengdu 610500, China;Air Fo rce Plant Rep resentative Office ofChengdu Engine(Gro up)Co.L t d., Chengdu 610067, China) |
| Abstract: | In order to investigate an engine casing containment,a casing containment test has been carried out in a spin facility.In this test,interference between adjacent blades has been considered.The rotational speed when the broken blade flings out,and the strain responses of the casing as the broken blade impacts on the casing are described in the paper.At the same time,the impacting process is recorded on the film by a hi-speed camera.The released blade exerted two impacts one after another on the casing.The casing has been broken through at the second impact.The casing is destroyed by shear stress.The casing containment has been calculated using containment-curve methods,and the results are in good agreement with the test results.The study can be used as a reference for the engine casing containment design. |
| Keywords: | aerospace propulsion system aero-engine casing blade containment strain responses |
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