高涵道比涡扇发动机结构与力学性能定量评估

彭刚; 朱彬; 张大义; 洪杰

doi:10.13224/j.cnki.jasp.2017.07.025

高涵道比涡扇发动机结构与力学性能定量评估

doi: 10.13224/j.cnki.jasp.2017.07.025

1.
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 201108
2.
北京航空航天大学能源与动力工程学院，北京 100191
3.
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

基金项目: 国家自然科学基金（51575022，51475021）

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出版历程
- 收稿日期: 2016-11-16
- 刊出日期: 2017-07-28

Quantitative evaluation for the structure and mechanics properties of the high bypass ratio turbofan engines

摘要

摘要: 针对高涵道比涡扇发动机结构设计需求，提出转子系统、承力系统和整机的结构效率评估参数，建立了结构设计参数与力学特征参数之间的联系。典型发动机评估结果表明：受大尺寸风扇限制，高涵道比涡扇发动机低压转子系统的平均应力系数在0.2~0.3之间，低于其他类型的航空燃气涡轮发动机。在工作转速范围内，低压转子不可避免地存在弯曲型临界转速，须将转子连接结构设计在低应变能区域。机动飞行中，整机的转静间隙值变化范围为［-1.4,1.0］mm，低压涡轮是间隙控制的重点位置。
- 涡扇发动机 /
- 高涵道比 /
- 结构设计 /
- 力学性能 /
- 结构效率 /
- 定量评估
Abstract: The structural efficiency parameters for the rotor system, supporting system and whole engine were put forward respectively according to the structure design requirements of the high bypass ratio turbofan engine, and the relations between the structural design parameters and the mechanics property parameters were established. The evaluation results for one typical engine exhibited that the average stress coefficients for the low pressure rotor of the high bypass ratio turbofan engine were between 0.2 and 0.3, lower than those of the other types of aero gas turbo engines because of the particularly large size of the fan. There were several unavoidable critical speeds with bending modes within the operation speed range, therefore the location of the joint structures of the rotor should be designed into the low stain energy zone. During maneuvering, the interval for the clearance between the stator and the rotor was ［-1.4,1.0］mm for the whole engine, and the low pressure turbine was the key position for the clearance control.
- turbofan engine /
- high bypass ratio /
- structure design /
- mechanics property /
- structural efficiency /
- quantitative evaluation

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