Assessment parameters and calculation methods of structural efficiency on rotor system in aero engine

MA Yan-hong; CHEN Lu-lu; ZHANG Da-yi; HONG Jie

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Assessment parameters and calculation methods of structural efficiency on rotor system in aero engine

更新时间：2026-07-07

- Assessment parameters and calculation methods of structural efficiency on rotor system in aero engine
- Vol. 28, Issue 7, (2013)
- 作者机构：
  
  1. 北京航空航天大学能源与动力工程学院,北京,100191
  2. 中国航空工业集团公司中航商用发动机有限责任公司,上海,200241
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2013
- 稿件说明：
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MA Yan-hong, CHEN Lu-lu, ZHANG Da-yi, et al. Assessment parameters and calculation methods of structural efficiency on rotor system in aero engine[J]. 2013, 28(7).
DOI：

MA Yan-hong, CHEN Lu-lu, ZHANG Da-yi, et al. Assessment parameters and calculation methods of structural efficiency on rotor system in aero engine[J]. 2013, 28(7). DOI：

摘要

根据航空发动机转子系统的结构特征和力学特征

提出了从结构的承载能力、抗变形能力和动力学环境适应能力3个方面进行结构效率评估的参数体系及其计算方法

并以典型小涵道比涡扇发动机转子系统为例进行了结构效率评估参数的计算分析.研究表明:平均应力系数、等效比刚度、极限惯性载荷作用下最大变形量、无量纲M-H因子和弯曲应变能系数等作为评估航空发动机转子系统结构效率的评估参数能够有效地反映各种载荷作用下结构形式和材料性能对应力水平、变形分布以及动力敏感度的影响.同时指出了该发动机转子系统现有结构设计的特点

以及进行结构优化的方向.

Abstract

Based on the structural features and mechanical characteristics of aero engine rotor system

a calculation method and assessment parameters of structural efficiency were proposed.The method includes the bearing capacity

resistance to deformation and dynamic environment adaptability.A structural efficiency assessment on the rotor system of a typical turbofan engine was conducted.The study shows the assessment parameters include the average stress coefficient

the ratio of equivalent stiffness

maximum deformation at ultimate inertia loads

dimensionless M-H factor and the bending strain energy coefficient.Which can reflect the effect of structural style and material property to the stress level

deformation distribution and the power sensitivity under various loads effectively.The features of the structure of the engine rotor system were presented and further optimization was concluded.

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Related Author

MA Yan-hong

WANG Hong

HONG Jie

LIU Yanxu

LIU Baoguo

FENG Wei

MIAO Hui

ZANG Chaoping

Related Institution

School of Energy and Power Engineering, Beijing University of Aeronautics Astronautics

Space Precision Bearing Applications Laboratory, Beijing Institute of Control Engineering

大连民族大学智能感知与先进控制国家民委重点实验室

大连民族大学机电工程学院

中国航空发动机集团有限公司湖南动力机械研究所

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