Improved algorithm of flight conversion ratio for aero-engine based on probability

LI Hong-wei; YE Bin; CAI Na

Chinese

您当前的位置：

首页 >

文章列表页 >

Improved algorithm of flight conversion ratio for aero-engine based on probability

更新时间：2026-07-07

- Improved algorithm of flight conversion ratio for aero-engine based on probability
- Issue 5, (2014)
- 作者机构：
  
  海军航空工程学院青岛校区航空机械系,山东,青岛,266041
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
LI Hong-wei, YE Bin, CAI Na. Improved algorithm of flight conversion ratio for aero-engine based on probability[J]. 2014, (5).
DOI：

LI Hong-wei, YE Bin, CAI Na. Improved algorithm of flight conversion ratio for aero-engine based on probability[J]. 2014, (5). DOI：

摘要

针对斯贝MK202发动机应力标准对零部件工作寿命评定中未包含各种随机因素的影响，考虑零部件疲劳性能参数的分散性和发动机整机载荷谱的随机性，将实测数据统计分析、零部件应力有限元分析以及蒙特卡罗模拟分析有机结合，提出了基于概率的航空发动机飞行换算率改进算法，以解释航空发动机零部件实际工作寿命存在的差异.经范例验证表明：确定性寿命评定方法的飞行换算率计算结果与改进算法下的平均值相当；对于单次飞行换算率，改进算法的单次飞行换算率平均值比确定性方法的计算结果小2%；对于综合飞行换算率，改进算法的综合飞行换算率平均值比确定性方法的结果小1%；且在改进算法下单次飞行换算率和综合飞行换算率服从正态分布.

Abstract

For SPEY MK202 engine

the stress standard evaluation methods fail to contain various random factors. In order to explain the differences in the actual working life of engine component

as well as the dispersion of the fatigue characteristic parameters of component and the randomness of the whole engine load spectrum

statistical analysis of measured data

finite element analysis of stress and Monte Carlo simulations of component were combined to put forward the improved algorithm of flight conversion ratio for aero-engine based on probability. Actual example shows: the flight conversion ratio of ascertainable method for life assessment is the average value of the improved algorithm; for a single flight conversion rate

the average conversion rate of improved algorithm is 2% smaller than that of ascertainable method; for comprehensive flight conversion rate

the average conversion rate of improved algorithm is 1% smaller than that of ascertainable method; and the single fight conversion rate and comprehensive flight conversion ratio of improved algorithin are in normal distribution.

关键词

Keywords

references

Views

889

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical analysis on residual stress of foreign object damage on the leading edge of titanium alloy blade

Numerical simulation on seal-rotor system with airflow induced vibration

Numerical investigation of composite fan blade vibration characteristics due to blade-casing rub

Test method for the combined high and low cycle fatigues of turbine blade based on the whole engine operation

Bearing pedestal looseness dynamic model of dual rotor system and fault feature

Related Author

ZHAO Zhenhua

ZHANG Junhe

WANG Lingfeng

罗跃纲

王鹏飞

徐昊

王晨勇

贾海峰

Related Institution

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

先进航空发动机协同创新中心

上海交通大学机械与动力工程学院

中国航空发动机集团有限公司中国航空发动机研究院

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰