航空发动机综合飞行换算率的确定

为实现国内某型现役军用航空发动机寿命控制与管理，基于实测飞行剖面和任务混频，研究建立了军用航空发动机综合飞行换算率的确定算法和计算流程。考虑温度对材料强度的影响，将应力剖面向同一温度折算，综合应用雨流计数方法、古德曼方法和线性累积损伤方法，加权计算得到了国内某型现役军用航空发动机同时适用于压气机部件和涡轮部件的飞行任务换算率；基于工厂交付试车、部队地面试车、最坏发动机系数和削顶因子等因素，对飞行任务换算率进行修正，计算得到了国内某型现役军用航空发动机综合飞行换算率。工程应用表明，计算得到的综合飞行换算率准确合理，工程适用。

Study on assessment method of comprehensive flight conversion ratio for aero-engine

For the life control and management of some internal military aero engine in the service, based on the flight profile and task frequency mixing, the assessment process of comprehensive flight conversion ratio for aero-engine is established, and the assessment method for aero-engine conversion ratio is presented. Considering the effect of high temperature on the performance of material, the actual stress profile is converted to the stress profile at the same temperature. The rain flow counting method and the Good-man method and the Miner method for linear cumulative damage are all applied to estimate the flight mission conversion ratio of the active service military aero-engine which is applicable both to the compressor and the turbine. Considering the affecting factor such as the trial running for delivery at factory, the trial running under foot, the coefficient for the worst aero-engine and the decapitation factor, the flight mission conversion ratio of the active service military aeroengine is amended and the comprehensive flight conversion ratio of the active service military aero-engine is assessed. The comprehensive flight conversion ratio is applied into the life control and management of the active service military aero-engine. Result shows that the comprehensive flight conversion ratio is correct and reasonable, and is applicable for actual technical application.