Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums
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Hong-Zhong Huang
,
Jie Gong
Abstract
Aircraft engine components are subjected to variable amplitude load conditions usually they tend to experience fatigue damage. Many fatigue damage accumulation theories have been put forward to predict the fatigue lives of structure components. Under different load spectra, the aircraft engine has different working life. In this paper, based on the linear damage rule, the fatigue life of an aircraft engine was estimated by considering the load spectrum difference factor. According to one aircraft engine used for different load spectrums, the relationship between the load spectrum and the life is discussed. Moreover, the fatigue life of this engine used in A-type bomber is estimated based on the different load spectrum of the B-type bomber. A good agreement is found between the estimated results and real life data.
©[2012] by Walter de Gruyter Berlin Boston
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Artikel in diesem Heft
- Masthead
- Flow Field around a Blunt-nosed Body with Spike
- The Flow Analysis and Performance Improvement of the Flow Return System in High Pressure Fans
- Numerical Investigation of Heat Transfer Characteristic on Scalelike Platelet Inner Duct
- Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor
- Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums
- Numerical Simulation of Tangling in Jet Engine Turbines
- Statistical Turbofan Architecture Management for Use in a Supercirculation Wing Aircraft
- Calculating High Speed Centrifugal Compressor Performance from Averaged Measurements
- Preliminary Experimental Investigation on Detonation Initiation in the Ejector of a Pulse Detonation Rocket Engine
- An Application of Fuzzy Fault Tree Analysis to Uncontained Events of an Areo-Engine Rotor
