An Aircraft Engine Using The Load On Its Whole Life And Reliability Study

Accuratly the analysis of stress and life for aircraft engines need reasonable, highlyreliable load analysis. A reasonable load spectrum of the engine is very important to theprimary work of design an engine, have a significant impact on the success of thesubsequent reliability analysis and testing work. Aero-engine technology is a priority tothe development of a world military power and a high degree of monopoly and tightblockade of key technologies, an important marker of the military level of a nationalequipment and technology industrial strength and comprehensive national strength.Therefore, the aero-engines’ load spectrum and data processing technology, hasimportant theoretical value and prospects of significant engineering applications toimprove the structural strength of engine and spare parts and lifetime reliability.The engines include a large number of components; reliability of the enginedepends upon the reliability on the basis of the cell body (parts). Components each withits own characteristics and the reliability index, and only when the component reliabilitycan be achieved, the reliability of engine can be guaranteed and achieved. The reliabilityof engine is very difficult to estimate due to its complexcity. In order to study the life ofthe engine and its reliability, we must first find out the ctitical components or weakcomponents of the engine to determine the failure mode of these components in use inthe repair process. And then study the impact of these failure modes, differences instatistical load spectrum formation and development of the degree of influence of thesefaults, thus revealing the impact of difference in the engines’ load spectrum on its lifeand reliability.In this thesis, it took the complexity of the engine load spectrum and its structureinto account, and discussed the scope of application of the various life reliabilitymathematical model to determine load spectra and load distribution function on thebasis of the analysis, the finalization of engine life and reliable in mathematical model.Engine flight hours and the number of rotor cycle were used to determine therelationship between the load and the major components of life, by using thedistribution function and the generalized stress-strength interference model to calculate the life of a certain reliability and inspection cycle.