Impacts of low-pressure (LP) compressor's deterioration upon an aero-engine's high-pressure (HP) turbine blade's life consumption

被引：0
|
作者：
Naeem, M. [1 ]
机构：
[1] College of Aeronautical Engineering (CAE), National University of Sciences and Technology (NUST), Pakistan
来源：
Aeronautical Journal | 2006年 / 110卷 / 1106期
关键词：
Some in-service deterioration in any mechanical device; such as an aero-engine; is inevitable. As a result of experiencing a deterioration of efficiency and/or mass flow; an aero-engine will automatically adjust to a different set of operating characteristics; thereby frequently resulting in changes of rpm and/or turbine entry temperature in order to provide the same thrust. Rises in the turbine entry-temperatures and the high-pressure turbine's rotational speed result in greater rates of creep and fatigue damage being incurred by the hot-end components and thereby higher engine's life cycle costs. Possessing a better knowledge of the effects of engine deterioration upon the aircraft's performance; as well as fuel and life usages; helps the users to take wiser management decisions and hence achieve improved engine utilisation. For a military aircraft; using a computer performance simulation; the consequences of low-pressure (LP) compressor's deterioration upon an aero-engine high-pressure (HP) turbine blade's life-consumption have been predicted;
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摘要：
Journal article (JA)
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页码：227 / 238
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