Performance Deterioration of Commercial High-Bypass Ratio Turbofan Engines

Mehalic, C. M.; Ziemianski, J. A.

doi:10.4271/801118

Cited by 2 publications

(1 citation statement)

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“…Erosion and tip rubs introduce changes to the flow path geometry of the compressor, in particular, to the blade profiles and the rotor tip clearances. A study of performance deterioration of commercial high-bypass ratio turbofan engines showed that approximately one half of the long-ttsm deterioration of compressor performance was attributable to increased blade tip clearances, Mehalic and Ziemianski (1980). In helicopter engines the erosion/burring of the first stage blades and blade tip clearance changes were identified as major performance loss mechanisms, Przedpelski (1982).…”

Section: Compressor Degradationmentioning

confidence: 99%

The Effect of Compressor Rotor Tip Crops on Turboshaft Engine Performance

Frith

1992

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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The results from an experimental study into the effect of compressor rotor tip clearance changes on the steady-state performance and stability margins of a free-power turbine turboshaft engine are presented and discussed. This work was directed at the development of methods to diagnose engine condition from gas path measurements. It was found that the normal production suite of engine instrumentation was able to measure the deterioration in engine performance due to the implanted compressor degradation and the resultant deviations in the measured parameters from their respective nominal baselines do provide useful indicators of engine condition.

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Section: Compressor Degradationmentioning

confidence: 99%