Abstract
Current civil aviation is characterized by rising cost and competitive pressure, which is partly passed to the MRO (Maintenance, Repair and Overhaul) companies. To improve the maintenance, condition-based maintenance is established, which is characterized by tailored maintenance actions for each part of the jet engine, depending on the individual engine history and operating conditions. Thereby, prediction models help engineers to authorize maintenance actions as effectively as possible. This paper will help to improve these prediction models. Therefore, the influence of specific deterioration of a high pressure compressor (HPC) to jet engine performance parameters such as exhaust gas temperature (EGT) and specific fuel consumption (SFC) will be investigated. For this purpose, computational fluid dynamic (CFD) calculations of deteriorated HPC geometries are carried out and serve as a basis to scale the reference HPC performance characteristics to deteriorated ones. To evaluate the changes in performance parameters, a modular performance synthesis model is set up. In this model, the HPC map is exchanged with deteriorated ones. As a result, the influence of geometric deviations to the design intent can be determined, and the MRO companies are able to focus on the most relevant sections of the compressor blading.
Highlights
During operation of a jet engine, deterioration occurs and continually reduces the engine performance
This paper focuses on modified front and rear stages of the high pressure compressor (HPC)
For evaluating the impact of modified stage geometries to the engine performance parameters, the HPC map of the modular performance synthesis model was replaced by the scaled ones
Summary
During operation of a jet engine, deterioration occurs and continually reduces the engine performance. Power 2018, 3, 15 repair and rearrange the blading in such that the customer demands for the planned operation are met as cost-effectively as possible, while respecting the given limits of the Engine Manual (EM). More than two complete rotor bladings of operated jet engines [1] and 40 stator vanes for each of the analyzed HPC stages have been digitized by a structured light 3D-scanner in conjunction with a photogrammetric system. To analyze the impact of deteriorated HPC bladings, the geometric parameters of front and rear stages of the HPC are modified and implemented in a full HPC model. It is possible to identify the more relevant HPC stage in order to predict the possible performance range (by repairing the stage) and to analyze the interactions between the engine components
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