Abstract
The decreasing performance of jet engines during operation is a major concern for airlines and maintenance companies. Among other effects, the erosion of high-pressure compressor (HPC) blades is a critical one and leads to a changed aerodynamic behavior, and therefore to a change in performance. The maintenance of BLISKs (blade-integrated-disks) is especially challenging because the blade arrangement cannot be changed and individual blades cannot be replaced. Thus, coupled deteriorated blades have a complex aerodynamic behavior which can have a stronger influence on compressor performance than a conventional HPC. To ensure effective maintenance for BLISKs, the impact of coupled misshaped blades are the key factor. The present study addresses these effects on the aerodynamic performance of a first-stage BLISK of a high-pressure compressor. Therefore, a design of experiments (DoE) is done to identify the geometric properties which lead to a reduction in performance. It is shown that the effect of coupled variances is dependent on the operating point. Based on the DoE analysis, the thickness-related parameters, the stagger angle, and the max. profile camber as coupled parameters are identified as the most important parameters for all operating points.
Highlights
Wear occurs during the on-wing time of jet engines, and leads to a decreased performance
Special attention is given to the high-pressure compressor (HPC) because of its comparatively large influence on the overall engine performance
The present study addresses the effects of coupled deteriorated blades on the aerodynamic behavior of the first stage of a high-pressure compressor regarding three different operating points
Summary
Wear occurs during the on-wing time of jet engines, and leads to a decreased performance. Lange et al [2,3,4] investigated the influence of manufacturing tolerances on HPC performance by means of a probabilistic approach They developed a parametric model for compressor blades to reproduce the manufacturing tolerances by a transformation of blade profile parameters [2]. A sensitivity investigation on the influence of deterioration on high-pressure compressor performance was done by Reitz et al [5] They analyzed a deteriorated HPC front stage by means of a design of experiments (DoE) at cruise condition. The present study addresses the effects of coupled deteriorated blades on the aerodynamic behavior of the first stage of a high-pressure compressor regarding three different operating points. A fast prediction of characteristic performances of coupled deteriorated blades was done without using further CFD-simulations
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