Session: 36-09 Uncertainty Quantification & Sensitivity Analysis (1)

Paper Number: 122239

122239 - Probabilistic Analysis of Leading Edge Erosion Behavior of a High-Pressure Compressor in a Turbofan Engine 

The demands for competitiveness, performance, and sustainability in civil aviation become more and more challenging and therefore an increase in the efficiency of aero engines is required. A potential starting point for optimization to reach these goals is the compressor. The influence of the compressor blade's leading edges (LE) on the overall aerodynamic behavior and performance deterioration due to erosion are well-known topics. However, the interaction between LE geometry and erosion behavior still needs to be studied.
Therefore, a Monte Carlo simulation based analysis of LE erosion caused by ingestion of naturally occurring dust during operation is presented. The influence of blade geometry, operating point, and particle configuration on erosive wear is investigated by the example of a 10.5-stage high-pressure compressor of a modern civil turbofan engine.
By incorporating a one-way coupled Euler-Lagrangian approach trajectories of solid particles through the compressor have been calculated. To replicate naturally occurring mineral dust and volcanic ash different particle configurations have been studied, varying particle size, density, and drag behavior. Geometric effects have been taken into account by varying blade geometry based on a comprehensive database of optically measured ex-service blades. By applying an erosion model the resulting geometry of artificially eroded compressor blades is derived. The blade geometry is characterized utilizing a parametric model capable of describing LE variability.
The results indicate that the change of geometry caused by erosive wear shows a characteristic behavior. This erosion characteristic is mostly independent of the operating point and geometry considered. Abrasive effects mainly influence the area close to the blade tip, increase asymmetry, and change the curvature of the LE. These results are consistent with the analysis of optically measured ex-service blades.

Presenting Author: Andreas Türke Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion

Presenting Author Biography: Andreas Türke is a mechanical engineer with a background in aerospace engineering, specialized in turbomachinery and flight propulsion. He graduated from TUD Dresden University of Technology (Technische Universität Dresden) with a degree in mechanical engineering. As a student, he investigated erosion phenomena in axial compressor as part of a research project at the Chair of Turbomachinery and Flight Propulsion. For his diploma thesis, he worked at FTT Deutschland GmbH, where he developed a test bed matching process for radial compressors. In May 2023 Andreas Türke joined the he Chair of Turbomachinery and Flight Propulsion at TUD as a research associate. In his research he analyzes the impact of additive manufacturing on turbine blade cooling technologies.

Authors:

Andreas Türke Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion
Lukas Schlüter Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion
Matthias Voigt Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion
Robin Schmidt Rolls-Royce Deutschland Ltd & Co KG
Andreas Vogel Rolls-Royce Deutschland Ltd & Co KG
Ronald Mailach Technische Universität Dresden, Institute of Fluid Mechanics, Chair of Turbomachinery and Flight Propulsion