Motivation and objectives
Accurate prediction of aeroacoustic effects in compressor stages requires a detailed understanding of sound propagation and its dependence on flow and geometry parameters. An initial focus of the project is to identify the parameters relevant for aeroacoustic scaling, to scale a stator guide vane row on this basis, and to compare its acoustic behavior with that of the original guide vane from the 4AC. By transferring the acoustic characteristics between the original and scaled models, the aim is to verify how reliably aeroacoustic scaling approaches work in turbomachinery applications.
A second focus is on the use of high-quality measurement data from the acoustically optimized AWT, which enables a comprehensive analysis of the transmission and mode behavior of the guide vane row. This data forms the basis for the calibration and improvement of aeroacoustic models for predicting sound propagation in compressors. The project thus makes an important contribution to a better understanding of acoustic mechanisms in turbomachinery and supports the further development of numerical and analytical methods for aeroacoustic design.
Publications
On the Aeroacoustic Scaling of Axial Flow Turbines, DOI: 10.38036/jgpp.15.3_9
Aeroacoustic Numerical Investigations of a Scaled Compressor Cascade, DOI: 10.33737/gpps20-tc-94
Numerical Validation of an Aeroacoustic Scaling Approach, DOI: 10.2514/6.2023-3837
On the Aeroacoustic Scaling of Axial Flow Turbines, DOI: 10.38036/jgpp.15.3_9
Broadband interaction noise analytical predictions for an axial compressor stator, DOI: GPPS-TC-2024-0194
Aeroakustische Skalierung einer Verdichterleitschaufelreihe, DOI: N/A
Responsible institute
The project is managed by the Institute for Turbomachinery and Fluid Dynamics.
