Aeroacoustic Scaling of a Compressor Stator Blade Row

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Economic and regulatory requirements imposed on turbomachinery components of modern turbojet engines have been becoming more stringent over the last decades. The consideration of noise emissions in early development stages is thus becoming an increasingly important design criterion. In the industry, the modelling applied for this purpose is usually based on analytical or empirical approaches, which assume an abstraction of the blade rows, e.g. as flat plates. The validation of these models, but also of numerical tools in later design stages, based on experimental reference data is complicated by the fact that the common turbomachinery test rigs cannot be used for high-quality acoustic measurements due to acoustically unsuitable boundary conditions (low signal-to-noise ratio, high acoustic reflections within the measuring section).On the other hand, acoustically optimized test rigs are only available in selected designs and configurations. For the use of these acoustic test rigs, a similarity assessment is necessary, which allows a comparison between real machines and the test rig environments with controllable acoustic boundary conditions. To achieve this aeroacoustic similarity, approaches based on analytical methods already exist, but so far, they have only been validated with simplified numerical methods. The aim of the project is therefore to extend an existing scaling approaches and to validate them in extensive numerical and experimental investigations. As a practical application, the aeroacoustic similarity of a stator blade row between the high-speed axial compressor and the acoustic wind tunnel of the TFD will be established and investigated. Based on the high-precision measurements and numerical simulations, the validation of the scaling approach will be carried out in order to enable an easier transfer of experimental acoustic investigations to aero engines and stationary turbomachinery in the long term.