Abstract
This study investigates the aerodynamic and aeroelastic characteristics of a transonic axial compressor, focusing on blade count reduced rotor behavior. The analysis is based on experiments, conducted at the Transonic Compressor Darmstadt test rig at Technical University of Darmstadt and compulsory simulations. In order to obtain measurement data for the detailed aerodynamic and aeroelastic investigation, extensive steady and unsteady instrumentation was applied. Besides transient measurements at the stability limit to determine the operating range and limiting phenomena, performance measurements were performed, presenting promising results with respect to the capabilities of blade count reduced rotors. Close to the stability limit, aerodynamic disturbances like radial vortices were detected for both rotors, varying in size, count, speed and trajectory. Comparing the rotor configurations results in different stability limits along the compressor map as well as varying aeromechanical behavior. Those effects can partially be traced to the variation in blade pitch and associated aerodynamics.
Highlights
At near choke (NC), higher mass flows can be achieved for R-Red
The conducted experimental study with compulsory simulations, focusing on the aerodynamic and aeroelastic effects due to a reduced rotor blade count, presents promising results with respect to steady aerodynamics and performance capabilities as well as distinct influences affecting the fluid-structure-interaction in the vicinity of the stability limits
Results for subsonic and transonic operating conditions are taken into account, indicating a change in mechanism
Summary
Design trends for future aero engines aim for increased efficiency with reduced exhaust gas and noise emissions. As one of the major components of an aero engine, this requires smaller and lighter designs with maintained or even increased performance This can for example be achieved by a minimum number of compressor stages and reduced blade counts, resulting in increased aerodynamic stage and blade loading, higher susceptibility to secondary flow phenomena. The aerodynamic loading of single blades is increased for reduced blade counts at similar operating conditions within the compressor characteristic. This leads to an amplified susceptibility to secondary flow phenomena as well as varying interaction with the shock and related blockage. Multiple experiments and simulations are performed, to analyze the mechanisms leading to unsteady aerodynamic and aeroelastic effects close to the compressor operating limit, focusing on the phenomena due to a reduced rotor blade count. From an aerodynamic point of view, the reduced blade count rotor shows promising results with respect to performance capabilities, whereas distinct influences can be derived for the aeroelastic behavior, especially during stall inception
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