Experimental tests were performed to investigate flutter behaviour of the transonic rotor in a high-speed multistage compressor test facility. Besides the acquisition of overall performance parameters the rig was equipped with special instrumentation such as strain gauges, tip-timing system and dynamic pressure transducers. The 4-stage compressor comprises 3 variable vanes. The instrumentation was able to measure stall and flutter and forced responses of the rotor blades. The experimental data was used to validate the in-house aeroelastic solver. During testing flutter was triggered intentionally at part speed conditions with malscheduled variable vanes. The malschedule changed the flow incidences for the relevant rotor and induced flutter. An aeroelastic simulation was set up according to the flutter conditions found during the experiment. The measured boundary conditions were used to set up the aeroelastic simulation. The calculation shows the torsion mode with a negative aerodynamic damping which confirms the test results. The only difference between test and prediction is the nodal diameter, at which the flutter occurs.
This paper describes the relevance of unsteady flow investigations in turbomachinery and how they are included into the design process for compressors of modern aero engines. Significant work has been performed in leadership of Professor Gallus at the Institute for Jet Propulsion and Turbomachinery (IST) at the RWTH Aachen, University of Technology, Germany, in this area of interest. Selected topics of this numerical and experimental work will be shown. This academic work has of course to be made useful for application in the design process of turbomachinery, so the connection to today’s challenges is shown as well. In recent years, blisks have become a more attractive choice for design and manufacture of compressor rotors. In contrast to the earlier years, where blade flutter has enjoyed the main focus of interest, the blisk technology requires different approaches in terms of the assessment of the interaction between structure and fluid. The implementation of the flutter and forced response investigations into the design process for blisks is thus a major issue to be solved. The paper will describe, how the relevant unsteady flow phenomena are assessed. Results will be shown for a recent engine development, the high pressure compressor for the new TP400 engine for the Airbus A400M military transport aircraft. This compressor is currently designed at Rolls-Royce Deutschland (RRD).
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