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research-article

Influence of Rotor Tip Blockage on Near Stall Blade Vibrations in an Axial Compressor Rig

[+] Author and Article Information
Daniel Möller

Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, Darmstadt, Germany
moeller@glr.tu-darmstadt.de

Maximilian Juengst

Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, Darmstadt, Germany
juengst@glr.tu-darmstadt.de

Heinz-Peter Schiffer

Institute of Gas Turbines and Aerospace Propulsion, Technische Universität Darmstadt, Darmstadt, Germany
schiffer@glr.tu-darmstadt.de

Thomas Giersch

Rolls-Royce Deutschland, Blankenfelde-Mahlow, Germany
thomas.giersch@rolls-royce.com

Frank Heinichen

Rolls-Royce Deutschland, Blankenfelde-Mahlow, Germany
frank.heinichen@rolls-royce.com

1Corresponding author.

ASME doi:10.1115/1.4038316 History: Received August 28, 2017; Revised October 01, 2017

Abstract

Rotor blade vibrations observed in the Darmstadt transonic compressor rig are investigated in this paper. The vibrations are non-synchronous and occur in the near stall operating re- gion. Rotor tip flow fluctuations traveling near the leading edge against the direction of rotation (in the rotor relative frame of reference) with about 50% blade tip speed are found to be the reason for the occurrence of the vibrations. The investigations show, that the blockage at the rotor tip is an important factor for the aeroelastic stability of the compressor in the near stall region. It is found, that by application of a recirculating tip in- jection casing treatment, the aeroelastic stability increases as a result of reduced blockage in the rotor tip region.

Rolls-Royce plc
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