Response of a Transonic Compressor to a Massive Inlet Distortion

Authors

F. Wartzek - Technische Universität Darmstadt, Institute of Gas Turbines and Aerospace Propulsion, Germany
C. Brandstetter - Technische Universität Darmstadt, Institute of Gas Turbines and Aerospace Propulsion, Germany
F. Holzinger - Technische Universität Darmstadt, Institute of Gas Turbines and Aerospace Propulsion, Germany
H.-P. Schiffer - Technische Universität Darmstadt, Institute of Gas Turbines and Aerospace Propulsion, Germany

Abstract

The demand to extend the flight envelope of an aircraft makes predicting the behaviour of a plane and its components close to its aerodynamic limits imperative. The interaction of the plane, the engine and the atmosphere is still challenging to model. One problem is that by reducing the stability margin the risk of disturbances rises. A separation in the intake can lead to a distortion of the inflow, especially for the engines. In contrast to academic experiments, this publication shows the investigation of a realistic distortion pattern in a transonic compressor stage. A bevelled beam was installed upstream of the rotor. The radial extent was 10% of the channel height, the circumferential extent was 120° . This beam generated a separation that extended into the rotor. The interaction of this massive separation with the compressor was investigated using high-resolution measurement techniques. The flow in the compressor was influenced around the entire circumference and span even though the distortion was located only at the casing.