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ANALYSIS OF THE EFFECT OF MULTI-ROW AND MULTIPASSAGE AERODYNAMIC INTERACTION ON THE FORCED RESPONSE VARIATION IN A COMPRESSOR CONFIGURATION - PART 1: AERODYNAMIC EXCITATION

[+] Author and Article Information
Harald Schoenenborn

MTU Aero Engines AG, Munich, Germany
harald.schoenenborn@mtu.de

1Corresponding author.

ASME doi:10.1115/1.4038868 History: Received August 21, 2017; Revised October 24, 2017

Abstract

The aeroelastic prediction of blade forcing is still a very important topic in turbomachinery design. Usually, the wake from an upstream airfoil and the potential field from a downstream airfoil are considered as the main disturbances. In recent years, it became evident that in addition to those two mechanisms Tyler-Sofrin modes may have a significant impact on blade forcing. In Schrape et al. it was found that in multi-row configurations not only the next, but also the next but one blade row is very important as it may create a large circumferential forcing variation fixed in the rotating frame of reference. In the present paper a study of these effects is performed on the basis of a quasi 3D multi-row and multi-passage compressor configuration. A harmonic balancing code is used for various setups and the results are compared to full-annulus unsteady calculations. It is shown that the effect of the circumferentially different blade excitation is mainly contributed by the Tyler-Sofrin modes and not to blade-to-blade variation in the steady flowfield. The influence of various clocking positions, coupling schemes and number of harmonics onto the forcing is investigated. It is shown that along a compressor speedline the blade-to-blade forcing variation changes significantly. In addition, multi-row flutter calculations show the influence of the upstream and downstream blade row onto aerodynamic damping. The effect of these forcing variations onto random mistuning effects is investigated in the second part of the paper.

Copyright (c) 2017 by ASME
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