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research-article

Full-Annulus Simulation of Non-Synchronous Blade Vibration Excitation of an Axial Compressor

[+] Author and Article Information
Daniel Espinal

Ph.D. Candidate, Sr. Engineer, Pratt & Whitney
dan_espinal@hotmail.com

Hong-Sik Im

Ph.D., Principal Engineer, Doosan ATS America
sunny33156@gmail.com

Gecheng Zha

Professor, Dept. of Mechanical and Aerospace Engineering, University of Miami, Coral Gables, Florida 33124
gzha@miami.edu

1Corresponding author.

ASME doi:10.1115/1.4038337 History: Received September 26, 2016; Revised October 27, 2017

Abstract

A high speed 1-1/2 axial compressor stage is simulated in this paper using an Unsteady Reynolds-Averaged Navier-Stokes (URANS) solver for a full-annulus configuration to capture its non-synchronous vibration (NSV) flow excitation with rigid blades. The predicted dominant frequencies using the blade tip response signals are not harmonic to the engine order, which is the NSV excitation. The simulation is based on a rotor blade with a 1.1% tip-chord clearance. Comparison with the previous 1/7 annulus simulations show that the time-shifted phase-lag BCs used in the 1/7 annulus are accurate. For most of the blades, the NSV excitation frequency is 6.2% lower than the measurement in the rig test, although some blades displayed slightly different NSV excitation frequencies. The simulation confirms that the NSV is a full annulus phenomenon. The instability of the circumferential traveling vortices in the vicinity of the rotor tip due to the strong interaction of incoming flow is the main cause of the NSV excitation. This instability is present in all blades of the rotor annulus. For circumferentially averaged parameters like total pressure ratio, NSV is observed to have an effect on the radial profile, particularly at radial locations above 70% span. A design with a lower loading of the upper blade span and a higher loading of the mid blade spans is recommended to mitigate or remove NSV.

Copyright (c) 2017 by ASME
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