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research-article

NUMERICAL AND EXPERIMENTAL FSI-STUDY TO DETERMINE MECHANICAL STRESSES INDUCED BY ROTATING STALL IN UNSHROUDED CENTRIFUGAL COMPRESSOR IMPELLERS

[+] Author and Article Information
Bob Mischo

MAN Diesel & Turbo Schweiz AG, Hardstrasse 319, 8005 Zürich, Switzerland
Bob.Mischo@man.eu

Philipp Jenny

MAN Diesel & Turbo Schweiz AG, Hardstrasse 319, 8005 Zürich, Switzerland
philipp.jenny@man-es.com

Sebastiano Mauri

MAN Diesel & Turbo Schweiz AG, Hardstrasse 319, 8005 Zürich, Switzerland
sebastiano.mauri@man-es.com

Yves Bidaut

MAN Diesel & Turbo Schweiz AG, Hardstrasse 319, 8005 Zürich, Switzerland
yves.bidaut@man-es.com

Max Kramer

MAN Diesel & Turbo Schweiz AG, Hardstrasse 319, 8005 Zürich, Switzerland
max.kramer@man-es.com

Sebastian Spengler

MAN Diesel & Turbo SE, Stadtbachstr. 1, 86153 Augsburg, Germany
sebastian.spengler@man-es.com

1Corresponding author.

ASME doi:10.1115/1.4041400 History: Received July 12, 2018; Revised September 05, 2018

Abstract

Under normal unshrouded industrial centrifugal compressor impeller operation, high frequency interaction, e.g. with vaned diffusers, dominates blade excitation. In severe part load, rotating stall can occur and cause resonant blade vibration with significant dynamic impeller blade stress. Jenny and Bidaut [1] described and quantified unsteady interaction between rotating stall and two unshrouded impellers in full scale compression units. This paper expands Jenny and Bidaut's work to investigate experimental and computational fluid structure interaction for comparable conditions with a similar stage operated in a scaled down test facility. Strain gauge and time-resolved pressure transducers on the scaled down stationary and rotating parts measured similar rotating stall patterns and induced stress levels. Rotating stall cell induced resonant blade vibration was identified for severe off-design operating conditions and the measured induced dynamic stress peaked at 15% of the impeller mechanical endurance limit. To support part load condition influence on mechanical integrity in the aero-mechanical design process, a one-way numerical Fluid-Structure Interaction study of the test rig setup was conducted and anchored by experimental verification. Unsteady full annulus CFD simulations predicted the same measured rotating stall pattern and the related predicted pressure field was in excellent agreement with the measurements (as low as 2% relative difference). The predicted stress level and the aerodynamic damping at resonant blade vibration also agreed well with the measured quantities (relative differences of 17% and 27%, respectively).

Copyright (c) 2018 by ASME
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