Development of an Experimental Capability to Produce Controlled Blade Tip∕Shroud Rubs at Engine Speed

[+] Author and Article Information
Corso Padova, Jeffrey Barton, Michael G. Dunn

Gas Turbine Laboratory,  Ohio State University, Columbus, OH 43235

Steve Manwaring, Gamaliel Young

 GE Aircraft Engines, Cincinnati, OH 45215

Maurice Adams, Michael Adams

 Machinery Vibrations, Inc., Chagrin Falls, OH 44022

J. Turbomach 127(4), 726-735 (Mar 01, 2004) (10 pages) doi:10.1115/1.1934429 History: Received October 01, 2003; Revised March 01, 2004

An experimental capability using an in-ground spin-pit facility specifically designed to investigate aeromechanic phenomena for gas turbine engine hardware rotating at engine speed is demonstrated herein to obtain specific information related to prediction and modeling of blade-casing interactions. Experiments are designed to allow insertion of a segment of engine casing into the path of single-bladed or multiple-bladed disks. In the current facility configuration, a 90deg sector of a representative engine casing is forced to rub the tip of a single-bladed compressor disk for a selected number of rubs with predetermined blade incursion into the casing at rotational speeds in the vicinity of 20,000rpm.

Copyright © 2005 by American Society of Mechanical Engineers
Topics: Engines , Blades , Stress
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Figure 1

General view of facility (with protective top cover)

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Figure 2

Section of spindle

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Figure 4

Incursion mechanism support ring

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Figure 5

Incursion mechanism photo

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Figure 6

Incursion mechanism, cam, and slide

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Figure 8

Pneumatic control system

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Figure 9

Load measuring unit LMU

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Figure 10

Casing motion and incursion region

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Figure 11

Time Scales of blade rubs

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Figure 12

Triggering of case motion

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Figure 13

Blade contact trigger circuit

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Figure 14

Optical sensor trigger circuit

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Figure 15

Typical load cell measurements

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Figure 16

Typical strain gauge measurements

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Figure 17

Strain gauge measurements for shoe-sweep time scale



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