Research Papers: Gas Turbines: Manufacturing, Materials, and Metallurgy

An Experimental System for Assessing Combustor Durability

[+] Author and Article Information
Nagaraja S. Rudrapatna, Benjamin H. Peterson, Daniel Greving

 Honeywell Aerospace, 111 S. 34th Street, Phoenix, AZ 85034

J. Eng. Gas Turbines Power 133(4), 042103 (Nov 23, 2010) (6 pages) doi:10.1115/1.4002177 History: Received May 13, 2010; Revised May 25, 2010; Published November 23, 2010; Online November 23, 2010

Modern gas turbine combustors are made of high temperature alloys, employ effusion cooling, and are protected by a thermal barrier coating (TBC). Gas turbine combustor failure modes, such as TBC spallation, cracking, and distortion resulting from oxidation, creep, and thermal fatigue, are driven by hot spot peak temperature and the associated thermal gradient. Standard material characterization tests, such as creep, oxidation, and low cycle fatigue are indicators of a material’s potential performance but they neither fully represent the combustor geometric/material system nor fully represent the thermal fatigue conditions a combustor is subjected to during engine operation. Combustor rig tests and/or engine cyclic endurance tests to determine the suitability of new material systems for combustors are time-consuming and costly. Therefore, a simple yet efficient test method for screening material systems under representative combustor conditions is needed. An experimental system has been developed to fill this gap. This paper discusses the configured specimen geometry, test methodology, observed test results, and a comparison with typical failure modes observed in combustors.

Copyright © 2011 by American Society of Mechanical Engineers
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Figure 1

Honeywell’s TFE731-5 combustor

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Figure 2

Photograph of the subelement combustor can

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Figure 3

Schematic depicting the subelement combustor can test

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Figure 4

Photograph of the test setup

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Figure 5

Generalized thermal cycle definition for testing

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Figure 6

Infrared thermal image of the subelement can with hot spot T/C locations

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Figure 7

Photograph of the thermocouples on the inside (metal side) of the subelement can

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Figure 8

Typical thermal cycle data

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Figure 9

Photograph of hot spot on subelement can surface

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Figure 10

Permanent distortion of can, 543 cycles at ∼1660°F peak temperature

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Figure 11

Photographs of subelement can failure locations: (a) 543 cycles at ∼1660°F (904°C) peak temperature—TBC side, (b) cold (T/C) side, and (c) 1136 cycles at ∼1600°F (871°C) peak temperature

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Figure 12

Optical micrographs of metallographic cross sections from a subelement combustor can

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Figure 13

Crack at the edge of effusion hole, 543 cycles at ∼1660°F peak temperature



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