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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Effects of Combustion Chamber Geometry Deviations Upon Exit Temperature Profiles for Populations With Varied Service Limitations

[+] Author and Article Information
Clayton Kotzer, Marc LaViolette, William Allan, Asad Asghar

 Royal Military College of Canada, Kingston, ON, K7K 7B4, Canada

J. Eng. Gas Turbines Power 133(11), 111503 (May 19, 2011) (7 pages) doi:10.1115/1.4002845 History: Received June 04, 2010; Revised July 23, 2010; Published May 19, 2011; Online May 19, 2011

The purpose of this continuing research was to investigate the effects of combustion chamber geometry on exit temperature fields using a validated ambient pressure test rig. Rig test conditions were set to simulate an engine operating condition of 463 km/h (250 kn) at 7620 m (25,000 ft) by matching Mach number, equivalence ratio, and Sauter mean diameter of the fuel spray. Using a thermocouple rake, high resolution temperature measurements were obtained in the combustion chamber exit plane. Following the previously published procedures, a three-dimensional laser scanning system was used to quantify geometric deviations from two populations of combustion chambers. These populations differed in that one had a significantly higher allowable engine operating temperature for continuous cruise condition. Geometric deviations of both populations were compared with the reference model. The relationship between combustion chamber exit temperature profile and geometric deviation of each population was then compared. The main conclusion of this research was that the temperature profile degradation of both populations due to geometric deviations followed similar trends. These results highlighted that the difference in operating limitations of these populations did not significantly affect component performance.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 1

Contributors to pattern factor

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Figure 2

Significant locations of the T56-A-15 combustion chamber

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Figure 3

Combustion test section cross section, without dummy liners

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Figure 4

(a) Installed thermocouple rake and (b) definition of landmark positions in the combustion exit plane, both looking downstream

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Figure 5

Average nondimensional exit plane temperature maps

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Figure 6

Correlation of geometric deviations and nondimensional temperature distribution (model from Ref. 2, shown with solid line)

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Figure 7

Comparison of deviations of representative specimen cross sections at 488 mm looking downstream

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Figure 8

Difference in temperature profile between representative specimens of significant and minor geometric deviations

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Figure 9

Correlation of fishmouth geometry deviation to pattern factor (model from Ref. 2, shown with solid line)

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