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RESEARCH PAPERS

The Effects of Varying the Combustor-Turbine Gap

[+] Author and Article Information
N. D. Cardwell, N. Sundaram

Mechanical Engineering Department,  Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

K. A. Thole

Mechanical and Nuclear Engineering Department,  Pennsylvania State University, University Park, PA 16802

J. Turbomach 129(4), 756-764 (Jul 26, 2006) (9 pages) doi:10.1115/1.2720497 History: Received July 18, 2006; Revised July 26, 2006

To protect hot turbine components, cooler air is bled from the high pressure section of the compressor and routed around the combustor where it is then injected through the turbine surfaces. Some of this high pressure air also leaks through the mating gaps formed between assembled turbine components where these components experience expansions and contractions as the turbine goes through operational cycles. This study presents endwall adiabatic effectiveness levels measured using a scaled up, two-passage turbine vane cascade. The focus of this study is evaluating the effects of thermal expansion and contraction for the combustor-turbine interface. Increasing the mass flow rate for the slot leakage between the combustor and turbine showed increased local adiabatic effectiveness levels while increasing the momentum flux ratio for the slot leakage dictated the coverage area for the cooling. With the mass flow held constant, decreasing the combustor-turbine interface width caused an increase in uniformity of coolant exiting the slot, particularly across the pressure side endwall surface. Increasing the width of the interface had the opposite effect thereby reducing coolant coverage on the endwall surface.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 11

Contours of adiabatic effectiveness for (a) 0.75%, (b) 0.85%, (c) 1.0% upstream slot mass flow rate for a nominal slot width

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Figure 12

Plots of laterally averaged adiabatic effectiveness for the entire passage with varied upstream slot mass flow

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Figure 13

Nondimensionalized mid-passage gap temperature profiles varied upstream slot mass flow

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Figure 14

Contours of adiabatic effectiveness for (a) 0.1%, (b) 0.2%, and (c) 0.3% mid-passage gap mass flow with nominal upstream slot width

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Figure 15

Plots of laterally averaged adiabatic effectiveness for the entire passage with varied mid-passage gap cooling

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Figure 16

Nondimensionalized mid-passage gap temperature profiles with varied mid-passage gap cooling

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Figure 17

Plots of thermal field data for (a) 0% flow and (b) 0.3% flow within the mid-passage gap

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Figure 10

Nondimensionalized mid-passage gap temperature profiles varied upstream slot widths given a nominal slot momentum flux ratio

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Figure 1

Endwall geometry with film-cooling holes, an upstream slot, and a mid-passage gap

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Figure 2

Cross section view of the mid-passage gap geometry with an accompanying seal strip

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Figure 3

Illustration of the wind tunnel facility

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Figure 4

Separate plenums for film-cooling, upstream slot, and mid-passage gap provided by independent flow control

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Figure 5

Contours of adiabatic effectiveness for (a) double, (b) nominal, (c) half-width upstream slot with 0.85% slot mass flow ratio

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Figure 6

Pitchwise averaged adiabatic effectiveness for the entire passage with varied upstream slot widths

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Figure 7

Nondimensionalized mid-passage gap temperature profiles with varied upstream slot widths

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Figure 8

Contours of adiabatic effectiveness for (a) double, (b) nominal, (c) half-width upstream slot with I=0.08 average slot momentum flux ratio

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Figure 9

Plots of pitchwise averaged adiabatic effectiveness for the entire passage with varied slot widths

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