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TECHNICAL PAPERS

Scaling of Guide Vane Coolant Profiles and the Reduction of a Simulated Hot Streak

[+] Author and Article Information
Sean C. Jenkins

Mechanical Engineering Department, The University of Texas at Austin, Austin, TX 78712sjenkins@mail.utexas.edu

David G. Bogard

Mechanical Engineering Department, The University of Texas at Austin, Austin, TX 78712dbogard@mail.utexas.edu

J. Turbomach 129(3), 619-627 (Aug 08, 2006) (9 pages) doi:10.1115/1.2447803 History: Received March 09, 2006; Revised August 08, 2006

The turbine section of a gas turbine engine is subjected to a nonuniform temperature distribution in the gas flow from the combustor. Regions of elevated temperatures, known as “hot streaks,” subject the turbine airfoil to high heat loads. In this study, the reduction of hot streaks by coolant from a film cooled nozzle guide vane was experimentally evaluated. Experiments were conducted with an approach mainstream turbulence level of 20% to simulate actual turbine conditions. The coolant distributions downstream of the vane were measured for varying blowing ratios and varying coolant density, and scaling methods were found for variations in both parameters. For this study, the hot streak peak was positioned to impact the vane at the stagnation line. Measurements of the hot streak strength with coolant blowing showed as much as a 55% decrease in peak temperature compared with no coolant.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 4

Schematic of full width at 20%, δ20%

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Figure 5

Normalized temperature ratio (ΘR) coolant contours at Position T for full coverage blowing at Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6, DR=1.6

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Figure 6

Normalized temperature ratio (ΘR) coolant profiles at Position T at midspan (z∕S=0.50) and at the spanwise position of the peak coolant level (z∕S=0.31) at standard blowing ratios (Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6), DR=1.6

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Figure 19

Normalized temperature ratio (ΘR) profiles at Position T for the hot streak impacting the stagnation line without coolant and with full coverage blowing at adiabatic effectiveness optimum blowing ratios (Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6) and above optimum blowing ratios (Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0), with density ratios of DR=1.2 and 1.6

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Figure 1

Simulated vane cascade with hot streak generator

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Figure 2

Showerhead and pressure side cooling holes

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Figure 3

Schematic of film cooling hole configuration

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Figure 17

Normalized temperature ratio (ΘR) profiles at Position T and Position B for the hot streak impacting the stagnation line without coolant and with full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0, DR=1.6

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Figure 18

Normalized temperature ratio (ΘR) contours at Position T with the hot streak at the stagnation line with full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0 at (a) DR=1.2; and (b)DR=1.6

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Figure 10

Normalized temperature ratio (ΘR) coolant contours for full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0, DR=1.6 at: (a) Position T; and (b) Position B

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Figure 11

Comparison of normalized coolant temperature (ΘC) profiles at Position T at midspan (z∕S=0.50) and the position of peak coolant (z∕S=0.31) for full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0, at low-density ratio (DR=1.2) and high-density ratio (DR=1.6)

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Figure 12

Comparison of normalized coolant temperature (ΘC) profiles at Position T at midspan (z∕S=0.50) and the position of peak coolant (z∕S=0.31) for full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0, at low-density ratio (DR=1.2) and high-density ratio (DR=1.6)

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Figure 13

Normalized temperature ratio (ΘR) contours at Position T with the hot streak at the stagnation line: (a) no coolant; (b) full coverage blowing at Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6, DR=1.6

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Figure 14

Normalized temperature ratio (ΘR) contours at Position T with the hot streak at the stagnation line: (a) full coverage blowing at Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6, DR=1.6; and (b) full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0, DR=1.6

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Figure 15

Normalized temperature ratio (ΘR) profiles at position T for the hot streak impacting the stagnation line without coolant and with full coverage blowing at adiabatic effectiveness optimum blowing ratios (Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6) and above optimum blowing ratios (Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0), DR=1.6

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Figure 16

Normalized temperature ratio (ΘR) contours for full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0, DR=1.6: (a) Position T (trailing edge); and (b) Position B

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Figure 7

Normalized temperature ratio (ΘR) coolant contours at Position T, DR=1.6, for full coverage blowing at: (a) full coverage blowing at Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6; and (b) full coverage blowing at Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0

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Figure 8

Normalized temperature ratio (ΘR) coolant profiles at Position T at midspan (z∕S=0.50) and at the spanwise position of the peak coolant level (z∕S=0.31) for standard blowing ratios (Mshowerhead*=1.6, Mavg,suction=0.7, and Mavg,pressure=0.6) and high blowing ratios (Mshowerhead*=2.0, Mavg,suction=1.0, and Mavg,pressure=1.0), DR=1.6

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Figure 9

Normalized temperature ratio scaled by the ratio of coolant to core flow (ΘR∕mtotal*) for coolant profiles at Position T at midspan (z∕S=0.50) and at the spanwise position of the peak coolant level (z∕S=0.31) for standard blowing ratios and high blowing ratios, DR=1.6

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