Research Papers

Practical Slot Configurations for Turbine Film Cooling Applications

[+] Author and Article Information
Joshua E. Bruce-Black, Frederick T. Davidson, David G. Bogard

 University of Texas at Austin, Austin, TX 78712

David R. Johns

 GE Energy, Greenville, SC 29615

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J. Turbomach 133(3), 031020 (Nov 29, 2010) (8 pages) doi:10.1115/1.4002413 History: Received October 02, 2009; Revised January 18, 2010; Published November 29, 2010; Online November 29, 2010

Turbine component film cooling is most effective when using a continuous slot to introduce coolant to the surface. However, this is not practical due to the structural weakness that would be inherent with a continuous slot. In this study, several slotlike designs are investigated to establish the film cooling effectiveness. These slot configurations extended only a partial distance through the simulated turbine vane wall and were fed with impinging cylindrical holes. The configurations were studied on the suction side of a scaled-up turbine vane. In this study, varying slot widths, discrete and continuous slots, and diffusing the coolant flow within the slot prior to it being emitted onto the surface of the vane were investigated. Rows of discrete round and shaped holes were also tested for comparison with the slots. The study of varying slot geometries showed that decreasing the width of the slots led to a substantial increase in adiabatic effectiveness. An internal coolant diffusion technique showed promise by maintaining performance levels while potentially providing a design configuration that more readily meets structural demands in real-world operating conditions. The coolant flow characteristics were also studied through the use of thermal profiles measurements. These thermal profiles showed minimal mainstream ingestion on the top surface of the slot prior to the coolant emitting onto the surface of the vane.

Copyright © 2011 by American Society of Mechanical Engineers
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Figure 1

Schematic showing the geometry of an angled slot with impinging cylindrical holes

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Figure 2

Top view of the continuous and discrete partial slot configurations

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Figure 3

Internally diffused configuration

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Figure 4

Thermal profile measurements

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Figure 5

Schematic of the test section and test airfoil

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Figure 6

Detailed view of the test vane

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Figure 7

Photograph of a flat and curved block insert as well as the placement of these inserts in the hatch

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Figure 8

Spatially averaged adiabatic effectiveness for continuous slots with L/d=7, P/d=3, and varying widths

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Figure 9

Spatially averaged adiabatic effectiveness with respect to slot width, w/d

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Figure 10

Comparison of spatially averaged adiabatic effectiveness for continuous and discrete slot designs

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Figure 11

Comparison of cooling performance for three slots with similar L/w but varying L/d

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Figure 12

Spatially averaged adiabatic effectiveness for discrete slots with varying width

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Figure 13

Comparison of an internally diffused discrete slot to a standard discrete slot

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Figure 14

Thermal profile of θ along the length of the slot aligned with an inlet hole: (a) L3 and (b) L7

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Figure 15

Thermal profile of θ along the length of the slot aligned between two inlet holes: (a) L3 and (b) L7

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Figure 16

Thermal profile of spanwise θ variation at the exit of the slot: (a) L3 and (b) L7

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Figure 17

Surface contours of adiabatic effectiveness for slots of varying depth and an expanded view of the slot region: (a) L3 and (b) L7 at M=1.8



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