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Research Papers

Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part II: Experimental Results

[+] Author and Article Information
C. W. Haldeman, R. M. Mathison, M. G. Dunn, S. A. Southworth, J. W. Harral

Gas Turbine Laboratory, The Ohio State University, Columbus, OH 43235

G. Heltland

 Honeywell Aerospace, Phoenix, AZ 85034

J. Turbomach 130(2), 021016 (Mar 24, 2008) (11 pages) doi:10.1115/1.2750678 History: Received July 13, 2006; Revised July 17, 2006; Published March 24, 2008

This paper presents measurements and the companion computational fluid dynamics (CFD) predictions for a fully cooled, high-work single-stage HP turbine operating in a short-duration blowdown rig. Part I of this paper (Haldeman, C. W., Mathison, R. M., Dunn, M. G., Southworth, S. A., Harral, J. W., and Heltland, G., 2008, ASME J. Turbomach., 130(2), p. 021015) presented the experimental approach, and Part II focuses on the results of the measurements and demonstrates how these results compare to predictions made using the Numeca FINE/Turbo CFD package. The measurements are presented in both time-averaged and time-accurate formats. The results include the heat transfer at multiple spans on the vane, blade, and rotor shroud as well as flow path measurements of total temperature and total pressure. Surface pressure measurements are available on the vane at midspan, and on the blade at 50% and 90% spans as well as the rotor shroud. In addition, temperature and pressure measurements obtained inside the coolant cavities of both the vanes and blades are presented. Time-averaged values for the surface pressure on the vane and blade are compared to steady CFD predictions. Additional comparisons will be made between the heat transfer on cooled blades and uncooled blades with identical surface geometry. This, along with measurements of adiabatic wall temperature, will provide a basis for analyzing the effectiveness of the film cooling scheme at a number of locations.

Copyright © 2008 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Sketch of flow path in vicinity of stage

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Figure 2

Blade internal cooling passage sketch (not to scale, with internal pressures)

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Figure 3

Blade tip grid blocks (O-mesh)

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Figure 4

Entire meshed model, including blocks for inlet, vane, blade, and tip grids

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Figure 5

Rotor internal pressures

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Figure 6

Vane Time-average pressures 50% span

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Figure 7

Vane time-average predictions, various spans

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Figure 8

Vane envelope shapes

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Figure 9

Vane pressure frequency domain data

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Figure 10

Vane 50% upper and lower gauge temperatures

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Figure 11

Time-dependent vane temperature data for gauge located at 50% span and 77.5%WD

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Figure 12

Vane 50% heat flux

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Figure 13

Time-averaged rotor shroud pressures

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Figure 14

Rotor shroud pressure envelopes

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Figure 15

Rotor shroud time-resolved data

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Figure 16

Blade 50% pressures (internal and external)

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Figure 17

Blade 50% time-resolved pressure data

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Figure 18

Blade 50% leading-edge frequency content

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Figure 19

Pulsation parameter on blade, 50% span

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Figure 20

Blade 15%, 50%, and 90% span steady pressure predictions

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Figure 21

Blade 50% gauge temperatures (cooled and uncooled)

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Figure 22

Blade cooled heat flux (various spans)

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Figure 23

50% span cooled and uncooled heat flux

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Figure 24

Blade 90% cooled and uncooled heat flux

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Figure 25

Blade 50% net heat flux reduction

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Figure 26

50% net heat flux reduction with heat flux

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Figure 27

Blade 90% net heat flux reduction

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