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Research Papers

Prediction of Film Cooling and Heat Transfer on a Rotating Blade Platform With Stator-Rotor Purge and Discrete Film-Hole Flows in a 1-12 Turbine Stage

[+] Author and Article Information
H. Yang1

Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

Z. Gao2

Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

H. C. Chen

Department of Civil Engineering, Texas A&M University, College Station, TX 77843-3136

J. C. Han

Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123jc-han@tamu.edu

M. T. Schobeir

Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

1

Present address: Compressor Development, Tech Center, Trane Co., La Crosse, WI 54601.

2

Present address: Siemens Energy, 11842 Corporate Boulevard, Orlando, FL 32817.

J. Turbomach 131(4), 041003 (Jun 30, 2009) (12 pages) doi:10.1115/1.3068325 History: Received April 01, 2008; Revised November 20, 2008; Published June 30, 2009

Numerical simulations were performed to predict the film cooling effectiveness and heat transfer coefficient distributions on a rotating blade platform with stator-rotor purge flow and downstream discrete film-hole flows in a 1-12 turbine stage using a Reynolds stress turbulence model together with a nonequilibrium wall function. Simulations were carried out with sliding mesh for the rotor under three rotating speeds (2000 rpm, 2550 rpm, and 3000 rpm) to investigate the effects of rotation and stator-rotor interaction on the rotor blade-platform purge flow cooling and discrete-hole film cooling and heat transfer. The adiabatic film cooling effectiveness and heat transfer coefficients were calculated using the adiabatic wall temperatures with and without coolant to examine the true coolant protection excluding the effect of turbine work process. The stator-rotor interaction strongly impacts the purge slot film cooling and heat transfer at the platform leading portion while only slightly affects the downstream discrete-hole film cooling near the platform trailing portion. In addition, the effect of turbine work process on the film cooling effectiveness and the associated heat transfer coefficients have been reported.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

(a) Computational domain of purge slot and discrete holes film-cooled platform in a 1-12 turbine stage and (b) numerical grids (repeated two times)

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Figure 2

Detailed grid distributions of the platform purge slot and discrete film holes on the rotating platform

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Figure 13

Overall film cooling effectiveness on the rotating blade platform for various rotating speeds at four time phases, purge slot MFR=1%, discrete holes M=1

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Figure 12

Overall heat transfer coefficients on the rotating platform for various rotating speeds, purge slot MFR=1%, discrete holes M=1

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Figure 11

Heat transfer coefficients (based on the adiabatic wall temperature) on the rotating platform for various rotating speeds, purge slot MFR=1%, discrete holes M=1

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Figure 10

Comparison of adiabatic film cooling effectiveness on the rotating blade platform between experiment (17) and simulation for 2550 rpm and 3000 rpm, purge slot MFR=1%, discrete holes M=1

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Figure 9

(a) Laterally averaged adiabatic cooling effectiveness for various rotating speeds. (b) Instantaneous and time averaged adiabatic film cooling effectiveness for 2550 rpm. (c) Laterally averaged unsteady intensity of adiabatic cooling effectiveness for various rotating speeds, with platform purge slot MFR=1%, discrete film holes M=1.

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Figure 8

Comparison of adiabatic film cooling effectiveness on the rotating blade platform for various rotating speeds, platform purge slot MFR=1%, discrete film holes M=1

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Figure 7

Coolant flow structures for (a) purge slot at leading portion based on the rotor relative velocity and (b) discrete holes at trailing portion based on the rotor absolute velocity

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Figure 6

Comparison of static pressure contours on the rotor blade hub region: (a) without platform purge flow and (b) with platform purge flow; 2550 rpm, time phase 14, MFR=1%

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Figure 5

Comparison of streamlines and dimensionless temperature (θ) contours on the annular cross sections for various rotating speeds, time phase 14

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Figure 4

(a) Conceptual rotor inlet velocity triangle and (b) predicted rotor relative velocity for various working conditions

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Figure 3

(a) Vertical cross section and (b) corresponding dimensionless temperature contours and streamlines, 2550 rpm, MFR=1%

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