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Research Papers

Influence of Coolant Density on Turbine Platform Film-Cooling With Stator–Rotor Purge Flow and Compound-Angle Holes

[+] Author and Article Information
Kevin Liu, Shang-Feng Yang

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

Je-Chin Han

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: jc-han@tamu.edu

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received October 28, 2013; final manuscript received February 24, 2014; published online May 9, 2014. Assoc. Editor: Srinath V. Ekkad.

J. Thermal Sci. Eng. Appl 6(4), 041007 (May 09, 2014) (9 pages) Paper No: TSEA-13-1182; doi: 10.1115/1.4026964 History: Received October 28, 2013; Revised February 24, 2014

A detailed parametric study of film-cooling effectiveness was carried out on a turbine blade platform. The platform was cooled by purge flow from a simulated stator–rotor seal combined with discrete hole film-cooling. The cylindrical holes and laidback fan-shaped holes were accessed in terms of film-cooling effectiveness. This paper focuses on the effect of coolant-to-mainstream density ratio on platform film-cooling (DR = 1 to 2). Other fundamental parameters were also examined in this study—a fixed purge flow of 0.5%, three discrete-hole film-cooling blowing ratios between 1.0 and 2.0, and two freestream turbulence intensities of 4.2% and 10.5%. Experiments were done in a five-blade linear cascade with inlet and exit Mach number of 0.27 and 0.44, respectively. Reynolds number of the mainstream flow was 750,000 and was based on the exit velocity and chord length of the blade. The measurement technique adopted was the conduction-free pressure sensitive paint (PSP) technique. Results indicated that with the same density ratio, shaped holes present higher film-cooling effectiveness and wider film coverage than the cylindrical holes, particularly at higher blowing ratios. The optimum blowing ratio of 1.5 exists for the cylindrical holes, whereas the effectiveness for the shaped holes increases with an increase of blowing ratio. Results also indicate that the platform film-cooling effectiveness increases with density ratio but decreases with turbulence intensity.

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References

Figures

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Fig. 1

Schematic of (a) experimental facility (b) linear cascade

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Fig. 2

Configuration of upstream stator rotor seal

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Fig. 3

Discrete hole configuration on platform

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Fig. 4

PSP working principle and calibration

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Fig. 5

Velocity profile and freestream turbulence intensity measured at the cascade inlet

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Fig. 6

Pressure and Mach number distribution without coolant injection

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Fig. 7

Density ratio effect on adiabatic film-cooling effectiveness for configuration A (M = 1.5, Tu = 10.5%, MFR = 0.5%)

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Fig. 8

Density ratio effect on adiabatic film-cooling effectiveness for configuration B (M = 1.5, Tu = 10.5%, MFR = 0.5%)

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Fig. 9

Blowing ratio effect on adiabatic film-cooling effectiveness for configuration A (DR = 1.5, Tu = 10.5%, MFR = 0.5%)

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Fig. 10

Blowing ratio effect on adiabatic film-cooling effectiveness for configuration B (DR = 1.5, Tu = 10.5%, MFR = 0.5%)

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Fig. 11

Adiabatic effectiveness distribution at two different turbulence intensities for configuration A (DR = 1.5, M = 1.5, MFR = 0.5%)

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Fig. 12

Adiabatic effectiveness distributions at two different turbulence intensities for configuration B (DR = 1.5, M = 1.5, MFR = 0.5%)

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Fig. 13

Laterally averaged film-cooling effectiveness

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Fig. 14

Area averaged film-cooling effectiveness

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