Technical Brief

Influence of Coolant Density on Turbine Blade Film-Cooling With Axial and Compound Shaped 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

Je-Chin Han

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

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received August 17, 2012; final manuscript received October 19, 2013; published online January 24, 2014. Assoc. Editor: Phillip M. Ligrani.

J. Heat Transfer 136(4), 044501 (Jan 24, 2014) (5 pages) Paper No: HT-12-1441; doi: 10.1115/1.4025901 History: Received August 17, 2012; Revised October 19, 2013

Adiabatic film-cooling effectiveness is examined systematically on a typical high pressure turbine blade by varying three critical flow parameters: coolant blowing ratio, coolant-to-mainstream density ratio, and freestream turbulence intensity. Three coolant density ratios 1.0, 1.5, and 2.0 are chosen for this study. The average blowing ration and the turbulence intensity are 1.5% and 10.5%, respectively. Conduction-free pressure sensitive paint (PSP) technique is used to measure film-cooling effectiveness. Foreign gases are used to study the effect of coolant density. Two test blades feature axial angle and 45 deg compound-angle shaped holes on the suction side and pressure side. Both designs have 3 rows of 30 deg radial-angle cylindrical holes around the leading edge region. The inlet and the exit Mach number are 0.27 and 0.44, respectively. Reynolds number based on the exit velocity and blade axial chord length is 750,000. Overall, the compound angle design performs better film coverage that axial angle. Greater coolant-to-mainstream density ratio results in lower coolant-to-mainstream momentum and prevents coolant to lift-off.

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Han, J. C., and Rallabandi, A. P., 2010, “Turbine Blade Film Cooling Using PSP Technique,” Front. Heat Mass Transfer, 1(1), pp. 1–21. [CrossRef]
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Fig. 1

Schematic of (a) experimental facility (b) optical setup

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Fig. 2

Details of the test blade

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Fig. 3

Surface Mach number distributions

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Fig. 4

Velocity profile and freestream turbulence intensity measured at the cascade inlet

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Fig. 5

Coolant-to-mainstream pressure ratio

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Fig. 6

Adiabatic effectiveness distribution at three different density ratio (M = 1.5, Tu = 10.5%)

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Fig. 7

Spanwise average adiabatic effectiveness



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