Detailed numerical and experimental investigations of film cooling effectiveness were conducted on the blade tips of the first rotor row pertaining to a three-stage research turbine. Four different blade tip ejection configurations were utilized to determine the impact of the hole arrangements on the film cooling effectiveness. Plane tip with tip hole cooling, squealer tip with tip hole cooling, plane tip with pressure side (PS) edge compound angle hole cooling, and squealer tip with PS-edge compound angle hole cooling. To avoid rotor imbalance, every pair is installed radially. Film cooling effectiveness measurements were performed for three blowing ratios (M) of 0.75, 1.25, and 1.75. Film cooling data was also obtained for three rotational speeds; 3000 rpm (reference condition), 2550 rpm and 2000 rpm. Film cooling measurements were performed using pressure sensitive paint (PSP) technique. In a parallel effort, extensive numerical investigations of the above configurations were performed to give a better view of flow behavior using a commercially available code. The experimental investigations were performed in the three-stage multipurpose turbine research facility at the Turbomachinery Performance and Flow Research Laboratory (TPFL), Texas A&M University.
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Research-Article
A Combined Experimental and Numerical Study of the Turbine Blade Tip Film Cooling Effectiveness Under Rotation Condition
Mohsen Rezasoltani,
Mohsen Rezasoltani
Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
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Kun Lu,
Kun Lu
Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
Search for other works by this author on:
Meinhard T. Schobeiri,
Meinhard T. Schobeiri
1
Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
e-mail: tschobeir@tamu.edu
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
e-mail: tschobeir@tamu.edu
1Corresponding author.
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Je-Chin Han
Je-Chin Han
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
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Mohsen Rezasoltani
Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
Kun Lu
Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
Meinhard T. Schobeiri
Turbomachinery Performance and
Flow Research Laboratory,
Department of Mechanical Engineering,
e-mail: tschobeir@tamu.edu
Flow Research Laboratory,
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
e-mail: tschobeir@tamu.edu
Je-Chin Han
Department of Mechanical Engineering,
Texas A&M University
,College Station, TX 77843-3123
1Corresponding author.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 21, 2014; final manuscript received September 8, 2014; published online November 26, 2014. Editor: Ronald Bunker.
J. Turbomach. May 2015, 137(5): 051009 (12 pages)
Published Online: May 1, 2015
Article history
Received:
August 21, 2014
Revision Received:
September 8, 2014
Online:
November 26, 2014
Citation
Rezasoltani, M., Lu, K., Schobeiri, M. T., and Han, J. (May 1, 2015). "A Combined Experimental and Numerical Study of the Turbine Blade Tip Film Cooling Effectiveness Under Rotation Condition." ASME. J. Turbomach. May 2015; 137(5): 051009. https://doi.org/10.1115/1.4028745
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