An experimental and numerical investigation of detailed tip clearance flow structures and their effects on the aerodynamic performance of a modern low-aspect-ratio, high-through-flow, axial transonic fan is presented. Rotor flow fields were investigated at two clearance levels experimentally, at tip clearance to tip blade chord ratios of 0.27 and 1.87 percent, and at four clearance levels numerically, at ratios of zero, 0.27, 1.0, and 1.87 percent. The numerical method seems to calculate the rotor aerodynamics well, with some disagreement in loss calculation which might be improved with improved turbulence modeling and a further refined grid. Both the experimental and the numerical results indicate that the performance of this class of rotors is dominated by the tip clearance flows. Rotor efficiency drops six points when the tip clearance is increased from 0.27 to 1.87 percent, and flow range decreases about 30 percent. No optimum clearance size for the present rotor was indicated. Most of the efficiency change occurs near the tip section, with the interaction between the tip clearance flow and the passage shock becoming much stronger when the tip clearance is increased. In all cases, the shock structure was three-dimensional and swept, with the shock becoming normal to the endwall near the shroud.
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ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition
June 13–16, 1994
The Hague, Netherlands
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-7883-5
PROCEEDINGS PAPER
The Effect of Tip Clearance on a Swept Transonic Compressor Rotor
William W. Copenhaver,
William W. Copenhaver
Wright Laboratory, Wright Patterson AFB, OH
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Ellen R. Mayhew,
Ellen R. Mayhew
Wright Laboratory, Wright Patterson AFB, OH
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Chunill Hah
Chunill Hah
NASA Lewis Research Center, Cleveland, OH
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William W. Copenhaver
Wright Laboratory, Wright Patterson AFB, OH
Ellen R. Mayhew
Wright Laboratory, Wright Patterson AFB, OH
Chunill Hah
NASA Lewis Research Center, Cleveland, OH
Paper No:
94-GT-363, V001T01A124; 12 pages
Published Online:
February 18, 2015
Citation
Copenhaver, WW, Mayhew, ER, & Hah, C. "The Effect of Tip Clearance on a Swept Transonic Compressor Rotor." Proceedings of the ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. Volume 1: Turbomachinery. The Hague, Netherlands. June 13–16, 1994. V001T01A124. ASME. https://doi.org/10.1115/94-GT-363
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