Recent stall inception investigations have indicated that short-length scale stall initiates when the interface between the tip gap flow and the approach flow spills forward of the leading edge of the adjacent blade. This hypothesis was investigated in the present work using both numerical and experimental results from a range of compressor geometries and speed. First, full annulus unsteady computations of R35 were used to generate contours of entropy at the casing. It was found that a large gradient in entropy, which marked the leakage fluid, was aligned with the leading edge plane at the stalling mass flow. It was also observed that the flow direction in the region of increased entropy was in the reverse axial direction. The interface between the approach fluid and the reverse-direction leakage flow was related to a region in which the axial component of the wall shear stress was zero. The axial location of this line was measured experimentally using a surface streaking method using two separate facilities. It was found that the location of this line is determined by a momentum balance between the approach fluid and the tip leakage fluid. Measurements were acquired with varied tip clearance, radial distortion, and centerline offset to support these conclusions. In all cases the zero axial shear line was found to move upstream with decreased flow coefficient, and was in close proximity to the rotor leading edge at the stalling mass flow.
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ASME Turbo Expo 2008: Power for Land, Sea, and Air
June 9–13, 2008
Berlin, Germany
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4316-1
PROCEEDINGS PAPER
Investigation of Tip-Flow Based Stall Criteria Using Rotor Casing Visualization
Matthew A. Bennington,
Matthew A. Bennington
University of Notre Dame, Notre Dame, IN
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Joshua D. Cameron,
Joshua D. Cameron
University of Notre Dame, Notre Dame, IN
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Scott C. Morris,
Scott C. Morris
University of Notre Dame, Notre Dame, IN
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Camille Legault,
Camille Legault
University of Notre Dame, Notre Dame, IN
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Sean T. Barrows,
Sean T. Barrows
Ohio State University, Columbus, OH
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Jen-Ping Chen,
Jen-Ping Chen
Ohio State University, Columbus, OH
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G. Scott McNulty,
G. Scott McNulty
GE Aircraft Engines, Cincinnati, OH
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Aspi R. Wadia
Aspi R. Wadia
GE Aircraft Engines, Cincinnati, OH
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Matthew A. Bennington
University of Notre Dame, Notre Dame, IN
Joshua D. Cameron
University of Notre Dame, Notre Dame, IN
Scott C. Morris
University of Notre Dame, Notre Dame, IN
Camille Legault
University of Notre Dame, Notre Dame, IN
Sean T. Barrows
Ohio State University, Columbus, OH
Jen-Ping Chen
Ohio State University, Columbus, OH
G. Scott McNulty
GE Aircraft Engines, Cincinnati, OH
Aspi R. Wadia
GE Aircraft Engines, Cincinnati, OH
Paper No:
GT2008-51319, pp. 641-651; 11 pages
Published Online:
August 3, 2009
Citation
Bennington, MA, Cameron, JD, Morris, SC, Legault, C, Barrows, ST, Chen, J, McNulty, GS, & Wadia, AR. "Investigation of Tip-Flow Based Stall Criteria Using Rotor Casing Visualization." Proceedings of the ASME Turbo Expo 2008: Power for Land, Sea, and Air. Volume 6: Turbomachinery, Parts A, B, and C. Berlin, Germany. June 9–13, 2008. pp. 641-651. ASME. https://doi.org/10.1115/GT2008-51319
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