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TECHNICAL PAPERS

Aerodynamic Performance of a Transonic Turbine Cascade at Off-Design Conditions

[+] Author and Article Information
D. B. M. Jouini, S. A. Sjolander

Department of Mechanical & Aerospace Engineering, Carleton University, Ottawa, Ontario, Canada

S. H. Moustapha

Pratt & Whitney Canada Inc., Longueuil, Quebec, Canada

J. Turbomach 123(3), 510-518 (Feb 01, 2000) (9 pages) doi:10.1115/1.1370157 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

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Whitehouse,  D. R., Moustapha,  S. H., and Sjolander,  S. A., 1993, “The Effects of Axial Velocity Ratio, Turbulence Intensity, Incidence, and Leading Edge Geometry on the Mid-Span Performance of a Turbine Cascade,” Can. Aeronautics Space J., 39, pp. 150–156.
Benner,  M. W., Sjolander,  S. A., and Moustapha,  S. H., 1997, “Influence of Leading-Edge Geometry on Profile Losses in Turbines at Off-Design Incidence: Experimental Results and an Improved Correlation,” ASME J. Turbomach., 119, April pp. 193–200.
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Figures

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Carleton University blowdown wind tunnel 14.
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Plan view of the cascade test section
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Summary of the blade geometry and nomenclature
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Cascade blade row measurement locations
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(a) Cascade downstream total pressure at off-design incidence, i−ides=4.5 deg; (b) cascade downstream flow angle at off-design incidence, i−ides=4.5 deg
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Effects of incidence and Mach number on the axial velocity density ratio (AVDR)
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(a)Effects of the Mach number on blade loading at −10.0 deg off-design incidence; (b) effects of Mach number on blade loading at design incidence; (c) effects of Mach number on blade loading at +10.0 deg off-design incidence
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Effects of incidence on blade loading near the design Mach number
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Comparison between measured base pressures and the correlation of Sieverding et al.
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Variation of the base pressure coefficient
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(a) Effects of Mach number and incidence on losses; (b) effects of off-design incidence on losses at different Mach numbers
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Reynold’s numbers effects on losses at M2=0.56,ieffective=4.5 deg
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Effects of incidence and the Mach number on the exit flow angle

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