An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Axial Compression Systems

[+] Author and Article Information
Keith M. Boyer

Department of Aeronautics, USAF Academy, CO 80840-6222e-mail: keith.boyer@usafa.af.mil

Walter F. O’Brien

Mechanical Engineering Department, Virginia Tech, Blacksburg, VA 24061-0238e-mail: walto@vt.edu

J. Turbomach 125(3), 475-481 (Aug 27, 2003) (7 pages) doi:10.1115/1.1565085 History: Received October 22, 2001; Online August 27, 2003
Copyright © 2003 by ASME
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Rotor 1B radial loss prediction
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R1B radial deviation at peak efficiency
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R1B overall performance comparison at 100% Nc
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Use of shock angle at sonic point for loss estimation—(a) M=1.2, SAavg=68.1 deg,MA=56.4 deg, (b) M=1.5, SAavg=62.3 deg,MA=41.8 deg
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Assumed shock structure at different operating conditions—(a) modified (current) shock model (b) original shock model 22
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Approximate loss source distribution in highly transonic fan blade section (M1rel>1.4)
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Shock structure of high tip-speed fans −M1rel>1.4 (from 11)
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Blade section shock loss comparison at different loadings—(a) 5% from TE tip casing, (b) 20% from TE tip casing
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Prediction of loss attributed to detached bow shock—(a) 5% from TE tip casing, (b) 20% from TE tip casing




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