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TECHNICAL PAPERS

Kinematic Analysis of 3-D Swept Shock Surfaces in Axial Flow Compressors

[+] Author and Article Information
Peng Shan

Department of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, P. R. Chinae-mail: PShan@buaa.edu.cn

J. Turbomach 123(3), 490-500 (Feb 01, 2000) (11 pages) doi:10.1115/1.1370159 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Figures

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The leading edge spatial curve and helical surface model (HSM) generated on it
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Definitions of six kinds of frequently used shock sweep angles
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The jump of a shock’s N , the left-running shock’s appellation
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The meaning of the sweep vector Nrc with its components Sr and Sc of a 3-D shock surface and the relation of the sweep vector to the normal vector
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One plan to use a one-point–two-directions scheme of shock structure measurement
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Principle of a two-points–one-direction scheme of shock structure measurement
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Through flow calculating station, streamline, overall design data of ATS-2 single stage backward swept fan Rotation speed21500rpmUnit mass flow (By CFD)173.08kg/m2/sUnit annular mass flow208.66kg/m2/sMass flow26.32kg/sPressure ratio2.252Adiabatic efficiency0.8855Diameter0.44m
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Leading edge shock surface and three of its planar projections of ATS-2 fan’s rotor Tip speed of leading edge495.32 m/s, M1.661, positive ηBlade numbers14Leading edge total span r0.09080∼0.22 mLeading edge shock span ra: 0.1216∼b: 0.22 mShock runningroot right∼tip left
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Distributions of the sweep vector Nrc of two rotors’ leading edge shock surfaces
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Distributions of three major sweep variables of ATS-2 fan’s leading edge shock surface
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Leading edge shock surface and three of its planar projections of the HTFC’s rotor Tip speed of leading edge457.2 m/s, M1.658, positive ηBlade numbers20Leading edge total span r2.65∼8.50 inchLeading edge shock span ra: 4.75∼b:8.50 inchShock running (Defined by frame in Fig. 1)root right∼tip left
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Distributions of three major sweep variables of the HTFC’s leading edge shock surface
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The projection angle γF of the angle γ (included between two planes) onto the third plane F

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