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TECHNICAL PAPERS

Effect of the Hub Endwall Cavity Flow on the Flow-Field of a Transonic High-Pressure Turbine

[+] Author and Article Information
G. Paniagua, R. Dénos, S. Almeida

Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, Chaussée de Waterloo 72, B1640—Rhode Saint Genèse, Belgium

J. Turbomach 126(4), 578-586 (Dec 29, 2004) (9 pages) doi:10.1115/1.1791644 History: Received October 01, 2003; Revised March 01, 2004; Online December 29, 2004
Copyright © 2004 by ASME
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References

Figures

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Three-dimensional view of the turbine stage
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Turbine stage cross section with the disk cooling setup
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Three-dimensional view of the turbine stage grid: (a) blade-to-blade cut; (b) meridional plane cut, cavity upstream of the mixing plane; and (c) downstream
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Time-averaged distribution of the pitch-wise static pressure at the vane exit hub
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Flow field within the cavity: (a) Velocity vectors for −0.5% ingestion (at Stator pitch=1.1); (b) time averaged stream traces and static pressure contours across a vane pitch (at x/R0=0.0016); and (c) maximum and minimum static pressure as a function of the radius
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Time-resolved static pressure outside of the cavity: (a) at the vane exit, gauge at stator pitch=0.9; (b) gauge 1 on the rotor platform; and (c) gauge 2
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(a) Time-averaged stream traces and static pressure contours at the rotor platform; (b) measured static pressure
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Time-averaged rotor static pressure distribution at 15% span
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Isosurface of rothalpy (a- at Cp×353 K,b- at Cp×325 K) and contour plots of at the rotor trailing edge plane (c- for −0.5%, d- for +1.5%)
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Time-resolved blade force at 15% of the span for −0.5% and +1.5%
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Time-resolved axial force and torque on the rotor disk
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Measured time-averaged total pressure contours at the turbine exit
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Radial profiles pitch-wise averaged

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