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Research Papers

Radial Migration of Shed Vortices in a Transonic Rotor Following a Wake Generator: A Comparison Between Time Accurate and Average Passage Approaches

[+] Author and Article Information
Mark G. Turner

University of Cincinnatimark.turner@uc.edu

Steven E. Gorrell

Brigham Young University

David Car

Air Force Research Laboratory,Wright-Patterson Air Force Base

J. Turbomach 133(3), 031018 (Nov 18, 2010) (9 pages) doi:10.1115/1.4001241 History: Received September 23, 2009; Revised November 24, 2009; Published November 18, 2010; Online November 18, 2010

This paper shows a comparison of an unsteady simulation using turbo and an average passage simulation for a two blade row configuration consisting of a wake generator followed by a transonic rotor. Two spacings were simulated, both close and far. The unsteady results compare well with experiment especially for the profile of efficiency difference between close and far. An analysis of results helps to explain the unusual profile seen experimentally that is due to the radial migration of wake generator shed vortices with negative radial velocities near the tip. In addition, different components of the average passage body forces (deterministic stresses) are explored that shows the main terms are the axial momentum and the metal blockage.

Copyright © 2011This material is declared a work of the US government and is not subject to copyright protection in the United States. Approved for public release; distribution is unlimited.
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Figures

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Figure 1

SMI geometry for two blade row configuration (no stator)

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Figure 2

Grid extent for close and far simulations

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Figure 3

IGV grid with detail at leading and trailing edges (close is 61×71×138 in the blade-to-blade, radial, and axial directions, LE is 31, TE is 111, and No. of blades=24). Spanwise location of 2D sections are at j=35 or 71.6% span.

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Figure 4

Rotor grid in all configurations with detail at leading and trailing edges. (81×71×189 in the blade-to-blade, radial, and axial directions, LE is 19, TE is 99, No. of blades=33). Spanwise location of 2D sections are at j=35 or approximately 71% span. Notice the fillets in the grid at the hub.

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Figure 5

Static pressure at hub and casing comparing turbo and APNASA simulations with experiment

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Figure 6

Area averaged total pressure and total temperature ratio profiles of turbo and APNASA simulations compared with experiment for close and far spacings

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Figure 7

Efficiency profiles of turbo simulation compared with experiment for close and far spacing at 14 kg/s flow

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Figure 8

Efficiency Profiles of APNASA simulation compared with experiment for close and far spacings at 14 kg/s flow

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Figure 9

Efficiency difference profiles of turbo and APNASA simulations compared with experiment for close and far spacings at 14 kg/s flow

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Figure 10

Rothalpy profiles of turbo and APNASA simulations for close and far spacing at 14 kg/s flow

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Figure 11

Contours of the time-mean axisymmetric-average rotor solution in the close and far configuration. Same scales are used for close and far. Loss hole shows up as high entropy, rothalpy, and blockage.

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Figure 12

Contours of the time-mean rotor solution in the close configuration at the 65% span plane (j=35)

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Figure 13

Contours of an instantaneous rotor solution (time=3/4 period) in the close configuration

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Figure 14

Radial Velocity contours on a Radial Vorticity isosurface of the t=3/4 rotor solution in the close configuration. Clearly seen are the shed vortex and the tip vortex. The radial velocities are negative in the vortex near the tip. View is forward looking aft down midpassage.

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Figure 15

Axisymmetric projection of the particle paths in the rotor for the turbo simulation of the close configuration. Particles were released near the tip just upstream of the leading edge and in the path of the pressure side shed vortex. A total of 55 solution files were used for one IGV wake-passing period representing every fourth iteration. Some of the particles do not appear to go all the way downstream. Those left the domain of the single rotor passage.

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Figure 16

Contours of deterministic stress terms for the close turbo simulation. These are net body forces in the rotor frame of reference.

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Figure 17

Contours of relative Mach number for different APNASA runs at the 65% span plane (j=35). The metal blockage impacts the upstream shock angle as shown.

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