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TECHNICAL PAPERS

An Investigation of Wake-Shock Interactions in a Transonic Compressor With Digital Particle Image Velocimetry and Time-Accurate Computational Fluid Dynamics

[+] Author and Article Information
Steven E. Gorrell, David Car, Steven L. Puterbaugh

 Air Force Research Laboratory, AFRL/PRTF, Bldg. 18, Wright-Patterson AFB, OH 45433

Jordi Estevadeordal

 Innovative Scientific Solutions, Inc., 2766 Indian Ripple Road, Dayton, OH 45440

Theodore H. Okiishi

College of Engineering, 104 Marston Hall, Iowa State University, Ames, IA 50011

J. Turbomach 128(4), 616-626 (Feb 01, 2005) (11 pages) doi:10.1115/1.2220049 History: Received October 01, 2004; Revised February 01, 2005

The effects of varying axial gap on the unsteady flow field between the stator and rotor of a transonic compressor stage are important because they can result in significant changes in stage mass flow rate, pressure rise, and efficiency. Some of these effects are analyzed with measurements using digital particle image velocimetry (DPIV) and with time-accurate simulations using the 3D unsteady Navier-Stokes computational fluid dynamics solver TURBO. Generally there is excellent agreement between the measurements and simulations, instilling confidence in both. Strong vortices of the wake can break up the rotor bow shock and contribute to loss. At close spacing vortices are shed from the trailing edge of the upstream stationary blade row in response to the unsteady, discontinuous pressure field generated by the downstream rotor bow shock. Shed vortices increase in size and strength and generate more loss as spacing decreases, a consequence of the effective increase in rotor bow shock strength at the stationary blade row trailing edge. A relationship for the change in shed vorticity as a function of rotor bow shock strength is presented that predicts the difference between close and far spacing TURBO simulations.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 5

Entropy flux contours at close spacing, 75% span from 2002 simulation (2) (466,293 nodes)

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Figure 9

TURBO/DPIV velocity magnitude comparison across shock, close spacing

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Figure 4

Laser-sheet spanwise locations for 24-WG configuration with respect to the blade clockings (delays/locations)

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Figure 11

TURBO close spacing entropy flux contours for operating point A of Fig. 2, rotor at 34% above wake generator pitch

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Figure 12

DPIV far spacing velocity magnitude contours for operating point B of Fig. 2, rotor at 13% above wake generator pitch

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Figure 13

TURBO far spacing velocity magnitude contours for operating point B of Fig. 2, rotor at 13% above wake generator pitch

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Figure 14

TURBO/DPIV velocity magnitude comparison across shock, far spacing

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Figure 15

Far spacing flow visualization for operating point B of Fig. 2, rotor at 13% above wake generator pitch

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Figure 16

TURBO far spacing entropy flux contours for operating point B of Fig. 2, rotor at 13% above wake generator pitch

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Figure 17

DPIV far spacing with convection velocity subtracted for operating point B of Fig. 2, rotor at 13% above wake generator pitch

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Figure 18

TURBO close spacing entropy flux contours for operating point A of Fig. 2, constant 75% span

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Figure 19

TURBO far spacing entropy flux contours for operating point C of Fig. 2, constant 75% span

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Figure 20

Sketch defining relationship between interaction and vortex generation

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Figure 21

TURBO comparison of close and far spacing shed vortices for operating points A and C of Fig. 2, 70% span

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Figure 22

TURBO close spacing vorticity magnitude contours and static pressure rise across bow shock for operating point A of Fig. 2

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Figure 3

Illustration of DPIV measurement area

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Figure 2

Wake generator/rotor only performance, 100% Nc

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Figure 1

Stage matching investigation rig layout

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Figure 6

Entropy flux contours at close spacing, 75% span from present simulation (1,684,617 nodes)

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Figure 7

DPIV close spacing velocity magnitude contours for operating point A of Fig. 2, rotor at 34% above wake generator pitch

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Figure 8

TURBO close spacing velocity magnitude contours for operating point A of Fig. 2, rotor at 34% above wake generator pitch

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Figure 10

Close spacing flow visualization for operating point A of Fig. 2, rotor at 34% above wake generator pitch

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