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Research Papers

3D Unsteady Simulation of a Modern High Pressure Turbine Stage Using Phase Lag Periodicity: Analysis of Flow and Heat Transfer

[+] Author and Article Information
Vikram Shyam

 NASA Glenn Research Center, Cleveland, OH 44135

Ali Ameri

 Ohio State University, Columbus, OH 43210; NASA Glenn Research Center, Cleveland, OH 44135

Daniel F. Luk, Jen-Ping Chen

 Ohio State University, Columbus, OH 43210

J. Turbomach 133(3), 031015 (Nov 16, 2010) (8 pages) doi:10.1115/1.4001235 History: Received August 24, 2009; Revised August 28, 2009; Published November 16, 2010; Online November 16, 2010

Unsteady 3D Reynolds-averaged Navier–Stokes (RANS) simulations have been performed on a highly loaded transonic turbine stage, and results are compared with steady calculations and experiments. A low Reynolds number k-ε turbulence model is employed to provide closure for the RANS system. A phase lag boundary condition is used in the tangential direction. This allows the unsteady simulation to be performed by using only one blade from each of the two rows. The objective of this paper is to study the effect of unsteadiness on rotor heat transfer and to glean any insight into unsteady flow physics. The role of the stator wake passing on the pressure distribution at the leading edge is also studied. The simulated heat transfer and pressure results agree favorably with the experiment. The time-averaged heat transfer predicted by the unsteady simulation is higher than the heat transfer predicted by the steady simulation everywhere, except at the leading edge. The shock structure formed, due to stator-rotor interaction, is analyzed. Heat transfer and pressure at the hub and casing are also studied. Thermal segregation is observed that leads to the heat transfer patterns predicted by steady and unsteady simulations to be different.

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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References

Figures

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Figure 9

Stanton number at various instances in time on the rotor blade

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Figure 10

Stanton number on rotor hub for steady (top) and time-average (bottom) of unsteady cases

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Figure 11

Stanton number on rotor casing for steady (top) and time-average (bottom) of unsteady cases

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Figure 12

Percent difference between steady and time-averaged Stanton number on rotor hub

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Figure 13

Percent difference between steady and time-averaged Stanton number on rotor casing

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Figure 14

Percent difference between steady and time-averaged pressure on rotor casing

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Figure 15

Percent difference between steady and time-averaged pressure on rotor hub

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Figure 8

Steady shock function at rotor midspan

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Figure 7

Unsteady shock function at various span locations and at several instances in time

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Figure 6

Streamlines over suction side of rotor, showing contours of Stanton number

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Figure 5

Comparison between (a) steady (8) and (b) time-averaged Stanton number distribution on rotor blade pressure side

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Figure 4

Pressure distribution on unfolded rotor blade surface: (a) steady and (b) time-averaged

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Figure 3

Pressure (left) and Stanton number (right) profiles at (a) 15%, (b) 50%, and (c) 90% span of rotor blade

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Figure 2

Boundary conditions

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