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Research Papers

Aerothermal Study of the Unsteady Flow Field in a Transonic Gas Turbine With Inlet Temperature Distortions

[+] Author and Article Information
S. Salvadori, F. Martelli

Dipartimento di Energetica, Università degli Studi di Firenze, via di Santa Marta 3, 50139 Firenze, Italy

F. Montomoli1

Dipartimento di Energetica, Università degli Studi di Firenze, via di Santa Marta 3, 50139 Firenze, Italy

P. Adami2

Dipartimento di Energetica, Università degli Studi di Firenze, via di Santa Marta 3, 50139 Firenze, Italy

K. S. Chana

 QinetiQ, Cody Technology Park, Ively Road, Farnborough, Hants GU14 0LX, UK

L. Castillon

Department of Applied Aerodynamic, ONERA, 8 rue des Vertugadins, F-92190 Meudon, France

1

Present address: Whittle Laboratory, University of Cambridge, Cambridge CB2 1TN, UK.

2

Present address: Rolls-Royce plc, Derby DE248BJ, UK.

J. Turbomach 133(3), 031030 (Feb 28, 2011) (13 pages) doi:10.1115/1.4002421 History: Received December 29, 2009; Revised January 12, 2010; Published February 28, 2011; Online February 28, 2011

Computational fluid dynamics (CFD) prediction of the unsteady aerothermal interaction in the HP turbine stage, with inlet temperature nonuniformity, requires appropriate unsteady modeling and a low diffusive numerical scheme coupled with suitable turbulence models. This maybe referred to as high fidelity CFD. A numerical study has been conducted by the University of Florence in collaboration with ONERA to compare capabilities and limitations of their CFD codes for such flows. The test vehicle used for the investigation is a turbine stage of three-dimensional design from the QinetiQ turbine facility known as MT1. This stage is a high pressure transonic stage that has an unshrouded rotor, configured, and uncooled with 32 stators and 60 rotor blades. Two different CFD solvers are compared that use different unsteady treatments of the interaction. A reduced count ratio technique has been used by the University of Florence with its code HYBFLOW , while a phase lag model has been used by ONERA in their code, ELSA . Four different inlet conditions have been simulated and compared with focus on the experimental values provided by QinetiQ in the frame of TATEF and TATEF2 EU Sixth Framework Projects. The differences in terms of performance parameters and hot fluid redistribution, as well as the time- and pitch-averaged radial distributions on a plane downstream of the rotor blade, have been underlined. Special attention was given to the predictions of rotor blade unsteady pressure and heat transfer rates.

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Segregation effect for wakes and hot streaks

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Figure 2

Schematic of the TTF

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Figure 3

OTDF profiles: contour map at the stator inlet

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Figure 6

Isentropic Mach number—stator blade

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Figure 7

Static pressure—rotor blade

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Figure 8

Unsteady load on the rotor blade

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Figure 9

Nusselt number—stator (pres. side negative)

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Figure 10

Nusselt number—rotor (pres. side negative)

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Figure 11

Pressure and heat transfer probe position

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Figure 12

Pressure fluctuation in the overtip region

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Figure 13

Tip leakage vortex visualization

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Figure 14

Nusselt number fluctuations in the overtip region

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Figure 15

Yaw angle and Mach number distributions

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Figure 4

Scheme of the OTDF positions

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Figure 5

Rotor blade original and scaled geometry

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