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TECHNICAL PAPERS: Gas Turbines: Cycle Innovations

The Influence of In Situ Reheat on Turbine-Combustor Performance

[+] Author and Article Information
Steven Chambers, Horia Flitan

Department of Aerospace Engineering, Texas A&M University, College Station, TX 77843

Paul Cizmas1

Department of Aerospace Engineering, Texas A&M University, College Station, TX 77843

Dennis Bachovchin, Thomas Lippert

 Siemens-Westinghouse Power Corporation, Pittsburgh, PA 15235

David Little

 Siemens-Westinghouse Power Corporation, Orlando, FL 32826

1

To whom correspondence should be addressed.

J. Eng. Gas Turbines Power 128(3), 560-572 (Mar 01, 2004) (13 pages) doi:10.1115/1.2135812 History: Received October 01, 2003; Revised March 01, 2004

This paper presents a numerical and experimental investigation of the in situ reheat necessary for the development of a turbine-combustor. The flow and combustion were modeled by the Reynolds-averaged Navier-Stokes equations coupled with the species conservation equations. The chemistry model used herein was a two-step, global, finite rate combustion model for methane and combustion gases. A numerical simulation was used to investigate the validity of the combustion model by comparing the numerical results against experimental data obtained for an isolated vane with fuel injection at its trailing edge. The numerical investigation was then used to explore the unsteady transport phenomena in a four-stage turbine-combustor. In situ reheat simulations investigated the influence of various fuel injection parameters on power increase, airfoil temperature variation, and turbine blade loading. The in situ reheat decreased the power of the first stage, but increased more the power of the following stages, such that the power of the turbine increased between 2.8% and 5.1%, depending on the parameters of the fuel injection. The largest blade excitation in the turbine-combustor corresponded to the fourth-stage rotor, with or without combustion. In all cases analyzed, the highest excitation corresponded to the first blade passing frequency.

Copyright © 2006 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Experimental setup for a single-vane burner

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Figure 2

Detail of the computational domain of the single-vane burner

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Figure 3

Detail of the single-vane burner grid

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Figure 4

Contour plots of methane mass fraction

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Figure 5

Contour plots of methane mass fraction at x=constant planes

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Figure 6

Contour plots of carbon monoxide mass fraction

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Figure 7

Contour plots of carbon monoxide mass fraction at x=constant planes

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Figure 8

Contour plots of total temperature

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Figure 9

Contour plots of total temperature at x=constant planes

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Figure 10

Detail of the medium grid (every other grid point in each direction shown)

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Figure 11

Variation of averaged total enthalpy (absolute or relative)

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Figure 12

Variation of stagnation temperature along first row of rotors for the case without combustion and case 1 of in situ reheat

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Figure 13

Contour plots of methane mass fraction (case 1, first three stages)

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Figure 14

Contour plots of oxygen mass fraction (case 1, first three stages)

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Figure 15

Variation of tangential forces on the rotors

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Figure 16

Fast Fourier transform of tangential forces

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