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Research Papers

Integrated Combustor and Vane Concept in Gas Turbines

[+] Author and Article Information
Budimir Rosic

Osney Laboratory, Oxford University, Oxford OX1 3PJ, UKbudimir.rosic@eng.ox.ac.uk

John D. Denton, John H. Horlock

Whittle Laboratory, Cambridge University, Cambridge CB3 0DY, UK

Sumiu Uchida

 Mitsubishi Heavy Industries Ltd., Takasago R&D Center, 2-1-1 Shinhama, Arai-Cho, Takasago, Hyogo, Japan

J. Turbomach 134(3), 031005 (Jul 14, 2011) (10 pages) doi:10.1115/1.4003023 History: Received June 28, 2010; Revised June 29, 2010; Published July 14, 2011; Online July 14, 2011

This paper numerically investigates the interaction between multiple can combustors and the first vane in an industrial gas turbine with 16 can combustors and 32 vanes in order to find ways of reducing the overall cooling requirements. Two promising concepts for the overall cooling reduction are presented. In the first, by minimizing the axial distance between the combustor wall and the vane, the stagnation region at the leading edge (LE) of every second vane can be effectively shielded from the hot mainstream gases. The LE shielding allows continuous cooling slots to be used (as an alternative to discrete cooling holes) to cool the downstream parts of the vane using a portion of the saved LE showerhead cooling air. The second concept proposes a full combustor and first vane integration. In this novel concept the number of vanes is halved and the combustor walls are used to assist the flow turning. All remaining vanes are fully integrated into the combustor walls. In this way the total wetted area of the integrated system is reduced, and by shielding the LEs of the remaining vanes the total amount of cooling air can be reduced. The proposed combustor and first vane integration does not detrimentally affect the aerodynamics of the combustor and vane system. The concept also simplifies the design and should lower the manufacturing costs.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic of an industrial gas turbine with multiple combustors and the first turbine vane

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Figure 2

Flow domain used to model LE film cooling

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Figure 3

Instantaneous y-vorticity contours at the central plane

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Figure 4

Predicted time averaged adiabatic cooling effectiveness contours at the LE top wall (without and with upstream wake)

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Figure 5

Static pressure and y-vorticity contours at the cylindrical LE for three different upstream geometries

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Figure 6

Schematic of the flow domain with the minimized axial distance between the combustor wall and LE (LE shielding)

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Figure 7

Comparison of predicted time averaged adiabatic cooling effectiveness for shielded (slot film cooled) and data (discrete film hole cooled) LEs

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Figure 8

Schematic of data configuration (with separated combustor and first vane) and configuration with shielded first vane LE

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Figure 9

Computational flow domain used to simulate vane LE shielding concept

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Figure 10

Predicted time averaged adiabatic cooling effectiveness contours at the vane pressure side

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Figure 11

Predicted time averaged adiabatic cooling effectiveness contours at the vane suction side

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Figure 12

Total pressure distribution downstream of the vane TE for the (a) data configuration and (b) shielded vane LE

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Figure 13

Yaw angle distribution downstream of the vane TE for the (a) data configuration and (b) shielded vane LE

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Figure 14

Combustor and vane integration development

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Figure 17

Static pressure contours through the combustor and first vane for (a) data configuration and (b) ICV

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Figure 18

Streamlines at the midspan and hub in the case of data configuration with separated combustor and vane

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Figure 19

Streamlines at the midspan and hub in the case of ICV

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Figure 20

Yaw angle distribution downstream of the vane TE for the (a) data configuration and (b) ICV

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Figure 21

Total pressure distribution downstream of the vane TE for the (a) data configuration and (b) ICV

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