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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Combustion Characteristics of a Can Combustor With a Rotating Casing for an Innovative Micro Gas Turbine

[+] Author and Article Information
Hsin-Yi Shih1

Department of Mechanical Engineering, Chang Gung University, Taoyuan 333, Taiwanhyshih@mail.cgu.edu.tw

Chi-Rong Liu

Department of Mechanical Engineering, Chang Gung University, Taoyuan 333, Taiwan

1

Corresponding author.

J. Eng. Gas Turbines Power 131(4), 041501 (Apr 15, 2009) (8 pages) doi:10.1115/1.3043807 History: Received June 05, 2008; Revised July 07, 2008; Published April 15, 2009

A can type combustor with a rotating casing for an innovative micro gas turbine has been modeled, and the combustion characteristics were investigated. The simulations were performed using commercial code STAR-CD , in which a three-dimensional compressible k-ε turbulent flow model and a one-step overall chemical reaction between methane/air were used. The results include the detailed flame structure at different rotation speeds of outside casing, ranging from stationary to the maximum speed of 58,000 rpm of the design point. The airflows are baffled when entering the combustor through the linear holes due to the centrifugal force caused by the rotating casing, and the inlet flow angle is inclined. When the rotation is in the opposite direction of the swirling flows driven by the designed swirler, a shorter but broader recirculation zone and a concave shape flame are found at a higher rotating speed. At maximum rotating speed, the swirling flows are dominated by the rotating flows caused by the casing, especially downstream of the combustor. The combustor performance was also analyzed, indicating a higher combustion efficiency and higher exit temperature when the casing rotates, which benefits the performance of the gas turbine, but the cooling and possible hot spots for turbines are the primary concerns.

Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

The schematic of innovative rotor shaft structures

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Figure 2

The schematic of the proposed innovative micro gas turbine

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Figure 3

The designed can combustor inside the rotating shaft

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Figure 4

The grid structure and the combustor liner represented by a baffle

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Figure 5

The velocity profiles on the axial centerline for 0 rpm (top) and 58,000 rpm (bottom)

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Figure 6

The velocity profiles on the radial planes through the primary holes for 0 rpm (top) and 58,000 rpm (bottom)

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Figure 7

The three-dimensional combustion simulation of the combustor

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Figure 8

The temperature profiles on the centerline planes for 0 rpm, 20,000 rpm, 40,000 rpm, and 58,000 rpm (from top to bottom)

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Figure 9

The velocity profiles on the centerline planes for 0 rpm (top) and 58,000 rpm (bottom)

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Figure 10

The velocity profiles on radial planes through the primary holes for 0 rpm (top) and 58,000 rpm (bottom)

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Figure 11

The temperature and velocity profiles on the centerline plane at −58,000 rpm

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Figure 12

The exit temperature and combustion efficiency of the combustor

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Figure 13

Pattern factor and pressure drop of the combustor

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Figure 14

The exit temperature distribution at 0 rpm

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Figure 15

The exit temperature distribution at 58,000 rpm

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