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Gas Turbines: Cycle Innovations

Evaluation of Design Performance of the Semi-Closed Oxy-Fuel Combustion Combined Cycle

[+] Author and Article Information
H. J. Yang, D. W. Kang, J. H. Ahn

Graduate School,  Inha University, Incheon, 402-751 Korea

T. S. Kim

Department of Mechanical Engineering,  Inha University, Incheon, 402-751 Koreakts@inha.ac.kr

J. Eng. Gas Turbines Power 134(11), 111702 (Sep 28, 2012) (10 pages) doi:10.1115/1.4007322 History: Received June 18, 2012; Revised June 29, 2012; Published September 28, 2012; Online September 28, 2012

This study aims to present various design aspects and realizable performance of the natural gas fired semi-closed oxy-fuel combustion combined cycle (SCOC-CC). The design parameters of the cycle are set up on the basis of the component technologies of today’s state-of-the-art gas turbines with a turbine inlet temperature between 1400 °C and 1600 °C. The most important part of the cycle analysis is the turbine cooling, which considerably affects the cycle performance. A thermodynamic cooling model is introduced in order to predict the reasonable amount of turbine coolant needed to maintain the turbine blade temperature of the SCOC-CC at the levels of those of conventional gas turbines. The optimal pressure ratio ranges of the SCOC-CC for two different turbine inlet temperature levels are researched. The performance penalty due to the CO2 capture is examined. The influences of the purity of the oxygen provided by the air separation unit on the cycle performance are also investigated. A comparison with the conventional combined cycle, adopting a postcombustion CO2 capture, is carried out, taking into account the relationship between the performance and the CO2 capture rate.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic diagram of the SCOC-CC system

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Figure 2

Efficiency versus the specific power chart for the SCOC-CC using the 1400 °C class gas turbine

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Figure 3

Variations in the compressor discharge temperature and turbine exhaust temperature with the pressure ratio (1400 °C class)

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Figure 4

Cooling effectiveness of the 1st stage nozzle blade (1400 °C class)

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Figure 5

Variations in the total coolant fraction (total coolant divided by compressor inlet air) with the pressure ratio (1400 °C class)

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Figure 6

Variations in the nozzle blade temperatures with the pressure ratio (1400 °C class)

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Figure 7

Efficiency versus the specific power chart for the SCOC-CC using the 1600 °C class gas turbine

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Figure 8

Schematic diagram of the conventional CC with a postcombustion CO2 capture

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Figure 9

Variations in reboiler heat demand, steam turbine power, and net cycle efficiency with the absorption capture rate (1400 °C class; PR 18)

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