System and method for providing compressed air to a gas turbine combustor
A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts withi...
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Main Authors | , , |
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Format | Patent |
Language | English |
Published |
05.07.2022
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Subjects | |
Online Access | Get full text |
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Summary: | A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve. |
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Bibliography: | Application Number: US201816178768 |