Operation and Turndown of a Segmented Annular Combustion System
First Claim
1. A method for operating a segmented annular combustion system, comprising:
- injecting a first combustible mixture into a primary combustion zone defined between a pair of circumferentially adjacent integrated combustor nozzles of the segmented annular combustion system via a fuel nozzle;
burning the first combustible mixture in the primary combustion zone to produce a flow of combustion gases;
flowing compressed air into a first premixing channel defined within a first integrated combustor nozzle of the pair of circumferentially adjacent integrated combustor nozzles;
injecting fuel into the first premixing channel such that the fuel mixes with the compressed air to provide a second combustible mixture;
injecting the second combustible mixture from the first premixing channel into a secondary combustion zone downstream from the primary combustion zone, the second combustible mixture burning in the secondary combustion zone and combining with the flow of combustion gases from the primary combustion zone; and
accelerating the flow of combustion gases toward a plurality of turbine blades, via a turbine nozzle portion of each integrated combustor nozzle.
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Accused Products
Abstract
The present disclosure is directed to the operation and turndown of a segmented annular combustion system. The method includes injecting, via a fuel nozzle, a combustible mixture into a primary combustion zone between an adjacent pair of integrated combustor nozzles and burning the combustible mixture. The method further includes flowing air and injecting fuel into a premixing channel defined within a first integrated combustor nozzle to produce a second combustible mixture. The second combustible mixture is injected into a secondary combustion zone where it is combusted. The flow of combustion gases is accelerated, via turbine nozzles of the integrated combustor nozzles, toward turbine blades of a downstream turbine section. The method permits turndown of the combustion system by reducing or shutting off fuel to various components of the combustion system.
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Citations
30 Claims
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1. A method for operating a segmented annular combustion system, comprising:
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injecting a first combustible mixture into a primary combustion zone defined between a pair of circumferentially adjacent integrated combustor nozzles of the segmented annular combustion system via a fuel nozzle; burning the first combustible mixture in the primary combustion zone to produce a flow of combustion gases; flowing compressed air into a first premixing channel defined within a first integrated combustor nozzle of the pair of circumferentially adjacent integrated combustor nozzles; injecting fuel into the first premixing channel such that the fuel mixes with the compressed air to provide a second combustible mixture; injecting the second combustible mixture from the first premixing channel into a secondary combustion zone downstream from the primary combustion zone, the second combustible mixture burning in the secondary combustion zone and combining with the flow of combustion gases from the primary combustion zone; and accelerating the flow of combustion gases toward a plurality of turbine blades, via a turbine nozzle portion of each integrated combustor nozzle. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30)
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Specification