Micro-Channel Cooling of Integrated Combustor Nozzle of a Segmented Annular Combustion System
First Claim
1. An integrated combustor nozzle, comprising:
- a fuel injection panel that extends radially between an inner liner segment and an outer liner segment, the fuel injection panel including a forward end portion, an aft end portion, a first side wall, a second side wall, a plurality of premixing channels defined between the first side wall and the second side wall, and a plurality of injection outlets defined along at least one of the first side wall and the second side wall, the aft end portion of the fuel injection panel defining a turbine nozzle;
wherein the inner liner segment defines a plurality of micro-channel cooling passages that extend between an inner surface and an outer surface of the inner liner segment, each micro-cooling passage having an inlet hole defined along the outer surface and a corresponding air outlet hole.
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Accused Products
Abstract
A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. The fuel injection panel includes an aft end portion, a first side wall, a second side wall, premixing channels defined between the first side wall and the side wall, and injection outlets defined along at least one of the first side wall and the second side wall. The aft end portion defines a turbine nozzle portion. An interior portion between the first side wall and the second side wall includes walls that extend between the first and second side walls, thereby partitioning the interior portion into discrete air cavities. The liner segments may be cooled by micro-channel cooling passages, which may be fluidly coupled to a collection trough.
19 Citations
18 Claims
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1. An integrated combustor nozzle, comprising:
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a fuel injection panel that extends radially between an inner liner segment and an outer liner segment, the fuel injection panel including a forward end portion, an aft end portion, a first side wall, a second side wall, a plurality of premixing channels defined between the first side wall and the second side wall, and a plurality of injection outlets defined along at least one of the first side wall and the second side wall, the aft end portion of the fuel injection panel defining a turbine nozzle; wherein the inner liner segment defines a plurality of micro-channel cooling passages that extend between an inner surface and an outer surface of the inner liner segment, each micro-cooling passage having an inlet hole defined along the outer surface and a corresponding air outlet hole. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. An integrated combustor nozzle, comprising:
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a fuel injection panel that extends radially between an inner liner segment and an outer liner segment, the fuel injection panel including a forward end portion, an aft end portion, a first side wall, a second side wall, a plurality of premixing channels defined between the first side wall and the second side wall and a plurality of injection outlets defined along at least one of the first side wall and the second side wall, the aft end portion of the fuel injection panel defining a turbine nozzle; wherein the outer liner segment defines a plurality of micro-channel cooling passages that extend between an inner surface and an outer surface of the outer liner segment, each micro-cooling passage having an inlet hole defined along the outer surface and a corresponding air outlet hole. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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Specification