초록 ▼

A dome assembly for a single annular combustor of a gas turbine engine is disclosed as having a first dome wall in flow communication with compressed air supplied to the combustor, the first dome wall including a central opening therein and at least one cooling passage therethrough. A baffle is spac

A dome assembly for a single annular combustor of a gas turbine engine is disclosed as having a first dome wall in flow communication with compressed air supplied to the combustor, the first dome wall including a central opening therein and at least one cooling passage therethrough. A baffle is spaced downstream of and connected to the first dome wall at radially outward and inward ends, the baffle also including a central opening therein. A second dome wall defining the central opening in the first dome wall is provided which extends upstream of the first dome wall. A venturi is located within the central opening of the first dome wall, with the venturi including a flange extending radially outward from the central opening, wherein the second dome wall is connected to the flange at an upstream end. A flare cone is located within the central opening of the baffle and radially outward of the venturi, wherein a substantially radial passage is provided between the venturi flange and the flare cone, the radial passage having a swirler located therein. Accordingly, a chamber is formed by the first dome wall, the second dome wall, the baffle, the venturi, and the flare cone, the chamber being in flow communication with the compressed air entering the combustor by means of the cooling passage in the first dome wall, whereby the compressed air impinges on the baffle, circulates in the chamber, and exits through the swirler. In addition, a circumferential row of cooling passages is preferably located in the baffle adjacent the flare cone and rows of cooling passages are also located at both the radially outward and inward ends of the baffle.

대표청구항 ▼

A dome assembly for a single annular combustor of a gas turbine engine comprising a plurality of modules, each of said modules further comprising: (a) a first dome wall in flow communication with compressed air supplied to said combustor, said first dome wall including a central opening therein and

A dome assembly for a single annular combustor of a gas turbine engine comprising a plurality of modules, each of said modules further comprising: (a) a first dome wall in flow communication with compressed air supplied to said combustor, said first dome wall including a central opening therein and at least one cooling passage therethrough; (b) a baffle spaced downstream of and connected to said first dome wall at radially outward and inward ends, said baffle including a central opening therein; (c) a second dome wall defining said central opening in said first dome wall, said second dome wall extending upstream of said first dome wall; (d) a venturi located within said central opening of said first dome wall, said venturi including a flange extending radially outward from said central opening, wherein said second dome wall is connected to said flange at an upstream end; (e) a flare cone located within said central opening of said baffle and radially outward of said venturi, wherein a substantially radial passage is provided between said venturi flange and said flare cone; and (f) a swirler located within said radial passage; wherein a chamber is formed by said first dome wall, said second dome wall, said baffle, said venturi, and said flare cone, said chamber being in flow communication with said compressed air by means of said cooling passage in said first dome wall, whereby said compressed air impinges on said baffle and circulates through said swirler.