General Electric Company

Varun Swaminathan Lakshmanan

Michael Anthony Benjamin

Perumallu Vukanti

Pradeep Naik

Steven Clayton Vise

Michael Terry Bucaro

Karthikeyan Sampath

Veeraraju Vanapalli

Kwanwoo Kim

Allen Michael Danis

Sripathi Mohan

Gurunath Gandikota

Vivekta Sharma

A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.

Combustor with dilution openings

A flare cone for a mixer assembly includes an annular conical wall extending circumferentially about a mixer assembly centerline, the annular conical wall including a conical inner surface defining a conical opening of the annular conical wall, and an annular axial wall extending in a longitudinal direction with respect to the mixer assembly centerline, the annular axial wall disposed at a radially outward portion of the annular conical wall and connected to the annular conical wall. The annular conical wall and the annular axial wall define an annular step circumferentially about the mixer assembly centerline and extending upstream in the longitudinal direction between a downstream end of the annular conical wall and an aft surface of the annular axial wall.

Flare cone for a mixer assembly of a gas turbine combustor

A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.

Combustor dilution hole

A fuel injector heat exchanger assembly is provided, in which the fuel injector assembly includes a body defining an outer surface and an inner surface. The body includes a plurality of walls in concentric arrangement. The plurality of walls defines a plurality of passages including a first passage surrounded by a second passage, and a third passage surrounding the second passage. Each passage is fluidly segregated from one another by the plurality of walls. A first conduit wall is defined through the body from the outer surface. The first conduit wall defines a first conduit in fluid communication with the second passage. The first conduit wall fluidly segregates the first conduit from the third passage. The first conduit is configured to admit a flow of fluid from outside the fuel injector into the second passage.

Fuel injector heat exchanger assembly

A turbo machine including a heat exchanger flowpath is generally provided. The turbo machine includes an outer casing extended along an axial direction, a prediffuser defining an inlet passage into a combustion section of the turbo machine, an inner casing extended from the prediffuser, in which a diffuser cavity is defined between the outer casing and the inner casing, a first plenum wall extended outward along a radial direction from the prediffuser, and a second plenum wall extended outward along a radial direction from the prediffuser. The second plenum wall is separated along the axial direction from the first plenum wall. A plenum is defined between the first plenum wall and the second plenum wall. The turbo machine includes a heat exchanger including a first conduit in fluid communication with the diffuser cavity. The first conduit is in fluid communication with a passage, and a second conduit in fluid communication with the passage and the plenum. A flow of working fluid is admitted from the diffuser cavity through the heat exchanger to the plenum via the first conduit, the passage, and the second conduit.

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Bengaluru, India

Varun Swaminathan Lakshmanan