A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. At least one of the outer liner and the inner liner has an upstream liner portion and a downstream liner portion with an annular gap therebetween. At least one dilution flow assembly is arranged to bridge across the annular gap. The at least one dilution flow assembly includes an upstream liner panel and a downstream liner panel with a dilution opening provided between the upstream liner panel and the downstream liner panel, and a plurality of dilution fence members arranged within the dilution opening and extending into a combustion chamber. The plurality of dilution fence members are arranged in successive arrangement in a circumferential direction and are arranged such that successive dilution fence members are alternatingly offset in an axial direction.

A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

Disclosed is a fuel mixed injection method for a gas turbine. The method includes the following steps: arranging a secondary fuel injection nozzle and a secondary air injection nozzle on a secondary combustion section, wherein the secondary fuel injection nozzles is closer to a main combustion section than the secondary air injection nozzle; and injecting secondary fuel and secondary primary air in sequence through the secondary fuel injection nozzle and the secondary air injection nozzle, respectively, thus enabling the secondary fuel to spontaneously combust in a mainstream high-temperature flue gas atmosphere to form a transverse jet flame and increase the flame lift-off height.

A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.

A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.

A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor liner, a dome assembly coupled to the combustor liner, a fuel nozzle fluidly coupled to the dome assembly, a combustion chamber fluidly coupled to the fuel nozzle, and at least one set of dilution openings located in the dome assembly or combustor liner that fluidly couple to the combustion chamber. A swirler can define at least one passage extending between at least one annular entrance and at least one annular exit, wherein the at least one annular entrance is fluidly coupled to the compressor section. A variable area device is movable relative to the at least one set of dilution openings or at least a portion of the swirler.

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.

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.

A combustor nozzle using fuel containing hydrogen, a combustor and gas turbine including the same are provided. The nozzle for a combustor configured to burn fuel containing hydrogen includes a fuel supply duct including a plurality of injection tubes through which air and fuel flow and a fuel passage through which fuel flows, a plurality of swirlers formed on a side surface of each of the plurality of injection tubes to guide air outside the injection tube to be introduced thereinto for swirling, and a plurality of fuel inlet holes formed radially through the injection tube to communicate with the fuel passage and allow fuel to flow through the fuel passage to the injection tube.