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公开(公告)号：US11371706B2
公开(公告)日：2022-06-28
申请号：US15845338
申请日：2017-12-18
Applicant: General Electric Company
Inventor： James Harper , Neal William Grooms , Yon Han Chong , Benjamin Robert Ryan
Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
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公开(公告)号：US20190178497A1
公开(公告)日：2019-06-13
申请号：US15838172
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , James Harper , Matthew Bernard Wilson , Robert Wade Clifford , Yon Han Chong , Benjamin Robert Ryan , Gilbert Otto Kraemer
Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.
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公开(公告)号：US11187415B2
公开(公告)日：2021-11-30
申请号：US15838172
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , James Harper , Matthew Bernard Wilson , Robert Wade Clifford , Yon Han Chong , Benjamin Robert Ryan , Gilbert Otto Kraemer
Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.
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公开(公告)号：US20190186749A1
公开(公告)日：2019-06-20
申请号：US15845338
申请日：2017-12-18
Applicant: General Electric Company
Inventor： James Harper , Neal William Grooms , Yon Han Chong , Benjamin Robert Ryan
CPC classification number: F23R3/286 , F02C3/30 , F05D2240/35 , F05D2260/212 , F23D14/58 , F23R3/343
Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
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