公开(公告)号：US10605459B2

公开(公告)日：2020-03-31

申请号：US15464419

申请日：2017-03-21

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Stanley Kevin Widener ,  Michael John Hughes ,  Matthew Troy Hafner ,  Joseph Vincent Citeno

IPC: F23R3/34 ,  F23R3/28 ,  F23R3/50 ,  F01D9/04 ,  F02C7/18 ,  F02C7/24

Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.

公开(公告)号：US10584876B2

公开(公告)日：2020-03-10

申请号：US15464431

申请日：2017-03-21

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Michael John Hughes

IPC: F23R3/34 ,  F23R3/00 ,  F23R3/60 ,  F23R3/28 ,  F23R3/50

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.

公开(公告)号：US10408455B2

公开(公告)日：2019-09-10

申请号：US15181539

申请日：2016-06-14

Applicant: General Electric Company

Inventor： Michael John Hughes ,  James Scott Flanagan ,  Jonathan Dwight Berry

IPC: F23R3/28 ,  F02C7/22 ,  F02C3/04

Abstract: The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.

公开(公告)号：US20180245792A1

公开(公告)日：2018-08-30

申请号：US15441421

申请日：2017-02-24

Applicant: General Electric Company

Inventor： Kevin Weston McMahan ,  Jonathan Dwight Berry ,  Michael John Hughes

IPC: F23R3/34 ,  F02C7/22

CPC classification number: F23R3/346 ,  F02C7/22 ,  F05D2220/32 ,  F05D2240/35 ,  F23R3/06

Abstract: An axially staged combustion system includes a primary fuel nozzle, a primary combustion zone defined downstream from the primary fuel nozzle, a conical duct disposed downstream from the primary combustion zone and an integrated exit piece disposed downstream from the conical duct. The conical duct and the integrated exit piece at least partially form a hot gas path of the duct section. A plurality of fuel injectors is oriented radially inwardly with respect to an axial centerline of the duct section and is disposed downstream from the primary combustion zone. Each fuel injector of the plurality of fuel injectors provides for injection of a secondary fuel-air mixture into the hot gas path. The plurality of fuel injectors is distributed along at least one of the conical duct and the integrated exit piece.

公开(公告)号：US09938903B2

公开(公告)日：2018-04-10

申请号：US14978019

申请日：2015-12-22

Applicant: General Electric Company

Inventor： Michael John Hughes ,  Jonathan Dwight Berry

IPC: F23R3/34 ,  F02C7/22 ,  F02C3/04 ,  F02C7/12 ,  F23R3/00 ,  F23R3/04 ,  F23R3/28 ,  F23R3/46 ,  F23R3/50

CPC classification number: F02C7/222 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F23R3/002 ,  F23R3/04 ,  F23R3/286 ,  F23R3/346 ,  F23R3/46 ,  F23R3/50 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A gas turbine including a working fluid flowpath extending aftward from a forward injector in a combustor. The combustor may include an inner radial wall, an outer radial wall, and, therebetween, a flow annulus, and a third radial wall formed about the outer radial wall that forms an outer flow annulus. A staged injector may intersect the flow annulus so to attain an injection point within the working fluid flowpath by which aftward and forward annulus sections are defined. Air directing structure may include an aftward intake section corresponding to the aftward annulus section and a forward intake section corresponding to the forward annulus section. The air directing structure may include a switchback coolant flowpath to direct air from the compressor discharge cavity to the staged injector. The switchback coolant flowpath may include an upstream section through the flow annulus, and a downstream section through the outer flow annulus.

公开(公告)号：US20170299187A1

公开(公告)日：2017-10-19

申请号：US15464419

申请日：2017-03-21

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Stanley Kevin Widener ,  Michael John Hughes ,  Matthew Troy Hafner ,  Joseph Vincent Citeno

IPC: F23R3/28 ,  F02C7/18 ,  F01D9/04 ,  F02C7/24

CPC classification number: F23R3/286 ,  F01D9/041 ,  F02C7/18 ,  F02C7/24 ,  F05D2220/30 ,  F05D2240/35 ,  F23R3/283 ,  F23R3/346 ,  F23R2900/03341

Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.

公开(公告)号：US20170298827A1

公开(公告)日：2017-10-19

申请号：US15442171

申请日：2017-02-24

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Michael John Hughes

IPC: F02C7/18 ,  F23R3/00 ,  F23R3/10 ,  F02C7/22 ,  F23R3/28 ,  F02C3/04

Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner including an inner band radially spaced from an outer band and an inner flow annulus formed therebetween, and an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween. The fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector extends radially between the inner liner and the outer liner. At least one of the inner flow passage and the outer flow passage is in fluid communication with at least one of a premix air plenum, a cooling air cavity and a cooling air plenum defined within the panel fuel injector.

公开(公告)号：US20170276366A1

公开(公告)日：2017-09-28

申请号：US15464400

申请日：2017-03-21

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Stanley Kevin Widener ,  Michael John Hughes ,  James Scott Flanagan

IPC: F23R3/28 ,  F23R3/36 ,  F23R3/34

CPC classification number: F23R3/286 ,  F23R3/34 ,  F23R3/346 ,  F23R3/36 ,  F23R3/46

Abstract: A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.

公开(公告)号：US20170276364A1

公开(公告)日：2017-09-28

申请号：US15442203

申请日：2017-02-24

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Michael John Hughes

IPC: F23R3/28 ,  F02C7/22 ,  F23R3/00

CPC classification number: F02C7/18 ,  F02C3/04 ,  F02C7/22 ,  F02C7/222 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R3/06 ,  F23R3/10 ,  F23R3/283 ,  F23R3/286 ,  F23R3/34 ,  F23R3/346

Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner having a hot side surface and a cool side surface and an outer liner having a hot side surface and a cool side surface. The inner liner, the outer liner and the panel fuel injector partially define a hot gas path downstream from the fuel nozzle. The inner liner and/or the outer liner define a plurality of micro-channel cooling passages which is disposed between the hot side surface and cool side surface of the inner liner. Each micro-channel cooling passage of the first plurality of micro-channel cooling passages is in fluid communication with an inlet hole defined along the cool side surface of the respective liner and an outlet hole.

公开(公告)号：US20170276363A1

公开(公告)日：2017-09-28

申请号：US15464443

申请日：2017-03-21

Applicant: General Electric Company

Inventor： Jonathan Dwight Berry ,  Michael John Hughes ,  Kevin Weston McMahan

IPC: F23R3/28

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. An aft end portion of the fuel injection panel defines a turbine nozzle. One or more hook plates attached to the outer surfaces of the liner segments are used to mount the integrated combustor nozzle to an inner mounting ring or an outer mounting ring. A mounting strut or mounting tenon(s) attached to the liner segments may also be employed.