公开(公告)号：US11112115B2

公开(公告)日：2021-09-07

申请号：US14910827

申请日：2014-06-30

Applicant: United Technologies Corporation

Inventor： Stanislav Kostka, Jr. ,  Randal G. McKinney ,  James B. Hoke ,  Timothy S. Snyder ,  Frank J. Cunha

IPC: F23R3/06 ,  F23R3/26 ,  F23R3/04 ,  F02C7/18 ,  F23R3/00

Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a support shell with a first inner periphery along an axis and a liner panel with a second inner periphery along the axis. The second inner periphery is smaller than the first inner periphery. Another wall assembly for use in a combustor of a gas turbine engine includes an annular grommet mounted between the support shell and the liner panel. The annular grommet defines a contoured inner wall.

公开(公告)号：US20210172605A1

公开(公告)日：2021-06-10

申请号：US16705644

申请日：2019-12-06

Applicant: United Technologies Corporation

Inventor： Timothy S. Snyder

IPC: F23R3/14 ,  F23R3/00 ,  F23R3/28

Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. A hood chamber is separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell. The bulkhead includes at least one opening extending between the hood chamber and the combustion chamber. A fuel injector extends through the at least one opening. The fuel injector includes a primary fuel passage including a primary fuel outlet located within the combustion chamber. The fuel injector further includes a secondary fuel passage including a plurality of secondary fuel outlets located within the hood chamber.

公开(公告)号：US20210172413A1

公开(公告)日：2021-06-10

申请号：US16705658

申请日：2019-12-06

Applicant: United Technologies Corporation

Inventor： Timothy S. Snyder

IPC: F02M43/04 ,  F02C7/12

Abstract: A method for operating a fuel injector of a gas turbine engine includes injecting a hydrogen-based primary fuel from a primary fuel passage of the fuel injector directly into a combustion chamber. The primary fuel passage includes a primary fuel outlet located within the combustion chamber. The method further includes injecting a second fuel, different than the hydrogen-based primary fuel, from a secondary fuel passage of the fuel injector into a hood chamber separated from the combustion chamber by a bulkhead. The secondary fuel passage includes a plurality of secondary fuel outlets located within the hood chamber.

公开(公告)号：US20210055000A1

公开(公告)日：2021-02-25

申请号：US16549722

申请日：2019-08-23

Applicant: United Technologies Corporation

Inventor： Fumitaka Ichihashi ,  Timothy S. Snyder ,  Jeffrey J. Lienau ,  Baris A. Sen

IPC: F23R3/08 ,  F01D25/12 ,  F01D25/26

Abstract: A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

公开(公告)号：US20210048196A1

公开(公告)日：2021-02-18

申请号：US16538544

申请日：2019-08-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Timothy S. Snyder

IPC: F23R3/28 ,  F23R3/14

Abstract: A guide plate for a swirler assembly is disclosed. In various embodiments, the guide plate includes a guide plate flange configured for engagement with a swirler body having a swirler inlet; and a guide plate collar, the guide plate collar having an aft protrusion with respect to an axial direction extending through the swirler body, the aft protrusion having an aft protrusion tip position configured to be equal to or extend downstream of a swirler inlet forward position with respect to the axial direction and a radially outer surface that forms a radially outer surface angle greater than ninety degrees with respect to a radial direction.

公开(公告)号：US10794596B2

公开(公告)日：2020-10-06

申请号：US14914825

申请日：2014-08-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Zhongtao Dai ,  Randolph J Smith ,  Kristin Kopp-Vaughan ,  Timothy S. Snyder ,  Donald J Hautman

IPC: F23R3/36 ,  F23R3/12 ,  F23R3/28 ,  F23D11/38 ,  F23R3/14 ,  F23D11/10 ,  F23D11/12 ,  F23D17/00 ,  F02C7/22

Abstract: A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.

公开(公告)号：US10551065B2

公开(公告)日：2020-02-04

申请号：US15165003

申请日：2016-05-26

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joey Wong ,  Robert M. Sonntag ,  Albert K. Cheung ,  Timothy S. Snyder

IPC: F23R3/00 ,  F23R3/10 ,  F23R3/44 ,  F23R3/06

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.

公开(公告)号：US20200025376A1

公开(公告)日：2020-01-23

申请号：US16260543

申请日：2019-01-29

Applicant: United Technologies Corporation

Inventor： Timothy S. Snyder ,  Randal G. McKinney ,  James B. Hoke

IPC: F23R3/00 ,  F23R3/26 ,  F23R3/12 ,  F02C7/236 ,  F23R3/06 ,  F23R3/28

Abstract: A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.

公开(公告)号：US09851105B2

公开(公告)日：2017-12-26

申请号：US14790970

申请日：2015-07-02

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Joel H. Wagner ,  Mark F. Zelesky ,  Stanislav Kostka ,  Timothy S. Snyder

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/00019 ,  F23R2900/03042 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A self-cooled orifice structure that may be for a combustor of a gas turbine engine, and may further be a dilution hole structure, includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice having a centerline and communicating axially through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel and are in fluid communication with the cavity, and each one of the plurality of inlet apertures are proximate to a first side of a respective one of the plurality of end walls. A plurality of outlet apertures extend through the hot side panel and are in fluid communication with the cavity, and each one of the plurality of outlet apertures are associated with an opposite second side of a respective one of the plurality of end walls.

公开(公告)号：US20160273773A1

公开(公告)日：2016-09-22

申请号：US15165003

申请日：2016-05-26

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joey Wong ,  Robert M. Sonntag ,  Albert K. Cheung ,  Timothy S. Snyder

IPC: F23R3/00 ,  F23R3/06

Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.

Abstract translation: 燃气涡轮发动机包括风扇，压缩机部分，燃烧器，风扇驱动齿轮系统和联接成通过齿轮系驱动风扇的涡轮部分。 燃烧器包括环形外壳和限定环形燃烧室的环形内壳。 在环形燃烧室中有一个隔壁，并在隔板上安装一个环形隔热罩。 环形隔热罩包括具有前表面和后表面，周向外侧和周向内侧的区段，前表面和后表面之间的中心孔，从中心孔周围的前表面突出的唇部 ，从前表面突出的轨道，以及轨道和唇缘之间的多个通孔。 轨道接触隔板以限定由轨道，唇缘和舱壁限定的空腔。