公开(公告)号：US12123355B2

公开(公告)日：2024-10-22

申请号：US18110140

申请日：2023-02-15

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason Ryon ,  Lev Alexander Prociw

IPC: F02C7/264

CPC classification number: F02C7/264 ,  F23R2900/00009

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.

公开(公告)号：US11982237B2

公开(公告)日：2024-05-14

申请号：US17983691

申请日：2022-11-09

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason Ryon ,  Lev Alexander Prociw

IPC: F02C7/264 ,  F02C7/18 ,  F23R3/06

CPC classification number: F02C7/264 ,  F02C7/18 ,  F23R3/06 ,  F23R2900/00009 ,  F23R2900/03043

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.

公开(公告)号：US20230193828A1

公开(公告)日：2023-06-22

申请号：US18110140

申请日：2023-02-15

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason Ryon ,  Lev Alexander Prociw

IPC: F02C7/264

CPC classification number: F02C7/264 ,  F23R2900/00009

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, a glow plug housing configured to receive a glow plug and allow an innermost end of the glow plug to extend into the combustion chamber, and a cooling system. The cooling system includes an air inlet formed within an exterior of the structural wall, a cooling channel forming a flow path through the structural wall at the glow plug housing, and an air passage.

公开(公告)号：US20230068242A1

公开(公告)日：2023-03-02

申请号：US17983691

申请日：2022-11-09

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason Ryon ,  Lev Alexander Prociw

IPC: F02C7/264 ,  F02C7/18 ,  F23R3/06

Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine comprises a combustion chamber oriented about an axis, a cap defining an axially upstream end of the combustion chamber and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet formed within the structural wall, a first flow path disposed between the structural wall and the igniter wall, and an aperture extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.

公开(公告)号：US12092333B2

公开(公告)日：2024-09-17

申请号：US18120183

申请日：2023-03-10

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason Ryon ,  Brandon P. Williams ,  Lev Alexander Prociw

IPC: F23R3/00 ,  F02C7/264 ,  F23R3/34

CPC classification number: F23R3/343 ,  F02C7/264 ,  F05D2240/35 ,  F05D2260/99

Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.

公开(公告)号：US20230392552A1

公开(公告)日：2023-12-07

申请号：US18123764

申请日：2023-03-20

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason A. Ryon ,  Lev Alexander Prociw ,  Brandon P. Williams

IPC: F02C7/264 ,  F02P21/00 ,  F23Q9/00 ,  F23R3/36

CPC classification number: F02C7/264 ,  F02P21/00 ,  F02C7/266 ,  F23R3/36 ,  F23Q9/00

Abstract: A torch igniter system for a combustor of a gas turbine engine includes a housing defining a combustion chamber, an ignition source disposed at least partially in the combustion chamber, a fuel injector, a first fluid path connecting a first fuel source to the fuel injector, a second fluid path connecting an air source to the fuel injector, and a third fluid path connecting a second fuel source to the combustion chamber. The fuel injector is configured to inject fuel, air, or a mixture of fuel and air into the combustion chamber and to impinge on the ignition source.

公开(公告)号：US20230213196A1

公开(公告)日：2023-07-06

申请号：US18120183

申请日：2023-03-10

Applicant: Collins Engine Nozzles, Inc.

Inventor： Jason Ryon ,  Brandon P. Williams ,  Lev Alexander Prociw

IPC: F23R3/34 ,  F02C7/264

CPC classification number: F23R3/343 ,  F02C7/264 ,  F05D2240/35 ,  F05D2260/99

Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle, and a torch igniter within the combustor case. The torch igniter includes a combustion chamber, a cap defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip defining the downstream end of the combustion chamber, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip that fluidly connects the combustion chamber to the combustor. The torch igniter is situated such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case.