Abstract: A system includes a combustor. The combustor has a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end. The combustor wall includes an inner wall portion and an outer wall portion defining an interior of the combustor therebetween. Each of the inner wall portion and outer wall portion extends from the combustor dome to the downstream end of the combustor wall. The combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion. The air cooling passage extends from the upstream end of the combustor wall to the downstream end of the combustor wall.

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 the axially upstream end of the combustion chamber and situated on the axis, 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, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

Abstract: A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.

Abstract: A method includes forming fluid conduit inside a heat shield in an additive manufacturing process, removing powder from an interior passage of the fluid conduit and from an insulation gap defined between the fluid conduit and the heat shield, separating the heat shield and fluid conduit from the build platform, and shifting the fluid conduit to a shifted position relative to the heat shield. The method includes securing the fluid conduit to the heat shield in the shifted position.

Abstract: A fuel injector for an exhaust heater includes a cover and an air blast nozzle. The cover has a nozzle seat, a fuel inlet, and an air inlet, the nozzle seat arranged along a flow axis. The air blast nozzle is seated in the nozzle seat and has a unibody. The air blast nozzle unibody is in fluid communication with the fuel inlet and the air inlet arranged along the flow axis to port fuel and air into a combustion volume, e.g., to heat a stream of exhaust gas flowing between an engine and a catalytic reactor by combustion with fuel introduced through the fuel inlet and air introduced through the air inlet.

Abstract: A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.

Abstract: A torch ignitor system for a combustor of a gas turbine engine includes a torch ignitor, the torch ignitor including a combustion chamber oriented about a torch axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug. The torch ignitor includes an elbow connected to the downstream end of the combustion chamber for diverting combustion products along an ignition jet flame axis that is off of the torch axis for injection of combustion products into a gas turbine engine combustor. The torch ignitor further includes a tip at a downstream end of the elbow for issuing the injection of combustion products.

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 the axially upstream end of the combustion chamber and situated on the axis, 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, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.

Abstract: An embodiment of a torch ignitor system for a combustor of a gas turbine engine includes a torch ignitor, the torch ignitor include a combustion chamber oriented about a torch axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor further includes a tip at a downstream end of the elbow for issuing the injection of combustion products. An embodiment of a method includes initiating combustion in a combustion chamber of a torch ignitor to produce an ignition jet flame extending along an ignition jet flame axis, and igniting a fuel/air mixture in a gas turbine combustor by issuing a respective spray cone of the fuel/air mixture from a respective fuel injectors in a plurality of fuel injectors, wherein the ignition jet flame axis intersects a plurality of the spray cones.

Abstract: A tile for a combustor dome of a gas turbine engine includes a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface. The tile body extends in a radial direction from a radially inner surface to a radially outer surface. The radially inner and outer surfaces define circular arcs that are concentric with one another. The tile body extends circumferentially from a first end face to a second end face. The first end face follows a sigmoid profile and the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical tile body.

Abstract: A fuel injector system for a torch igniter includes an injector body centered on an axis, a receiving aperture formed in a cap of the torch igniter, an injector aperture, an air channel, a fuel channel, and a purge passage formed in a housing of the torch igniter and fluidly connected to a cooling air source. The injector body includes an axial wall at a first axial end of the injector body, an outer wall connected to the axial wall and extending along the axis transverse to the first wall, and an inner portion connected to the axial wall and extending along the axis transverse to the axial wall. An outer surface of the inner portion is spaced a distance from an inner surface of the outer wall, forming an insulating space between the outer wall and the inner portion.

Abstract: A method includes forming fluid conduit inside a heat shield in an additive manufacturing process, removing powder from an interior passage of the fluid conduit and from an insulation gap defined between the fluid conduit and the heat shield, separating the heat shield and fluid conduit from the build platform, and shifting the fluid conduit to a shifted position relative to the heat shield. The method includes securing the fluid conduit to the heat shield in the shifted position.

Abstract: A torch igniter for a combustor of a gas turbine engine includes an igniter body and an igniter head. The igniter body is disposed within a high-pressure case of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector.

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, 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 tip is mounted through the combustor liner, the cap is downstream of the tip, and the torch igniter is downstream of the fuel nozzle and disposed radially between the combustor liner and the combustor case.

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 at an upstream end of the combustor liner, a torch igniter at least partially within the combustor case, and a removable surface igniter. The torch igniter includes a combustion chamber, a cap configured to receive a fuel injector, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, an aperture, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The torch igniter is configured to receive the removable surface igniter through the aperture. An internal end of the removable surface igniter extends through the aperture into the combustion chamber of the torch igniter.

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 at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, 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 which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.

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.

Abstract: An embodiment of an ignition system for a gas turbine engine includes a high pressure engine case, a torch ignitor disposed at least partially within the high pressure engine case, the torch ignitor having a combustion chamber oriented about a torch axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The ignition system also includes an access hatch configured to allow access through a high pressure engine case to the cap and to seal against the high pressure engine case when not accessing the cap. An embodiment of a method includes removing a hatch from a high pressure engine case to open a hatch opening, performing maintenance on a torch ignitor that is inside the high pressure engine case by accessing the torch ignitor through the hatch opening, replacing the hatch to close the hatch opening after completion of maintenance on the torch ignitor.

Abstract: A torch ignitor system for a combustor of a gas turbine engine includes a torch ignitor, the torch ignitor including a combustion chamber oriented about a torch axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug. The torch ignitor includes an elbow connected to the downstream end of the combustion chamber for diverting combustion products along an ignition jet flame axis that is off of the torch axis for injection of combustion products into a gas turbine engine combustor. The torch ignitor further includes a tip at a downstream end of the elbow for issuing the injection of combustion products.

Abstract: An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.