A combustor for a gas turbine engine includes a combustion chamber and a fuel igniter assembly. The combustion chamber is defined by an annular inner combustor liner and an annular outer combustor liner. The fuel igniter assembly is coupled to the combustor and extends radially outward from the outer combustor liner. The fuel igniter assembly includes an igniter housing configured to house a fuel igniter therein, and a heat-dissipating element coupled to the igniter housing. The heat-dissipating element includes a plurality of fins configured to dissipate heat from the fuel igniter assembly.

A combustor for a gas turbine engine includes a combustion chamber and a fuel igniter assembly. The combustion chamber is defined by an annular inner combustor liner and an annular outer combustor liner. The fuel igniter assembly is coupled to the combustor and extends radially outward from the outer combustor liner. The fuel igniter assembly includes an igniter housing configured to house a fuel igniter therein, and a heat-dissipating element coupled to the igniter housing. The heat-dissipating element includes a plurality of fins configured to dissipate heat from the fuel igniter assembly.

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.

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.

A system for igniting a combustion chamber of a turboshaft engine, comprising: a plurality of start-up injectors which are suitable for injecting fuel into said chamber during a combustion-initiating phase; a circuit for supplying fuel to said start-up injectors, comprising a first sub-circuit, referred to as the primary start-up circuit, designed to supply fuel to some of said plurality of start-up injectors; a second sub-circuit, referred to as the secondary start-up circuit, designed to supply fuel to the other start-up injectors of said plurality.

There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.

There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.

A spark plug having an insulating body defining a longitudinal axis and including a base portion and an obstruction portion, a first electrode including a proximal portion, a sheathed portion and a distal portion, the sheathed portion of the first electrode extending through the base portion of the insulating body, and a second electrode including a proximal portion, a sheathed portion and a distal portion, the sheathed portion of the second electrode extending through the base portion and the obstruction portion of the insulating body, wherein the obstruction portion axially extends beyond the distal portion of the first electrode.

A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.

A closed trapped vortex apparatus includes: a tubular structure having a structural wall, the structural wall forming a cavity within the tubular structure, the structural wall having a lower boundary wall forming a boundary between the cavity and a core flow passage; at least one driver hole passing through the structural wall; an ignition source communicating with the cavity; a fuel source communicating with the cavity; and a plurality of flame tubes extending through the lower boundary wall of the tubular structure at preselected locations so as to provide communication between the cavity and the core flow passage.