A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor has a flame outlet opening into the main flow passage of the fuel nozzle for issuing flame into the main flow passage.

A turbine engine comprising a compressor section, a combustion section having a combustor, and a turbine section in serial flow arrangement. The combustor having a combustion chamber, at least one fuel injector, at least one compressed air passage, and at least one igniter. The at least one igniter can be provided within a portion of the at least one fuel injector or the at least one compressed air passage.

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.

A gas turbine engine has: a casing; a combustor liner delimiting a combustion chamber; a fuel nozzle in fluid communication with the combustion chamber; and an igniter having a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a sleeve extending around the glow plug heater rod, the sleeve radially spaced apart from the glow plug heater rod by an annular gap, the sleeve defines fins circumferentially distributed around the axis, each two circumferentially adjacent fins of the fins spaced apart from one another by a spacing communicating with the annular gap, the fins extending in a direction having an axial component from roots to tips, the roots axially closer to the base than the tips, the rod end extending axially beyond the tips of the fins such that the rod end is located outside the annular gap.

There is provided a gas turbine combustor which includes a burner component which is molded by 3D additive manufacturing and is optimized in material strength per part. The burner component includes a first part which is used within a first temperature range and/or a first stress range and a second part which is used within a second temperature range which is lower than the first temperature range and/or a second stress range which is lower than the first stress range, and a lamination speed at which a metal material is laminated on the first part by the 3D additive manufacturing is lower than a lamination speed at which the metal material is laminated on the second part.

A torch ignitor system includes a torch wall defining a combustion chamber therein with a flame outlet passing out of the torch wall downstream of the combustion chamber. A fuel nozzle is mounted to the torch wall to issue fuel into the combustion chamber. An ignitor is mounted to the torch wall, extending into the combustion chamber to ignite fuel issued from the fuel nozzle. A cooling passage is in thermal communication with the ignitor for cooling the ignitor with fluid passing through the cooling passage.

A system for a gas turbine engine includes an igniter event conductor. The igniter event conductor has a first portion adjacent an igniter of the engine and in a combustion chamber of the engine and a second portion apart from the igniter and apart from the combustion chamber. The conductor is adapted to conduct an aspect of an igniter event at the igniter from the first portion to the second portion. A sensor is coupled to the second portion of the conductor to sense the aspect of the igniter event.

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.

The invention relates to a method for improving the performance and efficiency of diesel, gas-turbine, and turbojet combustion engines. The technical result is the creation of conditions for the formation of the open flame formed by burning (oxidation) of hydcerocarbon gases released directly at the moment the fuel is fed into combustion chamber. Consequently, it increases the efficiency and performance of the internal combustion engine. The claimed result is achieved by method of increasing the efficiency and performance of diesel, gas-turbine, turbojet internal combustion engines, which includes the following steps: obtaining hydrogen containing gas from a portion of fuel, previously split by way of overheating; injection into the combustion chamber previously split fuel; obtaining the flame of hydrogen-containing gases at the moment of injection; obtaining the effect of flaring combustion of the major portion of the injected fuel.

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.