Fuel igniter assembly having heat-dissipating element and methods of using same
AssigneeUnison Industries, LLC
InventorsRaul Arroyo Martinez Fabre, Juan Humberto Martinez Cervantes, Ricardo Arturo Gutierrez Espinosa, Hicham Benkabbou
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Abstract
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.
Claims18
A combustor for a gas turbine engine, said combustor comprising:
- a combustion chamber defined by an annular inner combustor liner and an annular outer combustor liner;
- a fuel igniter assembly coupled to said combustor and extending radially outward from the outer combustor liner, said fuel igniter assembly comprising an igniter housing configured to house a fuel igniter therein;
- a heat-dissipating element configured to be coupled to said igniter housing, said heat-dissipating element comprising a plurality of fins configured to dissipate heat from said fuel igniter assembly, wherein the plurality of fins are perpendicular to a hex nut disposed on the igniter housing;
- and
- a shroud that defines an airflow channel between igniter housing and the shroud, wherein the heat-dissipating element is included within the shroud.
A fuel igniter assembly for use in a combustor, said fuel igniter assembly comprising:
- an igniter housing comprising an elongate body having a cavity defined therein;
- a fastener disposed on the igniter housing;
- a fuel igniter positioned within said cavity;
- an ignition lead electrically coupled to said fuel igniter at a connection point within said igniter housing;
- a heat-dissipating element coupled to said igniter housing such that said heat-dissipating element at least partially surrounds the connection point between said ignition lead and said fuel igniter, wherein the heat-dissipating element includes a plurality of fins configured to dissipate heat from said fuel igniter assembly, and said fins are located between the fastener and the combustor;
- and
- a shroud that defines an airflow channel between igniter housing and the shroud, wherein the heat-dissipating element is disposed within the shroud.
A method of operating a gas turbine engine including a combustor and a compressor, the combustor including a fuel igniter assembly including an igniter housing, a fuel igniter positioned within the igniter housing, and a set of fins coupled to the igniter housing between the combustor, a shroud that at least partially encloses the set of fins and defines an airflow channel between the igniter housing and the shroud, and a nut disposed on the igniter housing, the method comprising:
- supplying an electrical voltage to the fuel igniter;
- directing an airflow through the shroud and across at least a subset of the fins to dissipate heat from the fuel igniter assembly;
- and
- coupling the fuel igniter to an air-cooled ignition lead wherein air is supplied through an air inlet and flows through a conduit and around the ignition lead, wherein directing the airflow across the subset of fins comprises directing air through the air inlet and along a longitudinal direction of the fins.
Dependencies are inferred from the claim text.