Igniter tube and method of assembling same
AssigneeGeneral Electric Company
InventorsThomas George Holland, Steven Clayton Vise, Marie Ann McMasters
Life of this patent
Estimating the term…
Abstract
An igniter tube assembly includes an axis of symmetry extending therethrough, an igniter tube that includes a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that the igniter tube circumscribes the igniter and such that a gap is defined between the igniter tube and the igniter, a ferrule coupled to the igniter tube, and a plurality of cooling air openings extending through at least one of the igniter tube and the ferrule to facilitate channeling cooling air into the gap.
Claims20
A method for assembling a gas turbine engine, the gas turbine engine including a combustor, and at least one igniter inserted at least partially into the combustor, said method comprising:
- providing an igniter tube assembly including an axis of symmetry extending therethrough, an igniter tube, and a ferrule that includes a radially inner surface and a radially outer surface, the igniter tube having a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that the igniter tube circumscribes the igniter and such that a gap is defined between the igniter tube and the igniter, and at least one of a first plurality of cooling air openings defined substantially by and extending through the igniter tube and a second plurality of cooling air openings axially spaced from the at least one of a first plurality of cooling air openings which are defined substantially by and extending through the ferrule to facilitate channeling cooling air into the gap, wherein at least one of the second plurality of cooling air openings extends through the ferrule from the radially inner surface to the radially outer surface;
- and
- coupling the igniter tube and the ferrule to the combustor.
An igniter tube assembly for a gas turbine engine, the gas turbine engine including a combustor, and at least one igniter inserted at least partially into the combustor, said igniter tube assembly comprising:
- an axis of symmetry extending therethrough;
- an igniter tube comprising a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that said igniter tube circumscribes the igniter and such that a gap is defined between said igniter tube and the igniter;
- a ferrule coupled to said igniter tube, said ferrule comprising a radially inner surface and a radially outer surface;
- and
- at least one of a first plurality of cooling air openings defined substantially by and extending through said igniter tube and a second plurality of cooling air openings axially spaced from the at least one of a first plurality of cooling air openings which are defined substantially by and extending through said ferrule to facilitate channeling cooling air into said gap, wherein at least one of said second plurality of cooling air openings extends through said ferrule from said radially inner surface to said radially outer surface.
A gas turbine engine including a combustor comprising an annular outer liner and an annular inner liner that define a combustion chamber therebetween, and at least one igniter tube assembly coupled to said combustor, and an igniter tube assembly comprising:
- an axis of symmetry extending therethrough;
- an igniter tube comprising a first opening extending coaxially therethrough having a diameter sized to receive a portion of the igniter therethrough such that said igniter tube circumscribes the igniter and such that a gap is defined between said igniter tube and the igniter;
- a ferrule coupled to said igniter tube, said ferrule comprising a radially inner surface and a radially outer surface;
- and
- at least one of a first plurality of cooling air openings defined substantially by and extending through said igniter tube and a second plurality of cooling air openings axially spaced from the at least one of a first plurality of cooling air openings which are defined substantially by and extending through said ferrule to facilitate channeling cooling air into said gap, wherein at least one of said second plurality of cooling air openings extends through said ferrule from said radially inner surface to said radially outer surface.
Dependencies are inferred from the claim text.