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US 10,309,314 B2Granted
Finned ignitor grommet for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsJames B. Hoke, James P. Bangerter
Life of this patent
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Abstract
A heat shield for a combustor of a gas turbine engine includes a cold side opposite a hot side, the cold side defines a grommet that surrounds an igniter aperture, the grommet includes a multiple of fins.
Claims17
A combustor of a gas turbine engine comprising:
- a support shell;
- and
- a heat shield mounted to the support shell, the heat shield comprising:
- a hot side;
- and
- a cold side opposite said hot side, wherein said cold side defines a grommet that surrounds an igniter aperture in the heat shield, said grommet contacts said support shell to provide a seal therewith, and said grommet includes a multiple of fins and a rail;
- wherein the multiple of fins are between the heat shield and the support shell;
- wherein the rail extends circumferentially around an axis of the igniter aperture along a first portion of a circular trajectory between opposing circumferential rail ends;
- wherein the multiple of fins are arranged circumferentially around the axis along a second portion of the circular trajectory such that the multiple of fins are circumferentially inline with the rail along the circular trajectory;
- wherein the multiple of fins are in a gap define between the opposing circumferential rail ends;
- and
- wherein each of the multiple of fins has a circular cross-sectional geometry.
9 more elements
A combustor of a gas turbine engine comprising:
- a support shell;
- and
- a heat shield with a grommet that surrounds an igniter aperture, wherein the heat shield is mounted to the support shell, said grommet includes a rail and a multiple of fins disposed between a cold side of the heat shield and the support shell, and the grommet contacts the support shell to provide a seal therewith;
- wherein the rail extends circumferentially about an axis of the igniter aperture along a first portion of an annular trajectory, and the multiple of fins are arranged circumferentially about the axis of the igniter aperture along a second portion of the annular trajectory such that the multiple of fins are circumferentially inline with the rail along the annular trajectory;
- and
- wherein a first of the multiple of fins has a circular cross-sectional geometry.
3 more elements
Dependencies are inferred from the claim text.