Passage geometry for gas turbine engine combustor
AssigneeUnited Technologies Corporation
InventorsDennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin
Life of this patent
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Abstract
An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.
Claims20
A grommet for a wall assembly of a combustor section of a gas turbine engine, the grommet comprising:
- a wall that at least partially defines
- a dilution passage along an axis;
- and
- at least one chamber that at least partially surrounds the dilution passage.
A wall assembly within a gas turbine engine, comprising:
- a liner panel with a hot side and a cold side;
- and
- a grommet with a passage wall and a flange wall transverse to the passage wall, wherein the grommet at least partially defines
- a dilution passage along an axis;
- and
- at least one chamber that at least partially surrounds the dilution passage.
A method of cooling a wall assembly within a gas turbine engine, comprising:
- communicating air into a chamber in an annular grommet.
Dependencies are inferred from the claim text.