Dilution holes with ridge feature for gas turbine engines
AssigneeUnited Technologies Corporation
InventorsDominic Mongillo, JR., Christopher Whitfield, Tracy Phropheter-Hinckley
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Abstract
A grommet may define a dilution hole in a combustor panel. The grommet may comprise a ridge having a stepped geometry formed about an inner diameter of the grommet, the ridge comprising a passage. The passage may comprise an outlet. The ridge may further comprise a fillet about the inner diameter of the grommet, wherein the outlet is configured to direct a cooling flow circumferentially along the fillet and fill the ridge with the cooling flow.
Claims20
A grommet having at least one of an annular geometry or an elliptical geometry defining a dilution hole, comprising:
- a ridge having a step geometry comprising at least one of a sharp geometry, a radial geometry, or a multi-radial geometry, the ridge formed about an inner diameter of the grommet and comprising a passage.
A combustor liner comprising:
- an array of cooling holes defined by the combustor liner;
- and
- a grommet having at least one of an annular geometry or an elliptical geometry and formed integrally with the combustor liner and defining a dilution hole, wherein the grommet comprises:
- a ridge having a step geometry comprising at least one of a sharp geometry, a radial geometry, or a multi-radial geometry, the ridge formed about an inner diameter of the grommet and comprising a passage.
A gas turbine engine comprising:
- a compressor section configured to compress a gas;
- a combustor section aft of the compressor section and configured to combust the gas, wherein the combustor section comprises a combustor liner having a grommet formed integrally with the combustor liner, having at least one of an annular geometry or an elliptical geometry and defining a dilution hole, wherein the grommet comprises:
- a ridge having a step geometry comprising at least one of a sharp geometry, a radial geometry, or a multi-radial geometry, the ridge formed about an inner diameter of the grommet and comprising a passage;
- and the gas turbine engine further comprises:
- a turbine section aft of the combustor section and configured to extract energy from the gas.
Dependencies are inferred from the claim text.