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US 7,451,600 B2Granted
Gas turbine engine combustor with improved cooling
AssigneePratt & Whitney Canada Corp.
InventorsBhawan Patel, Parthasarathy Sampath, Russell Parker
Life of this patent
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Abstract
A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide improved cooling efficiency in regions of the combustor dome corresponding to predetermined hotspots.
Claims16
A combustor for a gas turbine engine comprising:
- combustor walls including inner and outer cylindrical liners spaced apart and circumscribing an upstream annular dome portion, the combustor walls defining at least a portion of a combustion chamber therewithin;
- a plurality of fuel nozzles for injecting a fuel mixture into the combustion chamber, said fuel nozzles aligned with corresponding fuel nozzle openings defined in said dome portion;
- and
- a plurality of cooling apertures defined through said dome portion for delivering pressurized cooling air surrounding said combustor into said combustion chamber, said cooling apertures including first cooling holes and second cooling holes, said second cooling holes defining concentric circular configurations surrounding each of said fuel nozzle openings and are angled in the dome portion substantially tangentially relative to an associated one of said fuel nozzle openings, said first cooling holes being disposed in regions defined between adjacent concentric circular configurations of said second cooling holes and located proximate to the outer cylindrical liner, said first cooling holes extending substantially perpendicularly through the dome portion.
1 more element
An annular reverse flow combustor for a gas turbine engine comprising:
- combustor walls including inner and outer cylindrical liners spaced apart and circumscribing an upstream annular dome portion, the combustor walls defining at least a portion of a combustion chamber therewithin;
- a plurality of fuel nozzle openings defined in said dome portion, said fuel nozzle openings being adapted to receive therein fuel nozzles for injecting a fuel mixture into the combustion chamber;
- a plurality of cooling apertures defined through said dome portion for delivering pressurized cooling air surrounding said combustor into said combustion chamber, said cooling apertures including first cooling holes and second cooling holes, said second cooling holes defining concentric circular configurations surrounding each of said fuel nozzle openings, said first cooling holes being disposed in regions defined between adjacent concentric circular configurations of said second cooling holes, said first cooling holes extending substantially perpendicularly through the dome portion and said second cooling holes being angled in the dome portion relative to said first cooling holes, the second cooling holes are angled in the dome portion substantially tangentially relative to an associated one of said fuel openings.
Dependencies are inferred from the claim text.