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US 10,871,075 B2Granted
Cooling passages in a turbine component
AssigneePratt & Whitney Canada Corp.
InventorsSri Sreekanth, Si-Man Lao, Michael Leslie Clyde Papple
Life of this patent
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Abstract
A turbine component has a plurality of cooling passages each extending through a body of a structure between opposite hot and cold surfaces of the structure. According to one embodiment, at least one of the cooling passages includes a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface.
Claims20
A liner of an aircraft engine combustor, comprising:
- a body between a hot surface for being exposed to hot combustion gases and a cold surface for being exposed to cooling air, the hot and cold surfaces being opposite each other, the hot surface facing toward an interior of the aircraft engine combustor, the cold surface facing toward an exterior of the aircraft engine combustor;
- and
- a plurality of cooling passages extending through the body of the liner between the hot and cold surfaces, at least one of the cooling passages comprising:
- a plurality of upstream paths defining a plurality of inlet openings on the cold surface and merging into a downstream path that defines an outlet opening on the hot surface, the outlet opening having a cross-sectional area at the hot surface larger than a cross-sectional area of each one of the plurality of inlet openings at the cold surface, and a metering section having a constant cross-section over a distance along the hot surface, the constant cross-section transverse to the hot surface, the metering section extending parallel to the hot surface and disposed between the plurality of upstream paths and the downstream path, the constant cross-section smaller than each one of the plurality of inlet openings at the cold surface and the outlet opening at the hot surface.
1 more element
A combustor of an aircraft engine, comprising:
- a combustor liner having a hot surface for being exposed to hot combustion gases within the combustor and a cold surface for being exposed to cooling air, the hot and cold surfaces being opposite each other, the cold surface facing toward an exterior of the combustor and the hot surface facing toward an interior of the combustor;
- and
- a plurality of cooling passages extending through the combustor liner from the cold surface to the hot surface, at least one of the cooling passages comprising a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface, each one of the outlet openings having a cross-sectional area at the hot surface larger than a cross-sectional area of each one of the inlet openings at the cold surface, the at least one of the cooling passages including a metering section having a constant cross-section over a distance along the hot surface, the constant cross-section transverse to the hot surface, the metering section extending parallel to the hot surface and disposed between the plurality of upstream paths and the number of downstream paths.
An aircraft engine, comprising:
- a compressor for pressurizing air;
- a combustor in serial flow communication with the compressor downstream thereof, the combustor having a combustor liner including a hot surface for being exposed to hot combustion gases within the combustor and a cold surface for being exposed to cooling air, the hot and cold surfaces being opposite each other, the cold surface facing toward an exterior of the combustor and the hot surface facing toward an interior of the combustor,
- a plurality of cooling passages extending through the combustor liner between the hot and cold surfaces, each of the cooling passages comprising:
- a plurality of upstream paths defining respective inlet openings on the cold surface and extending from the respective inlet openings inwardly into the combustor liner toward the interior of the combustor,
- a plurality of downstream paths connected with the upstream paths and extending toward the hot surface to define respective outlet openings on the hot surface, all of the upstream and downstream paths being connected together, a flared section defining one of said outlet openings, each one of the outlet openings having a cross-sectional area at the hot surface larger than a cross-sectional area of each one of the inlet openings at the cold surface, and
- a metering section having a constant cross-section over a distance along the hot surface, the constant cross-section transverse to the hot surface and disposed between the plurality of upstream paths and the plurality of downstream paths,
- the respective metering sections of the plurality of cooling passages extending in a common plane parallel to the hot surface;
- and
- a turbine section for extracting energy from the combustion gases, the turbine section in serial flow communication with the combustor downstream thereof.
6 more elements
Dependencies are inferred from the claim text.