Back to results
US 2019/0292919 A1Published application
Turbine airfoils with micro cooling features
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsBrett J. Barker, Jeffrey F. Rhodes
Life of this patent
Estimating the term…
Abstract
A blade used in a gas turbine engine includes a pair of pedestals and an airfoil coupled between the pedestals. The airfoil includes cooling features to cool the airfoil.
Claims20
An airfoil for use in a gas turbine engine and having a pressure side and a suction side, the airfoil comprising
- a spar that extends radially relative to an axis and formed to define a cooling air plenum adapted to receive a flow of cooling air, and
- a skin coupled to an exterior surface of the spar and positioned to at least partially cover the spar along the pressure side and the suction side,
- wherein a first plurality of axially extending grooves is formed in the exterior surface of the spar on the suction side that defines a first plurality of cooling passageways between the spar and the skin, a second plurality of axially extending grooves is formed in the exterior surface of the spar on the pressure side that defines a second plurality of cooling passageways between the spar and the skin,
- wherein a first plurality of inlet ports is formed in the spar and in fluid communication with the cooling air plenum and the first plurality of cooling passageways to pass the flow of cooling air into the first plurality of cooling passageways from the cooling air plenum, a second plurality of inlet ports is formed in the spar and in fluid communication with the cooling air plenum and the second plurality of cooling passageways to pass the flow of cooling air into the second plurality of cooling passageways from the cooling air plenum, and
- wherein the first plurality of cooling passageways extending between the first plurality of inlet ports and a first plurality of outlet slots positioned axially aft of the first plurality of inlet ports, the second plurality of cooling passageways extending between the second plurality of inlet ports and a second plurality of outlet slots positioned axially aft of the second plurality of inlet ports, and the first and second plurality of outlet slots are configured to pass the flow of cooling air from the first and second plurality of cooling passageways to an exterior of the airfoil.
2 more elements
An airfoil for use in a gas turbine engine, the airfoil comprising
- a spar that extends radially relative to an axis, the spar formed to define a cooling air plenum, a first axially extending groove in an exterior surface of the spar on a suction side of the airfoil, a first inlet port in fluid communication with the cooling air plenum and the first axially extending groove, a second axially extending groove in the exterior surface of the spar on a pressure side of the airfoil, and a second inlet port in fluid communication with the cooling air plenum and the second axially extending groove, and
- a skin coupled to the exterior surface of the spar along the pressure side and the suction side of the airfoil to define a first outlet slot in fluid communication with the first axially extending groove and a second outlet slot in fluid communication with the second axially extending groove, the first and second outlet slots located axially aft of the first and second inlet ports, and the first and second outlet slots being in fluid communication with an exterior of the airfoil.
Dependencies are inferred from the claim text.