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US 2020/0370436 A1Published application
Near wall leading edge cooling channel for airfoil
AssigneePower Systems Mfg., LLC
InventorsGregory Edwin Vogel, Vladimir Kitaigorod
Life of this patent
Estimating the term…
Abstract
Airfoils, gas turbine engine assemblies including such airfoils, and methods of manufacturing the same. The airfoil includes multiple cooling channels proximate a leading edge of the airfoil, each of the cooling channels including an inlet provided on one an inner surface of the airfoil in one of the pressure side wall and the suction side wall, and an outlet provided on an outer surface of the airfoil in the other of the pressure side wall and the suction side wall. The cooling channels are arranged in a staggered configuration such there is an alternate pattern of cooling fluid flow provided at the leading edge of the airfoil, near the airfoil's stagnation point.
Claims20
An airfoil for a gas turbine having a leading edge and a trailing edge, the airfoil comprising:
- an airfoil wall having a pressure side and a suction side, the pressure side including a pressure side inner surface and a pressure side outer surface, the suction side including a suction side inner surface and a suction side outer surface, the pressure side inner surface and the suction side inner surface together defining an inner surface of the airfoil wall, and the pressure side outer surface and the suction side outer surface together defining an outer surface of the airfoil wall, wherein the inner surface of the airfoil wall at least partially defines an airfoil chamber at least partially enclosed within the airfoil wall;
- a plurality of first cooling channels proximate the leading edge of the airfoil, each of the plurality of first cooling channels including an inlet at a first opening provided on the pressure side inner surface and an outlet at a second opening provided on the suction side outer surface;
- and
- a plurality of second cooling channels proximate the leading edge of the airfoil, each of the plurality of second cooling channels including an inlet at a third opening provided on the suction side inner surface and an outlet at a fourth opening provided on the pressure side outer surface,
- wherein the plurality of first cooling channels and the plurality of second cooling channels provide fluid communication between the airfoil chamber and an exterior of the airfoil wall.
2 more elements
A gas turbine assembly, the assembly comprising:
- a plurality of airfoils, wherein each of the plurality of airfoils comprises:
- an airfoil wall having a pressure side and a suction side, the pressure side including a pressure side inner surface and a pressure side outer surface, the suction side including a suction side inner surface and a suction side outer surface, the pressure side inner surface and the suction side inner surface together defining an inner surface of the airfoil wall, and the pressure side outer surface and the suction side outer surface together defining an outer surface of the airfoil wall, wherein the inner surface of the airfoil wall at least partially defines an airfoil chamber at least partially enclosed within the airfoil wall;
- a plurality of first cooling channels proximate the leading edge of the airfoil, each of the plurality of first cooling channels including an inlet at a first opening provided on the pressure side inner surface and an outlet at a second opening provided on the suction side outer surface;
- and
- a plurality of second cooling channels proximate the leading edge of the airfoil, each of the plurality of second cooling channels including an inlet at a third opening provided on the suction side inner surface and an outlet at a fourth opening provided on the pressure side outer surface,
- wherein the plurality of first cooling channels and the plurality of second cooling channels provide fluid communication between the airfoil chamber and an exterior of the airfoil wall.
3 more elements
A method of manufacturing airfoils, the method comprising:
- forming, using additive manufacturing:
- an airfoil wall having a pressure side and a suction side, the pressure side including a pressure side inner surface and a pressure side outer surface, the suction side including a suction side inner surface and a suction side outer surface, the pressure side inner surface and the suction side inner surface together defining an inner surface of the airfoil wall, and the pressure side outer surface and the suction side outer surface together defining an outer surface of the airfoil wall, wherein the inner surface of the airfoil wall at least partially defines an airfoil chamber at least partially enclosed within the airfoil wall;
- a plurality of first cooling channels proximate the leading edge of the airfoil, each of the plurality of first cooling channels including an inlet at a first opening provided on the pressure side inner surface and an outlet at a second opening provided on the suction side outer surface;
- and
- a plurality of second cooling channels proximate the leading edge of the airfoil, each of the plurality of second cooling channels including an inlet at a third opening provided on the suction side inner surface and an outlet at a fourth opening provided on the pressure side outer surface,
- wherein the plurality of first cooling channels and the plurality of second cooling channels provide fluid communication between the airfoil chamber and an exterior of the airfoil wall.
3 more elements
Dependencies are inferred from the claim text.