Gas turbine component with platform cooling
AssigneeRaytheon Technologies Corporation
InventorsMatthew A. Devore, Matthew S. Gleiner
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component includes an airfoil that has a leading edge and extends from a first side of a platform that has a leading edge overhang. A root portion extends from a second side of the platform opposite the first side. A cooling passage extends through the platform and beneath a trailing edge of the airfoil. The cooling passage includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the leading edge of the airfoil and the inlet is located axially upstream of the root portion in the leading edge overhang.
Claims20
A gas turbine engine component comprising:
- an airfoil having a leading edge and extending from a first side of a platform having a leading edge overhang;
- a root portion extending from a second side of the platform opposite the first side;
- and
- a cooling passage extending through the platform and beneath a trailing edge of the airfoil, the cooling passage including an inlet located on a second opposite side of the platform, wherein the inlet is located axially upstream of the leading edge of the airfoil and the inlet is located axially upstream of the root portion in the leading edge overhang.
A gas turbine engine comprising:
- a first array of vanes;
- and
- a first rotor assembly including a first array of rotor blades located downstream of the first array of vanes, wherein at least one of the first array of rotor blades includes a cooling passage extending through a platform and beneath a trailing edge of an airfoil with an inlet to the cooling passage located axially upstream of a leading edge of the airfoil and in a radially inner side of a leading edge overhang of the platform.
A method of cooling a gas turbine engine component comprising:
- directing cooling air into a forward stage cavity;
- directing the cooling air through an inlet in an overhang of a platform of at least one rotor blade having an airfoil with a leading edge and beneath a trailing edge of the airfoil, wherein the overhang is a leading edge overhang located axially forward of the leading edge of the airfoil;
- and
- directing the cooling air through a cooling passage extending through the platform of the at least one rotor blade.
Dependencies are inferred from the claim text.