Back to results
US 2016/0108738 A1Published application
Gas turbine component with platform cooling
AssigneeUnited 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 extends from a first side of a platform and a cooling passage that extends through the platform and includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the airfoil.
Claims20
A gas turbine engine component comprising:
- an airfoil extending from a first side of a platform;
- and
- a cooling passage extending through the platform including an inlet located on a second opposite side of the platform, wherein the inlet is located axially upstream of the airfoil.
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 with an inlet located 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;
- and
- directing the cooling air through a cooling passage extending through the platform of the at least one rotor blade.
1 more element
Dependencies are inferred from the claim text.