Gas turbine engine airfoil having serpentine fed platform cooling passage
A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end. A platform cooling passageway is fluidly connected to the end and extends transversely into the platform. A cooling hole fluidly connects the platform cooling passageway to an exterior surface.
1. A core for a gas turbine engine airfoil comprising:
a serpentine core portion configured to provide an inlet extending to a first passageway, and a second passageway fluidly connected to the first passageway to form a U-shaped cooling passage, wherein the first and second passageways provide an up-pass passageway and a down-pass passageway that form the U-shaped cooling passage, wherein the first and second passageways are spaced apart from one another in a chord-wise direction, the serpentine cooling passage terminates at the platform at a second passageway end of the U-shaped cooling passage; and
a platform core portion configured to provide a platform cooling passageway arranged transverse and connected to the second passageway, wherein the platform cooling passageway is configured to extend along a pressure side of the platform, wherein the platform cooling passageway is configured to extend along a suction side of the platform, or wherein the platform cooling passageway is configured to extend along a pressure side and a suction side of the platform; and
wherein the platform cooling passageway has a first portion that extends generally circumferentially from the second passageway end to a second portion that extends generally axially.
2. The core for a gas turbine engine airfoil according to claim 1 , wherein the first passageway is an up-pass passageway and the second passageway is a down-pass passageway, the down-pass passageway terminates near the platform cooling passageway.
3. The core for a gas turbine engine airfoil according to claim 1 , wherein the first passageway is an up-pass passageway and the second passageway is a down-pass passageway, the platform cooling passageway is generally normal to the down-pass passageway.
4. The core for a gas turbine engine airfoil according to claim 1 , wherein the platform core portion extends in opposite directions from serpentine core portion.
5. The core for a gas turbine engine airfoil according to claim 1 , comprising multiple cooling holes fluidly connecting the platform cooling passageway to an exterior airfoil surface, wherein the cooling holes extend generally radially outward from the second portion.
6. The core for a gas turbine engine airfoil according to claim 1 , wherein the first and second portions of the platform cooling passageway form a T shape.
7. The core for a gas turbine engine airfoil according to claim 1 , wherein the second portion of the platform cooling passageway extends axially forward and aft of the first portion.