Airfoil having serpentine core resupply flow control

Patent metadata

Field	Value
Publication number	US-10612394-B2
Application number	US-201715656020-A
Country	US
Kind code	B2
Filing date	Jul 21, 2017
Priority date	Jul 21, 2017
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

Airfoils and airfoil cores for airfoils of gas turbine engines are provided. The airfoils include an airfoil body having a leading edge and a trailing edge, at least two serpentine flow cavities formed within the airfoil body, a resupply cavity fluidly connected to one serpentine flow cavity of the at least two serpentine flow cavities and arranged to supply a resupply air to the one serpentine flow cavity through a resupply bypass hole, a junction defined at a location where the resupply cavity fluidly connect to the one serpentine flow cavity, a separator rib within the airfoil body and fluidly separating part of the at least two serpentine flow cavities, at least one crossover rib located between the resupply bypass hole and the separator rib, and at least one crossover aperture located between the at least one crossover rib and the separator rib.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, the airfoil comprising:
an airfoil body having a leading edge and a trailing edge;
a first serpentine cavity formed within the airfoil body and defining a portion of a serpentine cooling flow path and enabling a cooling flow in a first direction within the airfoil body;
a second serpentine cavity fluidly connected to the first serpentine cavity and defining another portion of the serpentine cooling flow path and enabling a cooling flow in a second direction; and
a third serpentine cavity fluidly connected to the second serpentine cavity and defining another portion of the serpentine cooling flow path and enabling a cooling flow in at least one of the first direction or a third direction, wherein a serpentine cooling air flows through the serpentine cooling flow path;
a resupply cavity fluidly connected to the third serpentine cavity and arranged to supply a resupply air to the third serpentine cavity through a resupply bypass hole;
a junction defined where both the second serpentine cavity and the resupply cavity fluidly connect to the third serpentine cavity; and
a separator rib within the airfoil body and fluidly separating part of the first serpentine cavity from the second serpentine cavity,
wherein the separator rib includes at least one crossover rib located between the resupply bypass hole and
at least one crossover aperture that is formed in the separator rib to fluidly connect the resupply cavity to at least one of the second serpentine cavity and the third serpentine cavity.

2. The airfoil of claim 1 , comprising a plurality of crossover ribs located between the resupply bypass hole and the separator rib and a plurality of crossover apertures defined in part by the crossover ribs.

3. The airfoil of claim 1 , wherein the at least one crossover aperture includes a fillet.

4. The airfoil of claim 1 , further comprising a platform wherein the airfoil body extends from the platform, wherein the junction is located where the platform and airfoil body join.

5. The airfoil of claim 4 , further comprising an attachment, the attachment extending from the platform from a side of the platform opposite from the airfoil body.

6. The airfoil of claim 1 , further comprising a serpentine inlet arranged to supply serpentine cooling air into the one of the at least two serpentine flow cavities.

7. The airfoil of claim 6 , wherein a portion of the resupply air is fed into the serpentine cooling air at a location upstream from the resupply bypass hole.

8. The airfoil of claim 1 , wherein at least one crossover aperture is circular, elliptical, or “racetrack” shaped.

9. A core for manufacturing an airfoil of a gas turbine engine, the core comprising:
a first serpentine cavity core arranged to define a first serpentine cavity with a cooling flow in a first direction within a formed airfoil body;
a second serpentine cavity core connected to the first serpentine cavity core and arranged to define a second serpentine cavity with a cooling flow in a second direction within the formed airfoil body; and
a third serpentine cavity core connected to the second serpentine cavity core and arranged to define a third serpentine cavity with a cooling flow in at least one of the first direction or a third direction within the formed airfoil body;
a resupply cavity core connected to one of the serpentine cavity cores by a bypass core and arranged to form a resupply cavity in the formed airfoil body and a resupply bypass hole defined by the bypass core, wherein a core junction is defined and located at a location of the resupply cavity core, the bypass core, the second serpentine cavity core, and the third serpentine cavity core are connected; and
at least one crossover core located in the core junction to define a respective crossover aperture, with
a separator rib void located between a portion of the first serpentine cavity core and the second serpentine cavity core and ending at the at least one crossover core to define a separator rib in the formed airfoil and
at least one crossover void located between the at least one crossover core and the bypass core, the at least one crossover void forming a crossover rib within the formed airfoil body as part of the formed separator rib.

10. The core of claim 9 , further comprising a plurality of crossover cores, and a plurality of crossover voids located between the plurality of crossover cores, the separator rib void, and the bypass core.

11. The core of claim 9 , wherein the at least one crossover core includes a fillet.

12. The core of claim 9 , wherein at least one crossover core is circular, elliptical, or “racetrack” shaped.

Assignees

• United Technologies Corp

Inventors

• Thistle Charles
• Molony Evan P
• Clum Carey

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D25/12

  Cooling · CPC title