Double wall turbine gas turbine engine blade cooling configuration

Patent metadata

Field	Value
Publication number	US-10626735-B2
Application number	US-201715832430-A
Country	US
Kind code	B2
Filing date	Dec 5, 2017
Priority date	Dec 5, 2017
Publication date	Apr 21, 2020
Grant date	Apr 21, 2020

Abstract

An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A slot extends longitudinally in the skin passage. A resupply hole fluidly interconnects the core passage and the slot.

First claim

What is claimed is:

1. An airfoil comprising:
pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, a skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core passage, the core passage and the skin passage are configured to have a same direction of fluid flow, a slot extends longitudinally in the skin passage, and a resupply hole fluidly interconnects the core passage and the slot, wherein the resupply hole terminates in an exit at the slot, the exit is provided by a diffuser.

2. The airfoil of claim 1 , a centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulent flow region in the skin passage.

3. The airfoil of claim 2 , wherein the angle is in a range of 5°-45°.

4. The airfoil of claim 3 , wherein the skin passage has an aspect ratio that may vary between 3:1≥H/W≥1:5, wherein H corresponds to a passage height and W corresponds to a passage width.

5. The airfoil of claim 4 , wherein the passage height (H) is in a range of 0.010-0.200 inches (0.25-5.08 mm).

6. The airfoil of claim 3 , comprising serpentine cooling passage having first, second and third cooling passages, the first and third cooling passages having a direction of fluid flow toward the tip, and the second cooling passage having a direction of fluid flow away from the tip, the core passage provided by one of the first, second and third cooling passages.

7. The airfoil of claim 3 , wherein a film cooling hole extends from the skin passage to the exterior airfoil surface.

8. The airfoil of claim 3 , wherein the airfoil is a turbine blade.

9. The airfoil of claim 3 , wherein the slot extends longitudinally in a direction that is different than the direction of fluid flow.

10. The airfoil of claim 9 , wherein the direction of fluid flow is the radial direction.

11. The airfoil of claim 3 , wherein multiple resupply holes feed the slots from the core passage.

12. An airfoil comprising:
pressure and suction side walls extending in a chord-wise direction between leading and trailing edges, the pressure and suction side walls extending in a radial direction to provide an exterior airfoil surface, a core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip, a skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core passage, the core passage and the skin passage are configured to receive a cooling fluid from the compressor section and have a same direction of fluid flow, a slot extends longitudinally in the skin passage, and a resupply hole fluidly interconnects the core passage and the slot, a centerline of the resupply hole is arranged at an acute angle relative to the direction of fluid flow in the core passage and is configured to provide a low turbulent flow region in the skin passage.

13. The airfoil of claim 12 , wherein the angle is in a range of 5°-45°.

14. The airfoil of claim 13 , wherein the skin passage has an aspect ratio that may vary between 3:1≥H/W≥1:5, wherein H corresponds to a passage height and W corresponds to a passage width, wherein the passage height (H) is in a range of 0.010-0.200 inches (0.25-5.08 mm).

15. The airfoil of claim 13 , wherein the slot extends longitudinally in a direction that is different than the direction of fluid flow.

16. The airfoil of claim 15 , wherein the slot extends longitudinally in a direction that is normal to the direction of fluid flow.

17. The airfoil of claim 15 , wherein the direction of fluid flow is the radial direction.

18. The airfoil of claim 13 , wherein multiple resupply holes feed the slots from the core passage.

Assignees

• United Technologies Corp

Inventors

• Whitfield Christopher
• Clum Carey
• Mongillo Jr Dominic J

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/24

  for turbines · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2260/202

  by film cooling · CPC title