Double wall turbine gas turbine engine blade cooling configuration

Patent metadata

Field	Value
Publication number	US-10590779-B2
Application number	US-201715832491-A
Country	US
Kind code	B2
Filing date	Dec 5, 2017
Priority date	Dec 5, 2017
Publication date	Mar 17, 2020
Grant date	Mar 17, 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 resupply hole fluidly interconnects the core and skin passages. 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 turbulence flow region in the skin passage.

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, and a resupply hole fluidly interconnects the core and skin passages, 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 turbulence flow region in the skin passage, wherein the angle is in a range of 5°-45°, the skin passage has an aspect ratio that varies between 3:1≥H/W≥1:5, wherein H corresponds to a passage height and W corresponds to a passage width, the passage height (H) is in a range of 0.010-0.200 inches (0.25-5.08 mm).

2. The airfoil of claim 1 , wherein the resupply hole has an exit at the skin passage, the exit has a diffuser.

3. The airfoil of claim 1 , 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.

4. The airfoil of claim 1 , wherein a film cooling hole extends from the skin passage to the exterior airfoil surface.

5. The airfoil of claim 1 , wherein the airfoil is a turbine blade.

6. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a kidney shape with a concave side and a convex side joined by opposing curved sides, and cooling fluid is configured to flow out of the exit from the concave side toward the convex side.

7. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has an hourglass shape with a pair of concave sides joined by opposing curved sides, and cooling fluid is configured to flow out of the exit from one of the concave sides toward the other of the concave sides.

8. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a kidney shape with a concave side and a flat side joined by opposing curved sides, and cooling fluid is configured to flow out of the exit from the concave side toward the flat side.

9. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a tri-lobular shape with three concave sides joined by three curved sides, and cooling fluid is configured to flow out of the exit from one of the concave sides toward the one of the curved sides.

10. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a triangular shape with three flat sides and three corners, and cooling fluid is configured to flow out of the exit from one of the three flat sides toward one of the three corners.

11. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has an oval shape with major and minor axes, and cooling fluid is configured to flow out of the exit along the minor axis.

12. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a flat oval shape with a pair of flat sides joined by opposing curved sides, and cooling fluid is configured to flow out of the exit from one of the flat sides toward the other of the flat sides.

13. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a crescent shape with a concave side and a convex side joined at opposing corners, and cooling fluid is configured to flow out of the exit from the concave side toward the convex side.

14. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a crescent shape with a concave side and a convex side joined at opposing corners, and cooling fluid is configured to flow out of the exit from the convex side toward the concave side.

15. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a kidney shape with a concave side and a convex side joined by opposing curved sides, and cooling fluid is configured to flow out of the exit from the convex side toward the concave side.

16. The airfoil of claim 1 , wherein the resupply hole includes an exit at the skin passage, a cross-section of the resupply hole has a diamond shape with four corners, and cooling fluid is configured to flow out of the exit from one of the four corners toward another of the four corners.

17. A gas turbine engine comprising:
a combustor section arranged fluidly between compressor and turbine sections; and
an airfoil arranged in the turbine section, the airfoil including 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, and a resupply hole fluidly interconnects the core and skin passages, 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 laminar flow region in the skin passage, wherein the angle is in a range of 5°-45°, wherein the skin passage has an aspect ratio that varies 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).

Assignees

• United Technologies Corp

Inventors

• Whitfield Christopher
• Clum Carey
• Mongillo Jr Dominic J

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2250/13

  trapezoidal · CPC title

• F05D2260/2212

  by creating turbulence · CPC title