Double wall turbine gas turbine engine blade cooling configuration

Patent metadata

Field	Value
Publication number	US-10781697-B2
Application number	US-201715832455-A
Country	US
Kind code	B2
Filing date	Dec 5, 2017
Priority date	Dec 5, 2017
Publication date	Sep 22, 2020
Grant date	Sep 22, 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 at an outer surface and a cold side wall at an inner surface. The skin passage extends a height in the radial direction, a width in a width direction, and a thickness in a thickness direction. The thickness is less than the width. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage at a core passage surface. 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 first angle relative to the direction of fluid flow in the core passage. The first angle lies in a plane parallel to the thickness direction. The centerline of the resupply hole is arranged at a second angle relative to the direction of fluid flow in the core passage. The second angle lies in a plane parallel to the width direction. The second angle is at an acute angle. The first and second angles are 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 side 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 at an outer surface and a cold side wall at an inner surface, wherein the skin passage extends a length in the radial direction, a passage width in a width direction, and a passage height in a thickness direction, wherein the passage height is less than the passage width, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core passage at a core passage surface, the core passage and the skin passage are configured to have a direction of fluid flow that is the same as one another, and a resupply hole fluidly interconnects the core and skin passages, a centerline of the resupply hole is arranged at first angle relative to the direction of fluid flow in the core passage, the first angle lies in a plane parallel to the thickness direction, the centerline of the resupply hole is arranged at a second angle relative to the direction of fluid flow in the core passage, the second angle lies in a plane parallel to the width direction, the second angle is at an acute angle, and the first and second angles are configured to provide a low turbulence flow region in the skin passage, wherein the skin passage has an aspect ratio in a range of 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).

2. The airfoil of claim 1 , wherein the first angle is acute.

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

4. The airfoil of claim 1 , wherein the second angle is in a range of 15°-750.

5. The airfoil of claim 4 , wherein the second angle is in a range of 30°-60°.

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

7. The airfoil of claim 6 , wherein the exit has an edge at the inner surface that is perpendicular to the direction of fluid flow.

8. The airfoil of claim 6 , wherein the exit has an edge at the inner surface that is perpendicular to the centerline of the resupply hole.

9. The airfoil of claim 1 , comprising a 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.

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

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

12. 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 side 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 at an outer surface and a cold side wall at an inner surface, wherein the skin passage extends a length in the radial direction, a passage width in a width direction, and a passage height in a thickness direction, wherein the passage height is less than the passage width, the hot side wall defines a portion of the exterior airfoil surface, and the cold side wall defines a portion of the core passage at a core passage surface, the core passage and the skin passage are configured to have a direction of fluid flow that is the same as one another, and a resupply hole fluidly interconnects the core and skin passages, a centerline of the resupply hole is arranged at a first angle relative to the direction of fluid flow in the core passage, the first angle lies in a plane parallel to the thickness direction, the centerline of the resupply hole is arranged at a second angle relative to the direction of fluid flow in the core passage, the second angle lies in a plane parallel to the width direction, the second angle is at an acute angle, and the first and second angles are configured to provide a low turbulence flow region in the skin passage wherein the skin passage has an aspect ratio in a range of 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).

13. The gas turbine engine of claim 12 , wherein the first angle is acute.

14. The gas turbine engine of claim 12 , wherein the second angle is in a range of 15°-75°.

15. The gas turbine engine of claim 12 , wherein the resupply hole has an exit at the skin passage, the exit has a diffuser.

16. The gas turbine engine of claim 12 , wherein the airfoil is a turbine blade, comprising a 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.

17. The gas turbine engine of claim 16 , wherein a film cooling hole extends from the skin passage to the exterior airfoil surface.

Assignees

• Raytheon Tech Corp

Inventors

• Whitfield Christopher
• Clum Carey
• Mongillo Jr Dominic J

Classifications

• F05D2260/2212

  by creating turbulence · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2250/185

  serpentine-like · CPC title