Gas turbine engines with airfoils having improved dust tolerance

Patent metadata

Field	Value
Publication number	US-10655476-B2
Application number	US-201715841844-A
Country	US
Kind code	B2
Filing date	Dec 14, 2017
Priority date	Dec 14, 2017
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

An airfoil for a gas turbine engine includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; and an internal cooling system arranged within the first and second side walls configured to direct cooling air through and out of the airfoil. The internal cooling system has a first cooling circuit that includes an acceleration channel generally extending in a radial outward direction. A first section of the acceleration channel decreases in cross-sectional area along the radial outward direction such that the cooling air is accelerated through the first section of the acceleration channel. The first cooling circuit further includes a trailing edge chamber fluidly coupled to receive at least a portion of the cooling air from the acceleration channel and extending generally in a chordwise aft direction from the acceleration channel to the trailing edge.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, comprising:
a first side wall;
a second side wall joined to the first side wall at a leading edge and a trailing edge, the first and second side walls extending in a radial outward direction from a base coupled to an airfoil platform; and
an internal cooling system arranged within the first and second side walls configured to direct cooling air through and out of the airfoil, the internal cooling system including a first cooling circuit comprising:
an acceleration channel generally extending in a radial outward direction and receiving cooling air from a first source, wherein at least a first section of the acceleration channel decreases in cross-sectional area along the radial outward direction such that the cooling air is accelerated through the first section of the acceleration channel, the acceleration channel defined in a radial outward direction by a forward radial internal wall that extends radially from a chordwise wall, with a portion of the chordwise wall having a curved surface to transition from the forward radial internal wall to a trailing edge chamber;
the trailing edge chamber fluidly coupled to receive at least a portion of the cooling air from the acceleration channel and extending generally in a chordwise aft direction from the acceleration channel to the trailing edge; and
an aft radial internal wall extending between the acceleration channel and the trailing edge chamber, the aft radial internal wall cooperating with the forward radial internal wall to define the acceleration channel, the aft radial internal wall defining crossover passages that fluidly couple the acceleration channel to the trailing edge chamber, the aft radial internal wall extending from a chordwise orientation at a first end to a radial orientation at a second end, the first end spaced apart from an end of the forward radial internal wall to define an inlet for the acceleration channel and the second end spaced apart from the chordwise wall to form a slot interface between the acceleration channel and the trailing edge chamber.

2. The airfoil of claim 1 , wherein the first section of the acceleration channel continually decreases in the cross-sectional area along the radial outward direction such that the cooling air is continually accelerated through the first section of the acceleration channel.

3. The airfoil of claim 2 , wherein the first section of the acceleration channel extends from a last downstream crossover passage of the crossover passages to a downstream end of the acceleration channel.

4. The airfoil of claim 1 , wherein the curved surface has a constant radius of curvature or increasing radius of curvature.

5. The airfoil of claim 4 , wherein the trailing edge chamber is at least partially defined by a second portion of the chordwise wall that extends from the curved surface to the trailing edge of the airfoil.

6. The airfoil of claim 5 , wherein the chordwise wall has a radial height that increases along the chordwise aft direction.

7. The airfoil of claim 1 , wherein the internal radial wall has an enlarged radial end at a transition between the acceleration channel and the trailing edge chamber.

8. The airfoil of claim 7 , wherein the enlarged radial end is bulb-shaped.

9. The airfoil of claim 1 , wherein the acceleration channel is at least partially defined at a radial end by the curved surface of the portion of the chordwise wall, wherein a second portion of the chordwise wall that extends from the curved surface to the trailing edge of the airfoil includes at least a first crossover hole angled in the chordwise aft direction, the first crossover hole defined between the curved surface and the trailing edge of the airfoil.

10. The airfoil of claim 9 ,
further comprising a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip,
wherein the internal cooling system further includes a tip cap passage extending between the tip cap and the chordwise wall in the chordwise aft direction to the trailing edge, and wherein the first crossover hole fluidly couples the acceleration channel to the tip cap passage.

11. The airfoil of claim 10 , wherein the tip cap defines an exit hole aligned with the first crossover hole and angled in the chordwise aft direction, and configured to direct the cooling fluid through the first crossover hole and the exit hole in a generally straight line.

12. The airfoil of claim 1 , wherein the first cooling circuit includes a serpentine passage fluidly coupled to the acceleration channel as the first source, wherein the serpentine passage includes at least a first leg configured to direct the cooling air in the radial outward direction, a second leg configured to direct the cooling air in a radial inward direction, and a transition extending between the first and second legs.

13. The airfoil of claim 12 , wherein the transition is formed by an internal chordwise wall that includes at least one crossover hole.

14. An airfoil for a gas turbine engine, comprising:
a first side wall;
a second side wall joined to the first side wall at a leading edge and a trailing edge, the first and second side walls extending in a radial outward direction from a base coupled to an airfoil platform;
a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip; and
an internal cooling system arranged within the first and second side walls configured to direct cooling air through and out of the airfoil, the internal cooling system including:
a first cooling circuit comprising at least:
a leading edge cooling passage extending from a first source in the radial outward direction, and
a tip cap passage fluidly coupled to the leading edge cooling passage and extending in a chordwise aft direction between the leading edge cooling passage and the trailing edge, wherein the tip cap passage is at least partially formed by tip cap and a chordwise wall; and

a second cooling circuit comprising at least:
a serpentine passage including a first leg extending from a second source in the radial outward direction, a second leg extending in a radial inward direction, and a first transition fluidly coupling the first leg to the second leg, wherein the first transition is at least partially formed by the chordwise wall, and wherein the chordwise wall includes at least a first crossover hole at the first transition that fluidly couples the serpentine passage to the tip cap passage,
an acceleration channel fluidly coupled to the serpentine passage and generally extending in the radial outward direction, the acceleration channel defined by a forward radial internal wall that extends radially from the chordwise wall and an aft radial internal wall extending between the acceleration channel and a trailing edge chamber, the acceleration channel at least partially defined at a radial end by a second transition at least partially formed by the chordwise wall, and the chordwise wall includes at least a second crossover hole at the second transition that is angled in the chordwise aft direction to fluidly couple the acceleration channel to the tip cap passage and defines a slot that fluidly couples the acceleration channel to the trailing edge chamber, and
the trailing edge chamber fluidly coupled to the acceleration channel and extending generally in the chordwise aft direction from the acceleration channel to the trailing edge,
wherein the tip cap defines an exit hole aligned with the second crosso

Assignees

• Honeywell Int Inc

Inventors

• Halfmann Steve
• Crites Daniel C
• Morris Mark C
• Riahi Ardeshir

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2240/24

  for turbines · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F05D2220/32

  in gas turbines · CPC title