Turbine airfoil with minicore passage having sloped diffuser orifice

Patent metadata

Field	Value
Publication number	US-10968752-B2
Application number	US-201916373008-A
Country	US
Kind code	B2
Filing date	Apr 2, 2019
Priority date	Jun 19, 2018
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.

First claim

What is claimed is:

1. A turbine airfoil comprising:
an airfoil outer wall defining leading and trailing ends and first and second sides joining the leading and trailing ends, the airfoil outer wall circumscribing an internal cavity; and
at least one cooling passage embedded in the airfoil outer wall, the at least one cooling passage having a radially-elongated entrance manifold fluidly connected to receive cooling air from the internal cavity, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice, the radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold, the radially-elongated diffuser orifice is sloped at an angle relative to the radially-elongated entrance manifold, the airfoil outer wall has a span in centimeters between an inner and outer end, and a ratio of the angle to the span is from 8 to 15.

2. The turbine airfoil as recited in claim 1 , wherein the radially-elongated diffuser orifice has a rhomboid shape.

3. The turbine airfoil as recited in claim 1 , wherein the radially-elongated entrance manifold defines a forward perimeter edge and the radially-elongated diffuser orifice defines a central axis, wherein the central axis is sloped relative to the forward perimeter edge.

4. The turbine airfoil as recited in claim 1 , wherein the radially elongated diffuser orifice defines radially inner and outer sides and axially forward and aft sides, wherein the radially inner and outer sides are parallel with an axial direction that corresponds to a central axis of a turbine engine.

5. The turbine airfoil as recited in claim 1 , wherein the at least one cooling passage includes first and second cooling passages that are sloped in opposite directions.

6. The turbine airfoil as recited in claim 5 , further comprising an additional cooling passage embedded in the airfoil outer wall, the additional cooling passage also having a radially-elongated entrance manifold fluidly connected to receive cooling air from the internal cavity, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice, wherein the radially-elongated diffuser orifice of the additional cooling passage is parallel to the radially-elongated entrance manifold.

7. The turbine airfoil as recited in claim 6 , wherein the additional cooling passage is radially between the first and second cooling passages.

8. The turbine airfoil as recited in claim 1 , wherein the radially-elongated diffuser orifice is sloped at an angle of 1° to 45° relative to the radially-elongated entrance manifold.

9. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
the turbine section having a turbine airfoil that includes
an airfoil outer wall defining leading and trailing ends and first and second sides joining the leading and trailing ends, the airfoil outer wall circumscribing an internal cavity, and
at least one cooling passage embedded in the airfoil outer wall, the at least one cooling passage having a radially-elongated entrance manifold fluidly connected to receive cooling air from the internal cavity, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice, the radially-elongated diffuser orifice being elongated along a central axis extending between radially inner and outer sides of the radially-elongated diffuser orifice, the radially-elongated entrance manifold defining a forward perimeter edge that extends in a radial direction, and the central axis of the radially-elongated diffuser orifice is continuously sloped relative to the forward perimeter edge of the radially-elongated entrance manifold in the radial direction.

10. The gas turbine engine as recited in claim 9 , wherein the radially-elongated diffuser orifice has a rhomboid shape.

11. The gas turbine engine as recited in claim 9 , wherein the radially elongated diffuser orifice defines axially forward and aft sides, wherein the radially inner and outer sides are parallel with an axial direction that corresponds to a central axis of a turbine engine.

12. The gas turbine engine as recited in claim 9 , wherein the at least one cooling passage includes first and second cooling passages that are sloped in opposite directions.

13. The gas turbine engine as recited in claim 12 , further comprising an additional cooling passage embedded in the airfoil outer wall radially between the first and second cooling passages, the additional cooling passage also having a radially-elongated entrance manifold fluidly connected to receive cooling air from the internal cavity, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice, wherein the radially-elongated diffuser orifice of the additional cooling passage is parallel to the radially-elongated entrance manifold.

14. A turbine airfoil comprising:
an airfoil outer wall defining leading and trailing ends and first and second sides joining the leading and trailing ends, the airfoil outer wall circumscribing an internal cavity; and
a plurality of cooling passages embedded in the airfoil outer wall, each said cooling passage having a radially-elongated entrance manifold fluidly connected to receive cooling air from the internal cavity, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice, each said radially-elongated entrance manifold defining a forward perimeter edge, and the radially-elongated diffuser orifice is sloped at an angle relative to the forward perimeter edge, the airfoil outer wall has a span in centimeters between an inner and outer end, and a ratio of the angle to the span is from 8 to 15.

15. The turbine airfoil as recited in claim 14 , wherein the radially-elongated diffuser orifice has a rhomboid shape.

16. The turbine airfoil as recited in claim 14 , wherein the radially elongated diffuser orifice defines radially inner and outer sides and axially forward and aft sides, wherein the radially inner and outer sides are parallel with an axial direction that corresponds to a central axis of a turbine engine.

17. The gas turbine as recited in claim 1 , wherein the radially-elongated diffuser orifice is sloped at an angle of 10° to 30° relative to the forward perimeter edge of the radially-elongated entrance manifold.

18. The gas turbine engine as recited in claim 17 , wherein the trailing end is convex.

Assignees

• Raytheon Tech Corp

Inventors

• Auxier James Tilsley
• Propheter-Hinckley Tracy A
• Arisi Allan N

Classifications

• F01D5/187

  Convection cooling · CPC title

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2240/304

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

• F05D2260/204

  by the use of microcircuits · CPC title

• F05D2260/202

  by film cooling · CPC title