Airfoil cooling passageways for generating improved protective film

Patent metadata

Field	Value
Publication number	US-10280763-B2
Application number	US-201615177074-A
Country	US
Kind code	B2
Filing date	Jun 8, 2016
Priority date	Jun 8, 2016
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

An airfoil for a gas turbine engine, the airfoil comprising a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface, the passageway having one or more sections between the first opening and the second opening, the one or more sections in fluid communication with each other, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the passageway, a second diffuser section providing a second change in cross-sectional area within the passageway, a flow conditioning section, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening.

First claim

The invention claimed is:

1. An airfoil for a gas turbine engine, the airfoil comprising:
a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface,
the passageway having a plurality of sections between the first opening and the second opening, the plurality of sections in fluid communication with each other, the plurality of sections comprising:
a first diffuser section providing a first change in cross-sectional area within the passageway;
a second diffuser section providing a second change in cross-sectional area within the passageway;
a flow conditioning section located between the first diffuser section and the second diffuser section, the flow conditioning section having a constant cross-sectional area; and
an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening,
wherein surfaces of the flow conditioning section extend in parallel to a central axis extending through the wall in an axial direction of the passageway, and wherein each of the first and the second diffuser sections has a surface angle of 5 to 15 degrees relative to the surfaces of the flow conditioning section.

2. The airfoil of claim 1 , wherein the plurality of sections further comprises:
a flow controlling section beginning at the first opening opposite the edge section and extending to the first diffuser section.

3. The airfoil of claim 2 , wherein the constant cross-sectional area of the flow conditioning section is 1.8 to 3.6 times larger than a cross-sectional area of the flow controlling section.

4. The airfoil of claim 3 , wherein the first diffuser section increases its cross-sectional area from a first cross-sectional area to a second cross-sectional area, and wherein the second diffuser section increases its cross-sectional area from the second cross-sectional area to a third cross-sectional area.

5. The airfoil of claim 2 , wherein surfaces of the flow controlling section extend in parallel to the central axis.

6. The airfoil of claim 5 , wherein surfaces of each of the plurality of sections that extend through the wall are centered on a longitudinal axis.

7. The airfoil of claim 5 , wherein the passageway extends through the wall at an angle such that the central axis is not normal to the first surface or the second surface.

8. The airfoil of claim 7 further comprising:
a perimeter of the second opening including a portion of the edge section and a portion of the second diffuser section.

9. The airfoil of claim 8 , wherein the passageway comprises a channel in the wall at the edge section.

10. The airfoil of claim 1 , wherein the flow conditioning section has a length to hydraulic diameter ratio of 0.6 to 1.4.

11. The airfoil of claim 1 , wherein the wall further comprises a plurality of passageways extending between the first surface and second surface.

12. The airfoil of claim 11 , wherein a minimum distance on the second surface between a first passageway of the plurality of passageways and an adjacent second passageway of the plurality of passageways is 0.015 inches to 0.035 inches.

13. The airfoil of claim 12 , further comprising a spacing wall extending from the first surface to the second surface, the spacing wall preventing fluid communication between the first passageway and the second passageway.

14. A method of manufacturing an airfoil for a gas turbine engine, the airfoil having at least one passageway through a wall, the method comprising the steps of:
providing an airfoil having a wall, the wall extending from a first surface to a second surface; and
forming one or more passageways through the wall, wherein the one or more passageways each extends from a respective first opening in the first surface to a respective second opening in the second surface,
wherein each of the one or more passageways includes a plurality of sections between the respective first opening and the respective second opening, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the respective passageway, a second diffuser section providing a second change in cross-sectional area within the respective passageway, a flow conditioning section located between the first and second diffuser sections, the flow conditioning section having a constant cross-sectional area across its length, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening, wherein surfaces of the flow conditioning section extend in parallel to a central axis extending through the wall in an axial direction of the passageway, and wherein each of the first and the second diffuser sections has a surface angle of 5 to 15 degrees relative to the surfaces of the flow conditioning section.

15. The method of claim 14 , wherein the step of forming one or more passageways through the wall further comprises:
providing an electrode having one or more shaped electrode teeth;
the one or more shaped electrode teeth comprising a plurality of tooth sections, the plurality of tooth sections each including a constant width section, a first expansion section, a first constant area section, a second expansion section, a second constant area section, and a leading tip section; and
forming the at least one passageway by plunging a portion of the electrode through the wall.

16. The method of claim 15 , wherein the step of forming one or more passageways through the wall comprises performing an EDM plunge process.

17. The method of claim 15 , wherein the one or more shaped electrode teeth are aligned in a row.

18. An improved cooling hole for a turbine of a gas turbine engine comprising:
a first opening formed in an inner surface of a turbine airfoil wall and adapted to communicate a cooling fluid from within the airfoil, through a plurality of cavities, and out of a second opening formed in an outer surface of the airfoil wall;
a flow controlling cavity extending outwardly through a portion of the airfoil wall from the first opening;
a first diffusing cavity extending through a portion of the airfoil wall from the flow controlling cavity to a flow conditioning cavity, the first diffusing cavity having a first end located proximate to the flow controlling cavity, a second end located proximate to the flow conditioning cavity, the first end having a first cross-sectional area and the second end having a second cross-sectional area, the first cross-sectional area is smaller than the second cross-sectional area;
the flow conditioning cavity extending through a portion of the airfoil wall from the first diffusing cavity to a second diffusing cavity, the flow conditioning cavity having a constant cross-sectional area across its length;
the second diffusing cavity extending through a portion of the airfoil wall from the flow conditioning cavity to an edge cavity, the second diffusing cavity having a third end and a fourth end, the third end having the second cross-sectional area and the fourth end having a third cross-sectional area, the second cross-sectional area is smaller than the third cross-sectional area; and
the edge cavity extending through a portion of the airfoil wall from the second diffusin

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Torkaman Alex
• Vogel Gregory
• Johnston Christopher
• Borja Michele

Classifications

• F01D25/12

  Cooling · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/186 Primary

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