Turbine frame and airfoil for turbine frame

Patent metadata

Field	Value
Publication number	US-9784133-B2
Application number	US-201514676385-A
Country	US
Kind code	B2
Filing date	Apr 1, 2015
Priority date	Apr 1, 2015
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

A turbine frame for a turbine engine having an axial centerline, the turbine frame comprising an inner hub, an outer hub encircling the inner hub, a plurality of struts extending between the inner and outer hubs and having a maximum width portion relative to the axial centerline and an airfoil comprising at least first and second fairings mounted to the inner and outer hubs and encircling one of the struts.

First claim

What is claimed is:

1. An airfoil for a turbine frame having inner and outer hubs connected by a plurality of struts with a maximum width portion relative to an axial center of the turbine frame, the turbine frame having a forward and an aft, the airfoil comprising:
at least first and second fairings connected together along first and second join lines to form the airfoil and define an interior sized to receive one of the struts when the first and second fairings are mounted to the turbine frame;
a low pressure surface; and
a high pressure surface;
wherein each of the first and second fairings form at least a portion of each of the low and high pressure surfaces;
wherein the first join line is located such that the first join line is forward of the maximum width portion and the second join line is aft of the maximum width portion when the first and second fairings are mounted to the turbine frame and a strut is received within the interior, and
wherein the first fairing comprises more than half of the area of the high pressure surface and the second fairing comprises more than half of the area of the low pressure surface.

2. The airfoil of claim 1
wherein the first join line intersects with the outer periphery of the airfoil on the high pressure surface and the second join line intersects with the outer periphery of the airfoil on the low pressure surface.

3. The airfoil of claim 1 further comprising a first stiffener extending between the first and second fairings and the first join line is located at the first stiffener,
wherein the first fairing encapsulates a trailing edge of the airfoil and the second fairing encapsulates a leading edge of the airfoil.

4. The airfoil of claim 3 further comprising a second stiffener extending between the first and second fairings and the second join line is located at the second stiffener.

5. The airfoil of claim 4 wherein the first and second stiffeners are axially spaced from each other and the interior is located between the first and second stiffeners.

6. The airfoil of claim 1 wherein the airfoil has an asymmetrical cross section relative to an axis parallel to the axial direction of the engine.

7. The airfoil of claim 1 wherein the first and second fairings have opposing end plates mounted to a corresponding one of the inner and outer hubs.

8. An airfoil for a turbine frame having radially spaced, inner and outer hubs connected by a plurality of struts with the turbine frame defining an axial centerline, the airfoil comprising:
at least first and second fairings connected together along first and second join lines to form the airfoil and the first join line is located axially forward of the second join line;
a low pressure surface; and
a high pressure surface,
wherein each of the first and second fairings form at least a portion of each of the low and high pressure surfaces;
wherein the first fairing comprises a majority of the area of the high pressure surface and the second fairing comprises a majority of the area of the low pressure surface.

9. The airfoil of claim 8 further comprising a low pressure surface and a high pressure surface, and each of the first and second fairings form at least a portion of each of the low and high pressure surfaces.

10. The airfoil of claim 8 further comprising a first stiffener extending between the first and second fairings and the first join line is located at the first stiffener.

11. The airfoil of claim 10 further comprising a second stiffener extending between the first and second fairings and the second join line is located at the second stiffener.

12. The airfoil of claim 8 wherein the first and second stiffeners are axially spaced from each other.

13. A turbine frame for a turbine engine having an axial centerline, the turbine frame comprising:
an inner hub;
an outer hub encircling the inner hub;
a first plurality of vanes extending between the inner and outer hubs, the first plurality of vanes comprising:
a plurality of struts extending between the inner and outer hubs and having a maximum width portion relative to the axial centerline;
an airfoil comprising at least first and second fairings mounted to the inner and outer hubs and encircling one of the plurality of struts, and abutting along first and second join lines, with the first join line located axially forward of the second join line;
a low pressure surface of the airfoil; and
a high pressure surface of the airfoil, each of the first and second fairings forming at least a portion of each of the low and high pressure surfaces;
wherein the first fairing comprises more than half of the area of the high pressure surface and the second fairing comprises more than half of the area of the low pressure surface;

a second plurality of vanes circumferentially distributed around the turbine frame and extending between the inner and outer hub.

14. The turbine frame of claim 13 wherein each one of the plurality of struts has a maximum width portion and the first and second join lines are located on axially opposite sides of the maximum width portion,
wherein the second plurality of vanes comprises a greater number of vanes than the first plurality of vanes.

15. The turbine frame of claim 13 wherein the width of the airfoil at one of the first and second join lines is less than the maximum width portion,
wherein the first join line intersects with the outer periphery of the airfoil on the high pressure surface and the second join line intersects with the outer periphery of the airfoil on the low pressure surface; and
wherein the first fairing encapsulates a trailing edge of the airfoil and the second fairing encapsulates a leading edge of the airfoil.

16. The turbine frame of claim 15 wherein the width of the airfoil at each of the first and second join lines is less than the maximum width portion.

17. The turbine frame of claim 15 further comprising a first stiffener extending between the first and second fairings and the first join line is located at the first stiffener,
wherein the airfoil has an asymmetrical cross section relative to an axis parallel to the axial direction.

18. The turbine frame of claim 17 further comprising a second stiffener extending between the first and second fairings and the second join line is located at the second stiffener.

19. The turbine frame of claim 18 wherein the first and second stiffeners are axially spaced from each other and an interior is located between the first and second stiffeners.

20. The turbine frame of claim 19 wherein the first and second fairings have opposing end plates mounted to a corresponding one of the inner and outer hubs.

Assignees

• Gen Electric

Inventors

• Karafillis Apostolos Pavlos
• Frash Martin Wayne
• Ortega Schuyler Javier
• Parisi Angelo

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D25/162 Primary

  Bearing supports · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F01D9/042

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title