Small radial profile shroud for variable vane structure in a gas turbine engine

• US 7,713,022 B2
• Filed: 03/06/2007
• Issued: 05/11/2010
• Est. Priority Date: 03/06/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Operations
• Inventors: Torres, Edward, Burge, Joseph C., Major, Daniel W.
• Primary Examiner(s): Edgar; Richard
• Application Number:
  US11/682,358
• Publication Number:
  US 20080219832A1
• Time in Patent Office: 1,162 Days
• Field of Search: 415/209.3, 415/209.2, 415/160, 415/159, 415/191, 298/892.2, 416/214.A, 416/214.R
• US Class Current: 415/160
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F02C 9/20 by throttling; by adjusting vanes
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05B 2260/301 Retaining bolts or nuts
• CPC Class Codes: Y10T 29/49323 Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Abstract

A shroud for supporting a variable vane in a compressor section for a gas turbine engine includes a pair of components which are secured together by a threaded fastener extending into a blind hole in one of the two components. Additional material forms on the component which includes the blind hole extends beyond a pivot axis for the vane such that there is an increased length of engagement between the threaded fastener and the blind hole. The blind hole eliminates the need for multiple nuts and reduces the radial height of the shroud to save additional weight.

Claims

1. A shroud for supporting a variable vane in a compressor for a gas turbine engine comprising:

at least two components extending circumferentially, to support a radially inner trunnion on a variable vane and said at least two components being connected by a threaded fastener member extending through a hole in a first of said at least two components and into a blind hole in a second of said at least two components and wherein one of said components has additional material extending therefrom that is adapted to engage said threaded fastener and wherein said additional material is disposed within a slot within said other component.

2. The shroud as set forth in claim 1, wherein there are only two of said components, and each of said two components extend circumferentially for 360°

about a central axis.

3. The shroud as set forth in claim 1, wherein there is an upstream component and a downstream component, and said second component is said upstream component.

4. The shroud as set forth in claim 1, wherein said both components having a support surface for supporting the inner trunnion, with said second component having said additional material for extending beyond a pivot axis of the variable vane, said additional material including said blind hole to increase a threaded securement length of said threaded fastener within said blind hole.

5. The shroud as set forth in claim 4, wherein said additional material extends from locations circumferentially spaced between the support positions for mounting the inner trunnion, and into said slots in said first component.

6. The shroud as set forth in claim 4, wherein a bearing is mounted between the inner trunnion and support surfaces.

7. The shroud as set forth in claim 6, wherein an anti-rotation surface is formed on one of said at least two components, and said bearing having structure for engaging said anti-rotation surface.

8. The shroud as set forth in claim 7, wherein said bearing is formed of two separate parts, and at least one of said parts having a flat surface, said anti-rotation surface also being flat, and said flat surfaces being aligned with each other to prevent rotation of said bearing relative to support surfaces.

9. The shroud as set forth in claim 4, wherein each of said components having a radially outer support surface for supporting a radially outer portion of an inner peg, and a radially inner support surface for supporting a radially inner portion of the inner trunnion, and said additional material extending circumferentially between said radially inner support surfaces.

10. A compressor section for use in a gas turbine comprising:

a plurality of rotors for rotation about an axial center line and at least one variable vane assembly positioned axially intermediate said plurality of rotor stages; and

an inner shroud for mounting a radially inner portion of a variable vane in said variable vane assembly, and an actuator mechanism for causing said variable vane to pivot about a pivot axis, said inner shroud including at least two components extending circumferentially, to support a radially inner trunnion on said variable vane and said at least two components being connected by a threaded fastener member extending though a hole in a first of said at least two components and into a blind hole in a second of said at least two components and wherein one of said components has additional material extending therefrom that is adapted to engage said threaded fastener and wherein said additional material is disposed within a slot within said other component.

11. The compressor section as set forth in claim 10, wherein there are only two of said components, and each of said two components extend circumferentially for 360°

about said axis.

12. The compressor section as set forth in claim 10, wherein there is an upstream component and a downstream component, and said second component is said upstream component.

13. The compressor section as set forth in claim 10, wherein said components both having a support surface for supporting said radially inner trunnion with said second component having said additional material extending beyond the pivot axis, said additional material including said blind hole to increase a threaded securement length of said threaded fastener within said blind hole.

14. The compressor section as set forth in claim 13, wherein said additional material extends from locations circumferentially spaced between the support positions for mounting said inner trunnion, and into said slots in said first component.

15. The compressor section as set forth in claim 13, wherein a bearing is mounted between said inner trunnion and said support surfaces.

16. The compressor section as set forth in claim 15, wherein an anti-rotation surface is formed on one of said at least two components, and said bearing having structure for engaging said anti-rotation surface.

17. The compressor section as set forth in claim 16, wherein said bearing is formed of two separate parts, and at least one of said parts having a flat surface, said anti-rotation surface also being flat, and said flat surfaces being aligned with each other to prevent rotation of said bearing relative to said support surfaces.

18. The compressor as set forth in claim 13, wherein each of said components having a radially outer support surface for supporting a radially outer portion of said inner trunnion, and a radially inner support surface for supporting a radially inner portion of said inner trunnion, and said additional material extending circumferentially between said radially inner support surfaces.