Vane retainer

• US 10,502,077 B2
• Filed: 03/17/2016
• Issued: 12/10/2019
• Est. Priority Date: 03/17/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Torres, Edward
• Primary Examiner(s): Brockman, Eldon T
• Application Number:
  US15/073,008
• Publication Number:
  US 20170268357A1
• Time in Patent Office: 1,363 Days
• 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: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F02C 9/20 by throttling; by adjusting vanes
• CPC Class Codes: F04D 29/323 adjustable
• CPC Class Codes: F04D 29/54 Fluid-guiding means, e.g. diffusers
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/3217 for the first stage of a compressor or a low pressure compressor
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2240/14 Casings or housings protecting or supporting assemblies within
• CPC Class Codes: F05D 2250/181 ridged
• CPC Class Codes: F05D 2250/182 crenellated, notched
• CPC Class Codes: F05D 2260/31 Retaining bolts or nuts

Abstract

A vane retainer for a gas turbine engine includes a retainer body, an inner surface of the retainer body to engage complimentary threads of a mating component, and a plurality of castellations located at an end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the mating component. A gas turbine engine includes a combustor and a plurality of vane assemblies in fluid communication with the combustor. Each vane assembly includes a vane having an airfoil portion and a vane stem extending from the airfoil portion. The vane stem is inserted into a bushing. A vane retainer is engaged with the bushing and includes a retainer body, an inner surface of the retainer body to engage complimentary threads of the bushing, and a plurality of castellations located at an end of the retainer body for engagement with complementary installation tool features.

Claims

1. A vane retainer for a gas turbine engine comprising:

a retainer body;

a threaded inner surface of the retainer body configured to engage complimentary threads of an outer surface of a bushing installed to a casing, the bushing receptive of a vane stem; and

a plurality of castellations disposed at a distal end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the bushing.

2. The vane retainer of claim 1, wherein the plurality of castellations are equally spaced about a vane retainer axis.

3. The vane retainer of claim 1, wherein a castellation height is substantially equal to a castellation width.

4. The vane retainer of claim 1 further comprising a chamfer disposed at a top surface of the castellation.

5. The vane retainer of claim 1, further comprising a fillet disposed at a castellation base.

6. The vane retainer of claim 1, wherein the plurality of castellations is eight equally sized castellations.

7. A vane assembly for a gas turbine engine, comprising:

a vane having;

an airfoil portion; and

a vane stem extending from the airfoil portion;

a bushing into which the vane stem is inserted, a vane stem outer surface abutting a bushing inner surface; and

a vane retainer engaged with the bushing at a bushing outer surface, including;

a retainer body;

a threaded inner surface of the retainer body to engage complimentary threads of the bushing; and

a plurality of castellations disposed at a distal end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the bushing.

8. The vane assembly of claim 7, wherein the plurality of castellations are equally spaced about a vane retainer axis.

9. The vane assembly of claim 7, wherein a castellation height is substantially equal to a castellation width.

10. The vane assembly of claim 7, further comprising a chamfer disposed at a top surface of the castellation.

11. The vane assembly of claim 7, further comprising a fillet disposed at a castellation base.

12. The vane assembly of claim 7, wherein the plurality of castellations is eight equally sized castellations.

13. The vane assembly of claim 7, wherein the vane stem defines an axis of rotation of the vane.

14. A gas turbine engine, comprising:

a combustor; and

a plurality of vane assemblies in fluid communication with the combustor, each vane assembly including;

a vane having;

an airfoil portion; and

a vane stem extending from the airfoil portion;

a bushing into which the vane stem is inserted, a vane stem outer surface abutting a bushing inner surface; and

a vane retainer engaged with the bushing at a bushing outer surface, including;

a retainer body;

a threaded inner surface of the retainer body to engage complimentary threads of the bushing; and

a plurality of castellations disposed at a distal end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the bushing.

15. The gas turbine engine of claim 14, wherein the plurality of castellations are equally spaced about a vane retainer axis.

16. The gas turbine engine of claim 14, wherein a castellation height is substantially equal to a castellation width.

17. The gas turbine engine of claim 14, further comprising a chamfer disposed at a top surface of the castellation.

18. The gas turbine engine of claim 14, further comprising a fillet disposed at a castellation base.

19. The gas turbine engine of claim 14, wherein the plurality of castellations is eight equally sized castellations.