Method of mounting a turbine wheel axial retention device

Patent metadata

Field	Value
Publication number	US-10018057-B2
Application number	US-201514618662-A
Country	US
Kind code	B2
Filing date	Feb 10, 2015
Priority date	Feb 10, 2015
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

A technique for mounting a turbine retention device is provided. The technique comprises forming openings in a diffuser, aligning a mounting bracket with the openings, and installing fasteners through the openings and the mounting bracket. A turbine retention device mounted to a diffuser may is also provided. The turbine retention device may comprise a bullet, wings coupled to the bullet, mounting brackets coupled to the wings, and fasteners disposed through the mounting brackets and openings formed in the diffuser.

First claim

What is claimed is:

1. A method of mounting a turbine retention device, comprising:
aligning a mounting bracket with an opening in a cylindrical diffuser, the mounting bracket attached to a monolithic wing;
configuring at least one of the mounting bracket or the monolithic wing such that a proximal portion of the wing lies along an axial length of a bullet at a tangential angle to the bullet, wherein the tangential angle is such that the monolithic wing extends from a surface of the bullet and the monolithic wing lies on a non-radial plane with respect to a cylindrical geometry of the bullet; wherein the bullet comprises a solid cap to prevent flow through the bullet; and
installing a fastener through the opening and the mounting bracket.

2. The method of claim 1 , wherein the fastener comprises a bolt.

3. The method of claim 1 , wherein the fastener comprises a rivet.

4. The method of claim 1 , further comprising placing a spacer between the fastener and the cylindrical diffuser.

5. The method of claim 1 , wherein the opening is formed in the cylindrical diffuser while the cylindrical diffuser is installed on an aircraft.

6. The method of claim 1 , further comprising forming a plurality of openings equally spaced about the cylindrical diffuser.

7. The method of claim 6 , wherein forming the plurality of openings further comprises:
placing a drill fixture on the cylindrical diffuser; and
drilling the plurality of openings through the drill fixture.

8. The method of claim 7 , further comprising clocking the drill fixture to align the drill fixture.

9. A method of installing a turbine retention device in a radial turbine engine, comprising:
aligning a mounting bracket of the turbine retention device with an opening formed in a diffuser, the mounting bracket coupled to a monolithic wing coupled to a bullet such that a proximal portion of the monolithic wing lies along an axial length of the bullet at a tangential angle to the bullet, wherein the tangential angle is such that the monolithic wing extends from a surface of the bullet and the monolithic wing lies on a non-radial plane with respect to a cylindrical geometry of the bullet; wherein the bullet comprises a solid cap to prevent flow through the bullet and;
installing a fastener through the opening and the mounting bracket.

10. The method of claim 9 , wherein the fastener comprises a bolt.

11. The method of claim 9 , wherein the fastener comprises a rivet.

12. The method of claim 9 , further comprising placing a spacer between the fastener and the diffuser.

13. The method of claim 9 , further comprising forming the opening while the radial turbine engine is installed on an aircraft.

14. The method of claim 9 , further comprising forming sets of openings equally spaced about the diffuser.

15. The method of claim 14 , wherein the forming the sets of openings further comprises:
placing a drill fixture on the diffuser; and
drilling the sets of openings through the drill fixture.

16. The method of claim 15 , further comprising clocking the drill fixture to align the drill fixture.

17. A turbine retention device mounted to a diffuser, comprising:
a bullet;
monolithic wings coupled to the bullet such that a proximal portion of the monolithic wings lies along an axial length of the bullet at a tangential angle to the bullet, wherein the tangential angle is such that the monolithic wing extends from a surface of the bullet and the monolithic wings lie on a non-radial plane with respect to a cylindrical geometry of the bullet; wherein the bullet comprises a solid cap to prevent flow through the bullet;
mounting brackets coupled to the monolithic wings; and
fasteners disposed through the mounting brackets and openings formed in the diffuser.

18. The turbine retention device of claim 17 , wherein the fasteners comprise at least one of rivets or bolts.

19. The turbine retention device of claim 17 , wherein the openings formed in the diffuser are formed in pairs.

Assignees

• United Technologies Corp

Inventors

• Light Stacey H
• Hagshenas Behzad

Classifications

• F01D5/30 Primary

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F02K1/04

  Mounting of an exhaust cone in the jet pipe · CPC title

• F01D25/162

  Bearing supports · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title