Method of making a turbine wheel axial retention device

Patent metadata

Field	Value
Publication number	US-10072524-B2
Application number	US-201514618689-A
Country	US
Kind code	B2
Filing date	Feb 10, 2015
Priority date	Feb 10, 2015
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A turbine retention device is made by forming a bullet having a cylindrical geometry, forming a wing, coupling the wing to the bullet with a proximal portion of the wing along an axial length of the bullet, and coupling a mounting bracket to a distal end of the wing.

First claim

What is claimed is:

1. A method of making a turbine retention device, comprising:
forming a bullet having a cylindrical geometry; wherein the bullet comprises a solid cap to prevent flow through the bullet;
forming a solid wing;
coupling the wing to the bullet with a proximal portion of the wing along an axial length of the bullet at a tangential angle to the bullet wherein the tangential angle is such that the wing extends from a surface of the bullet and the wing lies on a non-radial plane with respect to the cylindrical geometry of the bullet; and
coupling a mounting bracket to a distal end of the wing.

2. The method of claim 1 , further comprising boring the bullet.

3. The method of claim 1 , wherein the forming the bullet having the cylindrical geometry further comprises forming the bullet additively.

4. The method of claim 1 , wherein the forming the wing further comprises forming the wing additively.

5. The method of claim 1 , wherein the forming the wing further comprises machining a wrought metal.

6. The method of claim 5 , wherein the forming the bullet having the cylindrical geometry further comprises machining the wrought metal.

7. The method of claim 1 , further comprising spacing a plurality of wings including the wing equally around the bullet.

8. The method of claim 7 , further comprising welding the wings to a plurality of mounting brackets including the mounting bracket.

9. The method of claim 7 , further comprising welding the wings to the bullet.

10. The method of claim 7 , wherein the coupling the wings to the bullet further comprises configuring the wing such that an angle between a plane of the wing and an axis of rotation of a turbine is greater than zero, wherein the axis of rotation of the turbine is in line with a centerline of the bullet.

11. A method of making a turbine retention device, comprising:
forming a bullet with solid wings extending away from a surface of a cylindrical body of the bullet at a substantially tangential angle wherein the tangential angle is such that the wing lies on a non-radial plane with respect to the cylindrical body of the bullet; wherein the bullet comprises a solid cap to prevent flow through the bullet; and
coupling mounting brackets to the wings.

12. The method of claim 11 , further comprising forming one of the bullet or the wings additively.

13. The method of claim 11 , further comprising configuring the wing such that an angle between a plane of the wing and an axis of rotation of a turbine is greater than zero, wherein the axis of rotation of the turbine is in line with a centerline of the bullet.

14. The method of claim 11 , wherein the forming the bullet with the wings further comprises forming the bullet integrally with the wings.

15. The method of claim 11 , further comprising forming the wings by machining a wrought metal.

16. The method of claim 15 , further comprising forming the bullet by machining the wrought metal.

17. A turbine retention device, comprising:
a bullet having a cylindrical body; wherein the bullet comprises a solid cap to prevent flow through the bullet;
solid wings disposed circumferentially about the bullet at a tangential angle to the bullet wherein the tangential angle is such that the wings extend from a surface of the bullet and the wings lies on a non-radial plane with respect to the cylindrical body of the bullet; and
mounting brackets coupled to the wings.

18. The turbine retention device of claim 17 , wherein the wings are configured such that an angle between a plane of the wings and an axis of rotation of a turbine is greater than zero, wherein the axis of rotation of the turbine is in line with a centerline of the bullet.

19. The turbine retention device of claim 17 , wherein the bullet, the wings, and the mounting brackets are made from one or more nickel superalloy.

20. The turbine retention device of claim 17 , wherein the bullet has a hollow and cylindrical geometry.

Assignees

• United Technologies Corp

Inventors

• Light Stacey H
• Hagshenas Behzad

Classifications

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F05D2300/175

  Superalloys · CPC title

• F05D2240/24

  for turbines · CPC title

• F01D25/162

  Bearing supports · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic