Tool for abrasive flow machining of airfoil clusters

Patent metadata

Field	Value
Publication number	US-9550267-B2
Application number	US-201314765723-A
Country	US
Kind code	B2
Filing date	Dec 19, 2013
Priority date	Mar 15, 2013
Publication date	Jan 24, 2017
Grant date	Jan 24, 2017

Abstract

A tool for use during the abrasive flow polishing of an airfoil cluster in an abrasive flow machine is described. The tool may comprise a body and prongs extending from the body. Each prong of the tool may be configured to insert between an adjacent pair of airfoils of the airfoil cluster to create at least one channel therebetween. The channel may allow the flow of an abrasive media therethrough.

First claim

What is claimed is:

1. A tool for the abrasive flow machining of an airfoil cluster, comprising:
a body; and
prongs extending from the body, each prong being configured to insert between an adjacent pair of airfoils of the airfoil cluster to create at least one channel therebetween, the channel allowing the flow of an abrasive media therethrough.

2. The tool of claim 1 , wherein the at least one channel includes a first capillary channel and a second capillary channel, the first capillary channel being formed between the prong and a convex surface of a first airfoil of the adjacent pair of airfoils, the second capillary channel being formed between the prong and a concave surface of a second airfoil of the adjacent pair of airfoils.

3. The tool of claim 2 , wherein the at least one channel further includes a platform channel formed between a tip of the prong and a platform of the airfoil cluster, the platform being located on a supporting rail of the airfoil cluster between the adjacent pair of airfoils.

4. The tool of claim 3 , wherein a channel width of the platform channel is greater than a channel width of each of the first capillary channel and the second capillary channel.

5. The tool of claim 4 , wherein a velocity of the abrasive media is greater in the platform channel than in each of the first capillary channel and the second capillary channel.

6. The tool of claim 4 , wherein each prong has a convex surface and a concave surface.

7. The tool of claim 6 , wherein the convex surface of the prong has a curvature identical to the curvature of the convex surface of the first airfoil, and wherein the concave surface of the prong has a curvature identical to the curvature of the concave surface of the second airfoil.

8. The tool of claim 7 , wherein the first capillary channel is formed between the concave surface of the prong and the convex surface of the first airfoil, and wherein the second capillary channel is formed between the convex surface of the prong and the concave surface of the second airfoil.

9. The tool of claim 8 , wherein the abrasive media follows a curved pathway when flowing through the first capillary channel and the second capillary channel, the curved pathway having a curvature matching the curvatures of the first airfoil and the second airfoil.

10. The tool of claim 8 , wherein the channel width of the platform channel is at least two times greater than the channel width of each of the first capillary channel and the second capillary channel.

11. The tool of claim 3 , wherein a channel width of the platform channel is about equal to a channel width of each of the first capillary channel and the second capillary channel.

12. The tool of claim 3 , wherein a channel width of the platform channel is thinner than a channel width of each of the first capillary channel and the second capillary channel.

13. An abrasive flow machine for polishing the surfaces of an airfoil cluster, comprising:
a housing;
an abrasive media contained in the housing;
a driver operatively associated with the abrasive media to cause the abrasive media to flow over the surfaces of the airfoil cluster; and
a tool configured to operatively associate with the airfoil cluster, the tool having a body and prongs extending from the body, each prong being configured to insert between an adjacent pair of airfoils of the airfoil cluster to create at least one channel therebetween, the channel allowing the flow of the abrasive media therethrough.

14. The abrasive flow machine of claim 13 , wherein the at least one channel includes a first capillary channel and a second capillary channel, the first capillary channel being formed between the prong and a convex surface of a first airfoil of the adjacent pair of airfoils, the second capillary channel being formed between the prong and a concave surface of a second airfoil of the adjacent pair of airfoils.

15. The abrasive flow machine of claim 14 , wherein the at least one channel further includes a platform channel formed between a tip of the prong and a platform of the airfoil cluster, the platform being located on a supporting rail of the airfoil cluster between the adjacent pair of airfoils.

16. The abrasive flow machine of claim 15 , wherein a channel width of the platform channel is greater than a channel width of each of the first capillary channel and the second capillary channel.

17. The abrasive flow machine of claim 15 , wherein each prong has a convex surface and a concave surface.

18. The abrasive flow machine of claim 17 , wherein the first capillary channel is formed between the concave surface of the prong and the convex surface of the first airfoil and the second capillary channel is formed between the convex surface of the prong and the concave surface of the second airfoil.

19. A method for using a tool for the abrasive flow machining of an airfoil cluster, comprising:
assembling the airfoil cluster with the tool by inserting a prong of the tool between an adjacent pair of airfoils of the airfoil cluster to create at least one channel therebetween, the channel allowing the flow of an abrasive media therethrough; and
initiating the flow of the abrasive media through the at least one channel, the curvature and widths of the channel assisting to control the direction and velocity of the flow of the abrasive media over surfaces of the airfoil cluster.

20. The method of claim 19 , wherein the at least one channel includes a first capillary channel, a second capillary channel, and a platform channel, the first capillary channel being formed between the prong and a surface of a first airfoil of the adjacent pair of airfoils, the second capillary channel being formed between the prong and a surface of a second airfoil of the adjacent pair of airfoils, the platform channel being formed between a tip of the prong and a platform of the airfoil cluster, the platform being located on a supporting rail of the airfoil cluster between the adjacent pair of airfoils.

Assignees

• United Technologies Corp

Inventors

• Beckman Micah
• Masiukiewicz David Krzysztof

Classifications

• B24B19/14

  for grinding turbine blades, propeller blades or the like (using grinding belts B24B21/16) · CPC title

• B24B31/116 Primary

  using plastically deformable grinding compound, moved relatively to the workpiece under the influence of pressure · CPC title