Method and fixture for airfoil array assembly

Patent metadata

Field	Value
Publication number	US-9731388-B2
Application number	US-201514955337-A
Country	US
Kind code	B2
Filing date	Dec 1, 2015
Priority date	Sep 26, 2012
Publication date	Aug 15, 2017
Grant date	Aug 15, 2017

Abstract

An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

First claim

The invention claimed is:

1. A method of assembling a turbomachine airfoil array comprising the steps of:
securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed;
mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area;
holding a replacement airfoil using the positioning saddle;
applying a curable material at an interface between the replacement airfoil and the inner and outer fairing; and
curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing,
wherein the positioning saddle holds the replacement airfoil by defining a first plane with at least two contact points between the positioning saddle and the replacement airfoil.

2. The method of claim 1 , wherein the replacement airfoil is a stator vane.

3. The method of claim 1 , further comprising defining a second plane with at least two contact points on the positioning saddle, and defining at least a portion of a third plane with at least one contact point on the saddle.

4. The method of claim 3 , wherein the positioning saddle includes a first portion and a separate, second portion, the first portion having the contact points defining the first and second planes, and the second portion having the at least one contact point defining the third plane.

5. The method of claim 3 , wherein the positioning saddle is selected from a group of positioning saddles, at least some of the positioning saddles within the group having contact points defining different first planes and different second planes.

6. The method of claim 1 , wherein the fixture does not include positioning saddles associated with the at least one existing airfoil.

7. The method of claim 1 , wherein the at least one existing airfoil is held within the fixture during curing of the curable material.

8. The method of claim 1 , wherein the positioning saddle is configured to be selectively positioned at one of a plurality of circumferential positions.

9. The method of claim 1 , wherein the fixture provides unobstructed areas that accommodate the existing airfoils when the partial airfoil array is secured within the fixture, the unobstructed areas lacking contact points defining planes for aligning airfoil vanes.

10. The method of claim 1 , wherein the mounting is before the securing.

11. A method of assembling a turbomachine airfoil assembly, comprising the steps of:
securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner fairing and an outer fairing, and an open area where at least one existing airfoil has been removed;
holding a replacement airfoil by defining a first plane with at least two contact points;
applying a curable material at an interface between the replacement airfoil and the inner fairing and the outer fairing; and
curing the curable material while maintaining a relative position between the replacement airfoil and the inner fairing and the outer fairing.

12. The method of claim 11 , wherein the holding comprises holding the replacement airfoil using a positioning saddle.

13. The method of claim 12 , further comprising positioning the replacement airfoil by defining the first plane with the at least two contact points on the positioning saddle, defining a second plane with at least two contact points on the positioning saddle, and defining at least a portion of a third plane with at least one contact point on the saddle, wherein the positioning saddle includes a first portion and a separate, second portion, the first portion having the contact points defining the first and second planes, and the second portion having the at least one contact point defining the third plane.

14. The method of claim 12 , wherein the positioning saddle is selected from a group of positioning saddles, at least some of the positioning saddles within the group having contact points defining different first planes and different second planes.

15. The method of claim 11 , wherein the replacement airfoil is a stator vane.

16. The method of claim 11 , wherein the at least one existing airfoil is held within the fixture during curing of the curable material.

17. The method of claim 12 , wherein the positioning saddle is configured to be selectively positioned at one of a plurality of circumferential positions.

18. The method of claim 11 , wherein the fixture provides unobstructed areas that accommodate the existing airfoils when the partial airfoil array is secured within the fixture, the unobstructed areas lacking contact points defining planes for aligning airfoil vanes.

19. The method of claim 11 , wherein the mounting is before the securing.

Assignees

• United Technologies Corp

Inventors

• Feigleson Steven J
• Tremblay Dennis R
• Mcmahon Michael E
• Johnson Nathan C

Classifications

• B23P15/04 Primary

  turbine or like blades from several pieces · CPC title

• F05D2230/68

  using auxiliary equipment for lifting or holding · CPC title

• Y10T29/53961

  with work-holder for assembly · CPC title

• B23P15/06

  piston rings from one piece · CPC title

• F05D2230/70

  Disassembly methods · CPC title