Gas turbine in situ inflatable bladders for on-wing repair

Patent metadata

Field	Value
Publication number	US-9970326-B2
Application number	US-201615057236-A
Country	US
Kind code	B2
Filing date	Mar 1, 2016
Priority date	Mar 1, 2016
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

A method for forming an in situ temporary barrier within a gas turbine engine is provided. The method can include installing a bladder within the gas turbine engine, wherein the bladder defines a bladder body, and inflating the bladder with an inflating fluid such that the bladder body forms a circumferential seal within the gas turbine engine. The bladder body can be positioned between a row of stator vanes and an annular array of rotating blades to form a circumferential seal therebetween. A second bladder may be positioned circumferentially within the gas turbine engine.

First claim

What is claimed is:

1. A method for forming an in situ temporary barrier within a gas turbine engine, the method comprising:
installing a first bladder within the gas turbine engine, wherein the first bladder defines a first bladder body;
inflating the first bladder with an inflating fluid such that the first bladder body forms a circumferential seal within the gas turbine engine, the circumferential seal occurring in a gas turbine gas path at a first axial location and occupying an entire gas turbine gas path area at said first axial location; and
installing a second bladder positioned circumferentially within the gas turbine engine; wherein the second bladder is axially spaced apart from the first bladder.

2. The method as in claim 1 , wherein the first bladder body is positioned between a row of stator vanes and an annular array of rotating blades to form the circumferential seal therebetween, the first bladder body forming an isolated compartment of the gas turbine gas path with the second bladder,
wherein the circumferential seal prevents at least one of cleaning and repair materials from traveling to an upstream or downstream location within the gas turbine gas path from said isolated compartment.

3. The method as in claim 2 , further comprising;
performing at least one repair operation within the gas turbine gas path,
wherein the first bladder comprises a plastic material.

4. The method as in claim 3 , wherein the plastic material is a film.

5. The method as in claim 3 , wherein the plastic material is a fibrous web.

6. The method as in claim 2 , wherein the first bladder comprises a rubber material, and wherein the first bladder comprises an arcuate inner band and an arcuate outer band.

7. The method as in claim 6 , further comprising:
inflating the second bladder with an inflating fluid, wherein the second bladder defines a plurality of ports therein.

8. The method as in claim 1 , wherein the first bladder comprises a paper material.

9. The method as in claim 1 , wherein the inflating fluid comprises a liquid, a foam, or a gas.

10. The method as in claim 1 , wherein the inflating fluid comprises cleaning fluid.

11. The method as in claim 1 , wherein the inflating fluid comprises an organic material.

12. The method as in claim 11 , wherein the organic material comprises wood chips, wood pellets, nut shells, or a mixture thereof.

13. The method as in claim 1 , wherein the first bladder body defines exit ports configured to supply the inflating fluid into the gas turbine engine.

14. The method as in claim 13 , wherein the inflating fluid has a fluid flow rate into the first bladder body that is greater than a fluid outflow rate through the exit ports.

15. The method as in claim 7 , wherein the second bladder is connected to a collection pump drawing a vacuum through the second bladder and the plurality of ports.

16. The method as in claim 15 , wherein any fluid exiting the first bladder body is recovered through the ports of the second bladder.

17. The method as in claim 16 , wherein the second bladder is adjacent to a third bladder for structural stability during fluid recovery.

18. The method as in claim 17 , wherein the second bladder is attached to the third bladder to form an integrated double bladder that defines separate internal compartments.

19. A method for forming an in situ temporary barrier within a gas turbine engine, the method comprising:
inserting an uninflated first bladder through a port into a gas turbine gas path;
placing the uninflated first bladder at a first axial location within the gas turbine gas path;
inflating the first bladder to seal off an entire gas turbine gas path annulus at said first axial location;
performing one or more operations within the gas turbine gas path adjacent to the first axial location;
flushing the gas turbine gas path adjacent to the first axial location;
deflating the first bladder; and
removing the deflated first bladder from the gas turbine gas path.

20. The method of claim 19 , further comprising;
after the first bladder is inflated, inserting a second bladder into the gas turbine gas path at a second axial location, the second axial location being downstream from the first axial location; and
inflating the second bladder,
wherein the one or more operations comprises one or more cleaning operations.

Assignees

• Gen Electric

Inventors

• Roberts Herbert Chidsey
• Diwinsky David Scott

Classifications

• F05D2230/60

  Assembly methods · CPC title

• F01D25/002

  Cleaning of turbomachines · CPC title

• F01D25/285 Primary

  Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures · CPC title

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title