Removable nosecone for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9759129-B2
Application number	US-201314141027-A
Country	US
Kind code	B2
Filing date	Dec 26, 2013
Priority date	Dec 28, 2012
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The nosecone includes at least a first tool hole extending through the nosecone. The first tool hole is structurally reinforced.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a nosecone assembly attached to the gas turbine engine, the nosecone assembly comprising:
a support structure;
a nosecone attached to the support structure, the nosecone comprising:
a tip end;
an aft end opposite the tip end; and
at least a first tool hole extending through the nosecone, wherein the first tool hole is positioned on or nearer the tip end than the aft end; and

a first reinforcing structure joined to the nosecone at the first tool hole.

2. The gas turbine engine of claim 1 , wherein the first reinforcing structure is a first grommet attached to the nosecone at the first tool hole.

3. The gas turbine engine of claim 1 , wherein the first reinforcing structure is a hard anodized coating applied to the nosecone at the first tool hole.

4. The gas turbine engine of claim 1 , wherein the support structure comprises a support ring positioned radially outward of and in friction contact with an aft end of the nosecone.

5. The gas turbine engine of claim 1 , wherein the gas turbine engine is an industrial gas turbine engine further comprising:
a first compressor section attached to a first turbine section via a first shaft;
a second compressor section attached to a second turbine section via a second shaft; and
a power turbine section positioned downstream of the first and second turbine sections.

6. The gas turbine engine of claim 1 , wherein the support structure is connected to an inner shroud of an inlet guide vane.

7. The gas turbine engine of claim 1 , wherein the nosecone further includes a second tool hole extending through the nosecone and a second reinforcing structure joined to the nosecone at the second tool hole.

8. The gas turbine engine of claim 7 , and further comprising:
a first removal tool extending through the first tool hole; and
a second removal tool extending through the second tool hole.

9. The gas turbine engine of claim 7 , wherein the first tool hole is positioned substantially circumferentially opposite the second tool hole.

10. The gas turbine engine of claim 1 , wherein the nosecone is substantially a unitary piece extending along a curved profile from the nosecone tip to the nosecone aft end.

11. A method comprising:
inserting a first removal tool in a first tool hole in a nosecone; and
applying a pulling force to the nosecone via the first removal tool so as to pull the nosecone away from a support structure of a gas turbine engine, wherein the support structure is a support ring positioned radially outward of and in friction contact with an aft end of the nosecone while the nosecone is pulled away from the support structure.

12. The method of claim 11 , wherein the nosecone and the support structure are at a substantially same temperature while the nosecone is pulled away from the support structure.

13. The method of claim 11 , wherein the nosecone and the support structure are at a substantially ambient temperature while the nosecone is pulled away from the support structure.

14. The method of claim 11 , wherein the nosecone includes at least a second tool hole and wherein the first removal tool is inserted into both the first and second tool holes before applying the pulling force to the nosecone.

15. The method of claim 11 , and further comprising:
inserting a second removal tool in a second tool hole in the nosecone; and
applying a pulling force to the nosecone via the second removal tool along with the first removal tool so as to pull the nosecone away from the support structure of the gas turbine engine.

16. The method of claim 11 , and further comprising:
performing maintenance on the gas turbine engine after removing the nosecone.

17. The method of claim 11 , and further comprising:
inserting the nosecone into the support structure after removing the nosecone; and
attaching the nosecone to the support structure via fasteners.

18. A nosecone assembly for a gas turbine engine, the nosecone assembly comprising:
a nosecone having at least a first tool hole extending through the nosecone;
a reinforcing structure joined to the nosecone at the first tool hole; and
a support structure comprising:
a support ring positioned radially outward of and in friction contact with an aft end of the nosecone.

19. The nosecone assembly of claim 18 , wherein the reinforcing structure is a first grommet attached to the nosecone at the first tool hole.

20. The nosecone assembly of claim 18 , wherein the reinforcing structure is a hard anodized coating applied to the nosecone at the first tool hole.

Assignees

• United Technologies Corp

Inventors

• Lindsey Anthony T
• Jayasingh Arun Kumar
• Walker Herbert L

Classifications

• F05D2230/70

  Disassembly methods · CPC title

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2230/60

  Assembly methods · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic