Apparatus to enable rotation of a compressor

Patent metadata

Field	Value
Publication number	US-10260369-B2
Application number	US-201614988253-A
Country	US
Kind code	B2
Filing date	Jan 5, 2016
Priority date	Jan 26, 2015
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

Apparatus to enable rotation of a compressor, the apparatus comprising: a guide for insertion through a fan of a gas turbine engine to the compressor, the guide including: a surface arranged to guide a drive assembly through an interior portion of the gas turbine engine to the compressor; and a first fastener arranged to fasten the guide to the gas turbine engine.

First claim

The invention claimed is:

1. Apparatus to enable rotation of a compressor, the apparatus comprising:
a guide for insertion through a fan of a gas turbine engine to the compressor, the guide including:
a surface configured to guide a drive head of a drive assembly through an interior portion of the gas turbine engine to the compressor, the drive head defining a housing for a belt and a plurality of teeth that extend outwardly from the belt; and
a first fastener configured to fasten the guide to the gas turbine engine.

2. Apparatus as claimed in claim 1 , wherein the guide is elongate and includes a first end and a second opposite end.

3. Apparatus as claimed in claim 2 , wherein the first end of the guide defines a channel configured to receive a first member of the drive assembly to at least partially fasten the drive assembly to the guide, the first member protruding from the drive head and including a first portion extending from the drive head and a second portion extending from the first portion, the second portion having a greater width than the first portion.

4. Apparatus as claimed in claim 2 , wherein the first fastener comprises a lever arranged to enable fastening and unfastening of the guide to the gas turbine engine, the lever being positioned at the second end of the guide.

5. Apparatus as claimed in claim 1 , wherein the guide defines a cavity arranged to receive a vane of the gas turbine engine therein.

6. Apparatus as claimed in claim 5 , wherein the cavity includes a notch to facilitate movement of the guide within the gas turbine engine and into position relative to the compressor.

7. Apparatus as claimed in claim 1 , wherein the guide comprises a second fastener arranged to fasten the drive assembly to the guide to prevent relative movement between the drive assembly and the guide.

8. Apparatus as claimed in claim 1 , wherein the guide further comprises at least one bushing for contacting the gas turbine engine during insertion of the guide to the gas turbine engine to prevent the guide from causing damage to the gas turbine engine.

9. Apparatus as claimed in claim 8 , further comprising at least one resilient member mounting the at least one bushing to the guide.

10. Apparatus as claimed in claim 1 , further comprising the drive assembly, the drive assembly configured for insertion into the gas turbine engine to rotate the compressor, the drive assembly comprising a first member to engage a channel in a first end of the guide.

11. Apparatus as claimed in claim 10 , wherein the drive assembly further comprises:
an elongate member; and
a second member protruding outwardly from the elongate member to contact the guide during insertion of the drive assembly into the gas turbine engine to prevent relative movement between the drive assembly and the guide, the contact between the second member and the guide being indicative that the drive assembly is to be rotated to align the drive assembly with blades of the compressor.

12. Apparatus as claimed in claim 11 , wherein the guide defines an open aperture though which the drive assembly is insertable, wherein the second member of the drive assembly contacts the guide at the open aperture prior to rotation, and the second member does not contact the guide at the open aperture subsequent to rotation.

13. A method to enable rotation of a compressor, the method comprising:
inserting a guide through a fan of a gas turbine engine to the compressor, the guide including:
a surface configured to guide a drive head of a drive assembly through an interior portion of the gas turbine engine to the compressor, the drive head defining a housing for a belt and a plurality of teeth that extend outwardly from the belt; and

operating a first fastener to fasten the guide to the gas turbine engine.

14. A method as claimed in claim 13 , further comprising: inserting a drive assembly into the gas turbine engine using the guide to rotate the compressor and at least partially fastening the drive assembly to the guide by moving a first member of the drive assembly into a channel defined within the guide, the first member protruding from the drive head and including a first portion extending from the drive head and a second portion extending from the first portion, the second portion having a greater width than the first portion.

15. A method as claimed in claim 14 , further comprising: rotating the drive assembly subsequent to a second member of the drive assembly contacting the guide at an open aperture of the guide.

16. A method as claimed in claim 14 , further comprising: operating a second fastener to fasten the drive assembly to the guide to prevent relative movement between the drive assembly and the guide.

17. A drive assembly for rotating a compressor of a gas turbine engine, the drive assembly comprising:
a drive head including:
an engagement mechanism configured to engage and rotate blades of the compressor; and
a first member arranged to engage a channel in a first end of a guide to at least partially fasten the drive assembly to the guide,

wherein the drive head defines a housing for a belt and a plurality of teeth that extend outwardly from the belt.

18. A drive assembly as claimed in claim 17 , further comprising a second member to contact the guide during insertion of the drive member into the gas turbine engine to prevent relative movement between the drive assembly and the guide, the contact between the second member and the guide being indicative that the drive assembly is to be rotated to align the drive assembly with the blades of the compressor.

Assignees

• Rolls Royce Plc

Inventors

• Unna Toby E

Classifications

• F01D25/36

  using electric motors · CPC title

• F01D21/003 Primary

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F16H35/18

  Turning devices for rotatable members, e.g. shafts · CPC title

• F01D5/005

  Repairing methods or devices · CPC title

• F01D25/285 Primary

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