Connector assembly for variable inlet guide vanes and method

Patent metadata

Field	Value
Publication number	US-9074489-B2
Application number	US-201213429839-A
Country	US
Kind code	B2
Filing date	Mar 26, 2012
Priority date	Mar 26, 2012
Publication date	Jul 7, 2015
Grant date	Jul 7, 2015

Abstract

A connector assembly for variable inlet guide vanes in a compressor case of a gas turbine engine comprises an annular case insert having a plurality of circumferentially distributed open-ended receptacles. The annular case insert is sized so as to be received inside a compressor case, with the plurality of circumferentially distributed open-ended receptacles being in register with holes in the compressor case. Bushings have an outer diameter sized to be received in a respective one of the receptacles of the annular case insert, and an inner diameter adapted to receive a connector portion of a vane. Sets of the bushing and the connector portion of a vane in one of the receptacles forming a rotational joint. A method for installing vanes in a compressor case is also provided.

First claim

What is claimed is:

1. A connector assembly for variable inlet guide vanes in a compressor case of a gas turbine engine comprising:
an annular case insert having a plurality of circumferentially distributed open-ended receptacles, the annular case insert being sized so as to be received inside a compressor case, with the plurality of circumferentially distributed open-ended receptacles being in register with holes in the compressor case; and
bushings having an outer diameter sized to be received in a respective one of the receptacles of the annular case insert, and an inner diameter adapted to receive a connector portion of a vane, sets of said bushing and said connector portion of a vane in one of said receptacles forming a rotational joint, each of said bushings having a first end being radially outward and a second end radially inward when received in the annular case insert, the first end being radially inward of an open end of the respective one of the receptacles of the annular case insert when therein.

2. The connector assembly according to claim 1 , wherein each said open-ended receptacle comprises a hollow neck projecting radially from a remainder of the receptacle, said necks accommodating one of the bushings.

3. The connector assembly according to claim 1 , wherein an inner surface of the annular case insert forms a continuous surface with an adjacent throat portion of the compressor case.

4. The connector assembly according to claim 1 , wherein each said bushing has a flange adapted to contact a radial edge of a respective vane.

5. The connector assembly according to claim 1 , wherein each said bushing is force fitted in a respective one of the receptacles.

6. The connector assembly according to claim 1 , wherein the rotational joint is formed between each said bushing and a respective one of the connector portions of the vanes.

7. A gas turbine engine comprising:
a compressor case with an inner cavity and a plurality of circumferentially distributed holes in the compressor case;
a plurality of vanes having a connector portion;

a connector assembly comprising:
an annular case insert having a plurality of circumferentially distributed open-ended receptacles, the annular case insert being sized so as to be received in the inner cavity of the compressor case, with the plurality of circumferentially distributed open-ended receptacles being in register with the holes in the compressor case; and
bushings having an outer diameter sized to be received in a respective one of the receptacles of the annular case insert, and an inner diameter receiving the connector portion of a corresponding one of the vanes, with sets of said bushing and said connector portion of a vane in one of said receptacles forming a rotational joint, each of said bushings and corresponding one of the vanes having a first end being radially outward and a second end radially inward when received in the annular case insert, the first ends being radially inward of an open end of the respective one of the receptacles of the annular case insert when therein.

8. The gas turbine engine according to claim 7 , further comprising an actuator interface for each said vane, the actuator interface being substantially outside of the compressor case and being operatively connected to the connector portion of a corresponding one of the vanes via one of the holes in the compressor case.

9. The gas turbine engine according to claim 8 , further comprising fasteners releasably securing each said actuator interface to the corresponding one of the vanes, a fastening end of each said fastener being substantially outside of the compressor case.

10. The gas turbine engine according to claim 7 , wherein each said open-ended receptacle comprises a hollow neck projecting radially from a remainder of the receptacle, each said neck accommodating one of the bushings.

11. The gas turbine engine according to claim 7 , wherein an inner surface of the annular case insert forms a continuous surface with an adjacent throat portion of the compressor case.

12. The gas turbine engine according to claim 7 , wherein each said bushing has a flange adapted to contact a radial edge of a respective one of the vanes.

13. The gas turbine engine according to claim 7 , wherein each said bushing is force fitted in a respective one of the receptacles.

14. The gas turbine engine according to claim 7 , wherein the rotational joint is formed between each said bushing and a respective one of the connector portions of the vanes.

15. A method for installing vanes in a compressor case comprising:
inserting bushings in receptacles of an annular case insert;
inserting a connector portion of vanes in at least some of the bushings to form a rotational joint between said vanes and the annular case insert;
positioning the annular case insert with the bushings and the vanes formed into the rotational joints inside a compressor case;
aligning the receptacles with holes in the compressor case; and
connecting an actuator interface to at least some of said connector portion of vanes through said holes from an exterior of the compressor case.

16. The method according to claim 15 , wherein inserting bushings in receptacles comprises force fitting the bushings in the receptacles of the annular case insert.

17. The method according to claim 15 , wherein positioning the annular case insert comprises moving the annular case insert along an axial direction of the compressor case.

18. The method according to claim 15 , wherein connecting the actuator interface to each said connector portion comprises using a fastener manipulated from an exterior of the compressor case.

Assignees

• Eleftheriou Andreas
• Menheere David Harold
• Marshall Andrew
• Pratt & Whitney Canada

Inventors

• Eleftheriou Andreas
• Menheere David Harold
• Marshall Andrew

Classifications

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F04D9/042

  and means for rendering its in operative · CPC title

• Y10T29/49245

  Vane type or other rotary, e.g., fan · CPC title