Integrated flex support and front center body

Patent metadata

Field	Value
Publication number	US-9945259-B2
Application number	US-201414765680-A
Country	US
Kind code	B2
Filing date	Mar 14, 2014
Priority date	Mar 15, 2013
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A gas turbine engine is provided. The gas turbine engine may include a geared architecture, a central body support and a bearing package. The geared architecture may interconnect a spool and a fan rotatable about an axis. The central body support may provide an annular wall for a core flow path and an integral flex support inwardly extending therefrom. The integral flex support may couple the geared architecture to the central body support. The bearing package may include a bearing support removably coupled to the integral flex support.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a geared architecture interconnecting a spool and a fan rotatable about an axis;
a central body support providing an annular wall for a core flow path and an integral flex support inwardly extending therefrom, the integral flex support coupling the geared architecture to the central body support and the integral flex support is disposed substantially aft of the geared architecture so as to provide sufficient axial clearance to an oil manifold associated with the geared architecture; and
a bearing package having a bearing support removably coupled to the integral flex support.

2. The gas turbine engine of claim 1 , wherein the integral flex support includes at least one flex member configured to at least partially suppress vibrations within the gas turbine engine.

3. The gas turbine engine of claim 2 , wherein the at least one flex member is geometrically structured to at least partially suppress vibrations within the gas turbine engine.

4. The gas turbine engine of claim 2 , wherein the at least one flex member is configured to at least partially suppress vibrations between the central body support and at least the geared architecture.

5. The gas turbine engine of claim 1 , wherein at least the integral flex support and the annular wall are formed of a unitary body.

6. The gas turbine engine of claim 1 , wherein the integral flex support is configured to form an oil seal with the bearing support, the oil seal being configured to lubricate lower bearings associated with one or more exit guide vanes associated with the gas turbine engine.

7. The gas turbine engine of claim 1 , wherein the integral flex support further includes a retaining member configured to axially retain a fan assembly associated with the gas turbine engine.

8. A central body support for a gas turbine engine, comprising:
an outer annular wall;
an inner annular wall defining a core flow path with the outer annular wall;
a plurality of vanes circumferentially disposed between the outer and inner annular walls; and
an integral flex support inwardly extending from the inner annular wall, the integral flex support including at least one flex member configured to at least partially suppress vibrations within the gas turbine engine and the integral flex support is configured to removably couple to a bearing support associated with a bearing package of the gas turbine engine, the integral flex support forming an oil seal with the bearing support for lubricating lower bearings associated with one or more exit guide vanes.

9. The central body support of claim 8 , wherein the at least one flex member is geometrically structured to at least partially suppress vibrations within the gas turbine engine.

10. The central body support of claim 8 , wherein the integral flex support is configured to couple to a geared architecture of the gas turbine engine.

11. The central body support of claim 10 , wherein the at least one flex member is configured to at least partially suppress vibrations between the inner annular wall and at least the geared architecture.

12. The central body support of claim 10 , wherein the integral flex support is disposed substantially aft of the geared architecture so as to provide sufficient axial clearance to an oil manifold associated with the geared architecture.

13. The central body support of claim 8 , wherein the integral flex support further includes a retaining member configured to axially retain a fan assembly associated with the gas turbine engine.

14. The central body support of claim 8 , wherein at least the integral flex support and the inner annular wall are formed of a unitary body.

15. A method of manufacturing a front architecture of a gas turbine engine, comprising the steps of:
casting a central body support having an annular wall for a core flow path and an integral stock piece inwardly extending therefrom;
machining the integral stock piece to form an integral flex support having at least one flex member, the integral flex support being machined to be disposed substantially aft of a geared architecture so as to provide sufficient axial clearance to an oil manifold associated with the geared architecture; and
removably coupling a fore section of the integral flex support to the geared architecture and an aft section of the integral flex support to a bearing support.

16. The method of claim 15 , wherein the at least one flex member is machined with at least one geometric structure configured to at least partially suppress vibrations between the central body support and at least the geared architecture.

17. The method of claim 15 , wherein the integral flex support and the bearing support are removably coupled to form an oil seal about lower bearings associated with one or more exit guide vanes.

Assignees

• United Technologies Corp

Inventors

• Cigal Brian P
• Davis Todd A

Classifications

• F02C7/20

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F05D2230/10

  by removing material · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title