Turbomachine fan clutch

Patent metadata

Field	Value
Publication number	US-2016003143-A1
Application number	US-201414769887-A
Country	US
Kind code	A1
Filing date	Jan 31, 2014
Priority date	Feb 26, 2013
Publication date	Jan 7, 2016
Grant date	—

Abstract

A gas turbine engine assembly includes, among other things, a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed. Whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction. When the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction. The clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure. The clutch is removable on-wing.

First claim

We claim:

1 . A gas turbine engine assembly, comprising:
a clutch configured to move from a first position to a second position in response to rotation of a gas turbine engine fan at a speed greater than a threshold speed, wherein, whether the clutch is in the first position or the second position, the clutch permits rotation of the gas turbine engine fan in a first direction, and when the clutch is in the first position, the clutch limits rotation of the gas turbine engine fan only in an opposite, second direction, wherein the clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure, whereby the clutch is removable on-wing.

2 . The gas turbine engine assembly of claim 1 , wherein the aft engine cover structure includes an engine exhaust cone.

3 . The gas turbine engine assembly of claim 2 , wherein the clutch is disposed within an aft bearing compartment and the aft engine cover structure further includes an aft bearing compartment cover plate, disposed axially inward of the exhaust cone.

4 . The gas turbine engine assembly of claim 1 , wherein the clutch is positioned within a gas turbine engine such that the clutch can be moved from an installed position within the gas turbine engine to an uninstalled position without removing any blades from the gas turbine engine.

5 . The gas turbine engine assembly of claim 1 , wherein the clutch is coupled to a low speed spool of a gas turbine engine.

6 . The gas turbine engine assembly of claim 5 , wherein the low speed spool is rotatably coupled to the gas turbine engine fan via a geared architecture.

7 . The gas turbine engine assembly of claim 6 , wherein the clutch is positioned within a gas turbine engine aft the geared architecture relative to a direction of flow through the gas turbine engine.

8 . The gas turbine engine assembly of claim 1 , wherein the threshold speed is less than an idling speed.

9 . The gas turbine engine assembly of claim 1 , wherein the threshold speed is a threshold rotational speed of the fan.

10 . The gas turbine engine assembly of claim 1 , wherein the clutch is an entirely mechanical clutch.

11 . A gas turbine engine assembly, comprising:
a fan; a spool configured to rotatably drive the fan through a geared architecture; and a clutch coupled to the spool, the clutch moveable between a first position that permits windmilling rotations of the fan, and a second position that limits windmilling rotations of the fan in one direction, wherein the clutch is a mechanical clutch, wherein the clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure, wherein the clutch is removeable on-wing.

12 . The gas turbine engine assembly of claim 11 , wherein the aft engine cover structure includes an engine exhaust cone.

13 . The gas turbine engine assembly of claim 12 , wherein the clutch is disposed within an aft bearing compartment and the aft engine cover structure further includes an aft bearing compartment cover plate, disposed axially inward of the exhaust cone.

14 . The gas turbine engine assembly of claim 11 , wherein the clutch is positioned aft the geared architecture relative to a direction of flow through the gas turbine engine.

15 . The gas turbine engine assembly of claim 11 , wherein the spool is a low speed spool.

16 . A method of controlling rotation of a gas turbine engine fan, including:
engaging a clutch to prevent rotation of a gas turbine engine fan in a first direction when a rotational speed of the gas turbine engine fan is below a threshold speed, the clutch being removable on-wing; and disengaging the clutch when the rotational speed of the gas turbine engine fan meets or exceeds the threshold speed, wherein the clutch is disposed within a compartment that is accessible and removable via removal of an aft engine cover structure, whereby the clutch is removable on-wing.

17 . The method of claim 16 , wherein the aft engine cover structure includes an engine exhaust cone.

18 . The method of claim 17 , wherein the clutch is disposed within an aft bearing compartment and the aft engine cover structure further includes an aft bearing compartment cover plate, disposed axially inward of the exhaust cone.

19 . The method of claim 16 , including positioning the clutch within a gas turbine engine such that the clutch can be moved from an installed position within the gas turbine engine to an uninstalled position without removing any blades from the gas turbine engine.

20 . The method of claim 16 , including coupling the clutch to a spool of a gas turbine engine that rotatably drives the gas turbine engine fan through a geared architecture.

Assignees

• United Technologies Corp

Inventors

• Sheridan William G
• Mccune Michael E

Classifications

• F16D43/06

  with centrifugal masses actuating axially a movable pressure ring or the like · CPC title

• F05D2260/4023

  through a friction clutch · CPC title

• F16D41/088

  the intermediate members being of only one size and wedging by a movement not having an axial component, between inner and outer races, one of which is cylindrical · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F02C3/107 Primary

  with two or more rotors connected by power transmission · CPC title