Turbine engine having variable pitch outlet guide vanes

Patent metadata

Field	Value
Publication number	US-2016333729-A1
Application number	US-201514708878-A
Country	US
Kind code	A1
Filing date	May 11, 2015
Priority date	May 11, 2015
Publication date	Nov 17, 2016
Grant date	—

Abstract

A gas turbine engine including a core engine and a fan configured in mechanical communication with the core engine is provided. The gas turbine engine also includes a plurality of outlet guide vanes positioned downstream from the fan along an axial direction defined by the gas turbine engine. The plurality of outlet guide vanes extend outwardly from an outer casing the core engine generally along the radial direction defined by the gas turbine engine. Each outlet guide vane defines a center of pressure and a pitch axis. The pitch axis of each outlet guide vane is positioned forward the center of pressure of each outlet guide vane such that in the event of a mechanical failure, the outlet guide vane defaults to a neutral position.

First claim

What is claimed is:

1 . A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a core engine including an outer casing; a fan configured in mechanical communication with the core engine; and a plurality of outlet guide vanes positioned downstream from the fan along the axial direction and extending outwardly from the outer casing of the core engine generally along the radial direction, each outlet guide vane defining a center of pressure and a pitch axis extending substantially parallel to the radial direction, the pitch axis of each outlet guide vane being positioned forward of the center of pressure of each outlet guide vane.

2 . The gas turbine engine of claim 1 , wherein the plurality of outlet guide vanes define a pitch angle, and wherein the plurality of outlet guide vanes are configured to rotate about their respective pitch axes to a pitch angle of at least about plus or minus ten degrees.

3 . The gas turbine engine of claim 2 , wherein the center of pressure of each outlet guide vane in the plurality of outlet guide vanes varies dependent on the respective pitch angle, and wherein the pitch axis of each outlet guide vane is positioned forward of the center of pressure of the respective outlet guide vane when the pitch angle of the respective outlet guide vane is between about minus ten degrees and about plus ten degrees.

4 . The gas turbine engine of claim 1 , wherein the plurality of outlet guide vanes define a pitch angle, and wherein the plurality of outlet guide vanes are configured to rotate about their respective pitch axes to a pitch angle of at least about plus or minus twenty degrees.

5 . The gas turbine engine of claim 4 , wherein the center of pressure of each outlet guide vane in the plurality of outlet guide vanes varies dependent on the respective pitch angle, and wherein the pitch axis of each outlet guide vane is positioned forward of the center of pressure of the respective outlet guide vane when the pitch angle of the respective outlet guide vane is between about minus twenty degrees and about plus twenty degrees.

6 . The gas turbine engine of claim 1 , further comprising
an attachment mechanism attaching one or more outlet guide vanes to the core engine and configured to allow for rotation of the one or more outlet guide vanes about a respective pitch axis.

7 . The gas turbine engine of claim 1 , further comprising
a pitch change mechanism configured to rotate one or more outlet guide vanes about their respective pitch axes.

8 . The gas turbine engine of claim 1 , wherein the fan is positioned forward of the core engine along the axial direction and in flow communication with the core engine.

9 . The gas turbine engine of claim 1 , wherein the pitch axis of each outlet guide vane is positioned at least a minimum amount forward of the center of pressure of the respective outlet guide vane through a pitch range of the respective outlet guide vane, and wherein the minimum amount is at least about four inches.

10 . The gas turbine engine of claim 1 , wherein the gas turbine engine is an unducted single fan gas turbine engine.

11 . The gas turbine engine of claim 1 , wherein the fan is a variable pitch fan.

12 . A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a core engine; a fan positioned in flow communication with the core engine; a plurality of outlet guide vanes positioned downstream from the fan along the axial direction, each outlet guide vane defining a center of pressure and a pitch change axis; and a pitch change mechanism configured to rotate one or more outlet guide vanes about their respective pitch axes within a pitch range, each respective pitch axis being positioned forward of a respective center of pressure of the respective outlet guide vane through the pitch range such that the outlet guide vane defaults to a neutral position during operation of the gas turbine engine.

13 . The gas turbine engine of claim 12 , wherein the pitch range is at least about twenty degrees.

14 . The gas turbine engine of claim 12 , wherein the pitch range is at least about forty degrees.

15 . The gas turbine engine of claim 12 , further comprising an attachment mechanism attaching one or more outlet guide vanes to the core engine and configured to allow for rotation of the one or more outlet guide vanes about their respective pitch axes.

16 . The gas turbine engine of claim 12 , wherein the fan is configured in mechanical communication with the core engine.

17 . The gas turbine engine of claim 12 , wherein the fan is positioned forward of the core engine along the axial direction.

18 . The gas turbine engine of claim 12 , wherein the pitch axis of each outlet guide vane is positioned at least a minimum amount forward of the center of pressure of the respective outlet guide vane through the pitch range of the respective outlet guide vane, and wherein the minimum amount is at least about four inches.

19 . The gas turbine engine of claim 12 , wherein the gas turbine engine is an unducted single fan gas turbine engine.

20 . The gas turbine engine of claim 12 , wherein the fan is a variable pitch fan.

Assignees

• Gen Electric

Inventors

• Miller Brandon Wayne
• Breeze-Stringfellow Andrew
• Zatorski Darek Tomasz

Classifications

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F02C7/042 Primary

  having variable geometry · 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

• B64C11/00

  Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft · CPC title

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title