Gas turbine engine with selective flow path

Patent metadata

Field	Value
Publication number	US-10107500-B2
Application number	US-201514713187-A
Country	US
Kind code	B2
Filing date	May 15, 2015
Priority date	May 22, 2014
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A gas turbine engine includes a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. There is a duct located downstream of the gas generator. The duct is configured to move between a first position and a second position. A fan drive turbine is positioned downstream of a path of the products of combustion and passes over at least one gas generator turbine rotor when the duct is in the first position. The fan drive turbine is for driving a shaft and the shaft is for engaging gears to drive at least two fan rotors. An augmentor section is positioned downstream of a path of products of combustion and passes over at least one gas generator turbine rotor when the duct is in second position.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a gas generator with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section;
a duct located downstream of said gas generator, said duct including an annular outlet configured to move between a first position and a second position;
wherein in the first position, the annular outlet connects the gas generator to an inlet of a fan drive turbine positioned downstream of a path of products of combustion having passed over a surface of said at least one gas generator turbine rotor and said duct, said fan drive turbine for driving a shaft and said shaft for engaging gears to drive at least two fan rotors, wherein an axis of rotation of said fan drive turbine is transverse to a gas generator axis of rotation; and
wherein in the second position, the annular outlet connects the gas generator to an inlet of an augmentor section positioned downstream of said path of products of combustion having passed over said at least one gas generator turbine rotor and said duct.

2. The gas turbine engine as set forth in claim 1 , wherein said duct is a three bearing swivel duct.

3. The gas turbine engine as set forth in claim 1 , wherein said augmentor section includes at least one spray bar for injecting fuel into an exhaust stream.

4. The gas turbine engine as set forth in claim 3 , wherein said augmentor section includes an igniter for igniting fuel injected into said exhaust stream.

5. The gas turbine engine as set forth in claim 1 , wherein said at least two fan rotors include a variable inlet opening.

6. The gas turbine engine as set forth in claim 5 , wherein said at least two fan rotors include a variable exhaust opening.

7. The gas turbine engine as set forth in claim 1 , wherein said duct includes a first exit flow path when in said first position and a second exit flow path when in said second position, said first exit flow path being generally perpendicular to said second exit flow path.

8. The gas turbine engine as set forth in claim 1 , wherein said gas generator includes at least two compressor rotors and at least two gas generator turbine rotors, with said fan drive turbine being positioned to be downstream of said path of said products of combustion having passed over each of said at least two gas generator turbine rotors.

9. The gas turbine engine as set forth in claim 1 , wherein said axis of rotation of said gas generator is generally perpendicular to an axis of rotation of said shaft.

10. The gas turbine engine as set forth in claim 1 , wherein said axis of rotation of said gas generator is generally coaxial with an axis of rotation of said at least two fan rotors.

11. The gas turbine engine of claim 1 , wherein said fan drive turbine and said shaft are coaxial.

12. The gas turbine engine of claim 1 , wherein said axis of rotation of said fan drive turbine is generally perpendicular to said at least two fan rotors.

Assignees

• United Technologies Corp

Inventors

• O'Flarity Steven M

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2240/40

  Use of a multiplicity of similar components · CPC title

• F02K3/04 Primary

  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

• F02K1/80

  Couplings or connections · CPC title

• F02K3/077

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title