Gas turbine engine with distributed fans with drive control

Patent metadata

Field	Value
Publication number	US-9909495-B2
Application number	US-201514600487-A
Country	US
Kind code	B2
Filing date	Jan 20, 2015
Priority date	Feb 7, 2014
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a plurality of fan rotors;
a gas generator comprising:
at least one compressor rotor;
at least one gas generator turbine rotor;
a combustion section; and
a fan drive turbine downstream of the at least one gas generator turbine rotor, a shaft configured to be driven by said fan drive turbine, said shaft engaging gears to drive the plurality of fan rotors; and

a system for controlling an amount of power supplied to said plurality of fan rotors;
said system includes a plurality of clutches, a respective clutch of the plurality of clutches being between said shaft and each of said plurality of fan rotors that is selectively opened;
each clutch of the plurality of clutches being configured to be opened to reduce power consumption by the gas turbine engine, said shaft also configured to drive an electric generator, each clutch of the plurality of clutches being configured to be opened to send more power to said electric generator; and
a control configured to open at least one clutch of the plurality of clutches associated with at least one of said plurality of fan rotors when reduced power is needed for propulsion of said gas turbine engine, and to thus increase an amount of power sent to said electric generator.

2. The gas turbine engine as set forth in claim 1 , wherein at least one clutch of the plurality of clutches is configured to be opened should it be determined that an associated fan rotor is damaged.

3. The gas turbine engine as set forth in claim 1 , wherein said plurality of fan rotors also being provided with variable inlet guide vanes, with said variable inlet guide vanes configured to be adjusted to control the amount of power supplied to said plurality of fan rotors, said control also being configured to control said variable inlet guide vane to reduce the power utilized by at least some of said plurality of fan rotors when reduced power is necessary to increase the amount of power sent to said electric generator.

4. The gas turbine engine as set forth in claim 3 , wherein said variable inlet guide vanes are configured to be adjusted to send more power to the electric generator.

5. A method of operating a gas turbine engine comprising: operating a gas generator including at least one compressor rotor and at least one gas generator turbine rotor and a combustion section, and driving a fan drive turbine by products of combustion from the gas generator, the fan drive turbine driving a shaft; said shaft engaging gears and driving a plurality of fan rotors; and controlling an amount of power utilized by said plurality of fan rotors; providing a plurality of clutches, positioning a respective clutch of the plurality of clutches between said shaft and each of said plurality of fan rotors, and opening or closing at least one clutch of the plurality of clutches to control the amount of power, opening at least one of said clutches to reduce power consumption by the gas turbine engine, said shaft also driving a generator to generate electricity; and
wherein a control opens said at least one clutch of the plurality of clutches to send more power to said electric generator when less power is required for propulsion.

6. The method as set forth in claim 5 , wherein a respective clutch of the plurality of clutches is opened when it is determined that an associated fan rotor is damaged.

7. The method as set forth in claim 5 , wherein said fan rotors are provided with variable inlet guide vanes, and said variable inlet guide vanes being adjusted to control the amount of power.

8. The method as set forth in claim 7 , wherein said variable inlet guide vanes are adjusted to send more power to the electric generator.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Lord Wesley K
• Chandler Jesse M
• Winter Michael
• Mccune Michael E
• Sheridan William G

Classifications

• F02C3/10 Primary

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F02K3/00

  Plants including a gas turbine driving a compressor or a ducted fan · CPC title

• F02C3/107

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

• B64D27/12

  within, or attached to, wings · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title