Fan clutch for convertible engine

Patent metadata

Field	Value
Publication number	US-2020017229-A1
Application number	US-201816035340-A
Country	US
Kind code	A1
Filing date	Jul 13, 2018
Priority date	Jul 13, 2018
Publication date	Jan 16, 2020
Grant date	—

Abstract

Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.

First claim

What is claimed is:

1 . A convertible engine for an aircraft, comprising:
an engine core comprising a low pressure turbine shaft; and a bypass fan system comprising:
a bypass fan comprising a fan clutch, wherein the fan clutch is configured to selectively decouple at least a portion of the bypass fan from the low pressure turbine shaft.

2 . The convertible engine of claim 1 , wherein the fan clutch is at least one of an electromechanical clutch and a piezoelectric clutch.

3 . The convertible engine of claim 1 , wherein the fan clutch is a magnetorheological clutch comprising a magnetorheological fluid.

4 . The convertible engine of claim 3 , wherein electromagnets are disposed in at least one non-rotating, fixed reference component of the convertible engine and in close proximity to the fan clutch, and wherein the electromagnets are configured to selectively induce a magnetic field through the magnetorheological fluid in the fan clutch to couple the at least a portion of the bypass fan to the low pressure turbine shaft.

5 . The convertible engine of claim 1 , wherein the bypass fan is coupled to the low pressure turbine shaft when the convertible engine is operated in a thrust mode, and wherein the bypass fan is decoupled from the low pressure turbine shaft when the convertible engine is operated in a shaft power mode.

6 . The convertible engine of claim 5 , further comprising: inlet guide vanes selectively operable to restrict bypass airflow through the convertible engine when the bypass fan is decoupled from the low pressure turbine shaft.

7 . The convertible engine of claim 1 , wherein the bypass fan comprises an inner fan and an outer fan, wherein the inner fan is rigidly coupled to the low pressure turbine shaft, and wherein the fan clutch is disposed between the inner fan and the outer fan and configured to selectively couple the outer fan to the inner fan.

8 . The convertible engine of claim 7 , wherein the outer fan is free to spin concentrically about the inner fan and does not generate bypass airflow to produce thrust when the outer fan is decoupled from the inner fan.

9 . The convertible engine of claim 8 , further comprising: inlet guide vanes selectively operable to restrict bypass airflow through the convertible engine when the outer fan is decoupled from the inner fan.

10 . The convertible engine of claim 9 , wherein the outer fan is coupled to the inner fan via the fan clutch when the convertible engine is operated in a thrust mode, and wherein the outer fan is decoupled from the inner fan when the convertible engine is operated in a shaft power mode.

11 . The convertible engine of claim 10 , wherein the low pressure turbine shaft is selectively coupled to a gearbox through a selectively operable gearbox clutch to cause selective rotation of a rotor system when the convertible engine is operated in the shaft power mode.

12 . An aircraft, comprising:
a fuselage; and a convertible engine disposed within the fuselage and operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode, the convertible engine comprising:
an engine core comprising a low pressure turbine shaft; and
a bypass fan system comprising:
a bypass fan comprising a fan clutch, wherein the fan clutch is configured to selectively couple at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode, and wherein the fan clutch is configured to decouple the at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.

13 . The aircraft of claim 12 , wherein the fan clutch is at least one of an electromechanical clutch, a piezoelectric clutch, and a magnetorheological clutch.

14 . The aircraft of claim 12 , wherein the bypass fan comprises an inner fan and an outer fan, wherein the inner fan is rigidly coupled to the low pressure turbine shaft, and wherein the fan clutch is disposed between the inner fan and the outer fan and configured to selectively couple the outer fan to the inner fan.

15 . The aircraft of claim 12 , wherein the low pressure turbine shaft is configured to provide shaft power to at least one aircraft system when the convertible engine is operated in the shaft power mode.

16 . The aircraft of claim 15 , further comprising: at least one additional mechanical locking component used to form a rigid mechanical connection between the bypass fan and the low pressure turbine shaft when the fan clutch selectively couples the at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode.

17 . The aircraft of claim 15 , wherein the low pressure turbine shaft is selectively coupled to a gearbox through a selectively operable gearbox clutch to cause selective rotation of a rotor system when the convertible engine is operated in the shaft power mode.

18 . A method of operating an aircraft, comprising:
providing an aircraft engine comprising: an engine core comprising a low pressure turbine shaft; and a bypass fan system comprising a bypass fan having a fan clutch; operating the aircraft engine to generate bypass airflow in order to induce thrust by selectively coupling at least a portion of the bypass fan to the low pressure turbine shaft; selectively decoupling at least a portion of the bypass fan from the low pressure turbine shaft; and operating the aircraft engine to provide shaft power to an aircraft system via the low pressure turbine shaft without generating bypass airflow that induces thrust.

19 . The method of claim 18 , wherein the selectively coupling at least a portion of the bypass fan from the low pressure turbine shaft is accomplished by passing an electrical current through a plurality of electromagnets to produce a magnetic field proximate to the fan clutch.

20 . The method of claim 19 , wherein the selectively decoupling at least a portion of the bypass fan from the low pressure turbine shaft is accomplished by interrupting the electrical current through a plurality of electromagnets.

21 . The method of claim 18 , wherein the low pressure turbine shaft is selectively coupled to a rotor system of the aircraft, and wherein the shaft power from the low pressure turbine shaft is used to cause rotation of the rotor system.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Steinert Alan Hisashi
• Parsons Thomas Dewey
• Schank Troy Cyril

Classifications

• 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

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F05D2260/407

  through piezoelectric conversion · CPC title

• F05D2220/325

  to drive unshrouded, high solidity propeller · CPC title

• F02K3/075 Primary

  controlling flow ratio between flows · CPC title