Counter-rotating propeller system with capability to stop rotation of one row

Patent metadata

Field	Value
Publication number	US-2019283864-A1
Application number	US-201815924030-A
Country	US
Kind code	A1
Filing date	Mar 16, 2018
Priority date	Mar 16, 2018
Publication date	Sep 19, 2019
Grant date	—

Abstract

A propeller system has a pair of rotors and a pair of blade sets and at least one a drive input to drive a first of the rotors and blade sets and a second of the rotors and blade sets. The blade sets are positioned such that when both are driven, air will be driven across the first blade set and then across the second blade set. There is a pitch change mechanism to change an angle of incidence of the blade in at least one blade sets. There is a device for selectively stopping rotation of at least one of the first or second rotor and blade set while still allowing rotation of the other rotor and blade set. The pitch change mechanism of the stopped blade set can still change the angle of incidence when the device has stopped rotation. A method is also disclosed.

First claim

1 . A propeller system comprising:
a pair of rotors and a pair of blade sets and at least one drive input to drive a first of said rotors and blade sets and a second of said rotors and blade sets; said blade sets being positioned such that when both are driven, air will be driven across said first blade set, and then across said second blade set; there being a pitch change mechanism to change an angle of incidence in at least one of said first and second blade sets, and there being a device for selectively stopping rotation of said at least one of said first and second blade sets while still allowing rotation of the other of said first and second blade sets; and said pitch change mechanism of said at least one of said first and second blade sets still allowing change of said angle of incidence when said device has stopped rotation.

2 . The propeller system as set forth in claim 1 , wherein said at least one drive input is a single drive input.

3 . The propeller system as set forth in claim 2 , wherein said device is a clutch.

4 . The propeller system as set forth in claim 1 , wherein a control selectively changes the angle of incidence of said one of said first and second blade sets and also selectively controls said device.

5 . The propeller system as set forth in claim 1 , said control causing said one of said first and second blade sets to be driven when at higher power operation of an associated aircraft, and stopping rotation of said one of said first and second blade sets at lower power operation of said aircraft.

6 . The propeller system as set forth in claim 5 , wherein said higher power operation includes a take-off condition for the associated aircraft.

7 . The propeller system as set forth in claim 6 , wherein said lower power operation includes a cruise condition of the associated aircraft.

8 . The propeller system as set forth in claim 1 , wherein said device is a clutch for stopping rotation of said one of said first and second blade sets.

9 . The propeller system as set forth in claim 1 , wherein said at least one drive input to said first and second rotors and blade sets are two separate drive inputs, and said device is a control for stopping drive input from a respective one of said first and second drive inputs.

10 . The propeller system as set forth in claim 9 , wherein a control causes said one of said first and second blade sets to be driven at higher power operation of an associated aircraft, and stops rotation of said one of said first and second blade sets at lower power operation of said aircraft.

11 . A method of operating a propeller system mounted on an aircraft comprising the steps of:
(a) providing a pair of rotors and a pair of blade sets and driving a first of said rotors and blade sets and a second of said rotors and blade sets; and (b) stopping rotation of one of said first and second blade sets, while still rotating a second of said first and second blade sets, and changing an angle of incidence of said one of said first and second blade sets while it is stopped from rotating.

12 . The propeller system as set forth in claim 11 , wherein a control selectively changing the angle of incidence of one of said first and second blade sets and also selectively controlling a device to stop rotation of said at least one of said first and second blade sets.

13 . The propeller system as set forth in claim 12 , wherein said control causing said one of said first and second blade sets to be driven at higher power operation of an associated aircraft, and stopping rotation of said one of said first and second blade sets at lower power operations.

14 . The propeller system as set forth in claim 13 , wherein said higher power operation includes a take-off condition for the associated aircraft.

15 . The propeller system as set forth in claim 14 , wherein said lower power operation includes a cruise condition of the associated aircraft.

16 . The propeller system as set forth in claim 11 , wherein a control causing said one of said first and second blade sets to be driven at higher power operation of an associated aircraft, and stopping rotation of said one of said first and second blade sets at lower power operations.

17 . The propeller system as set forth in claim 16 , wherein said higher power operation includes a take-off condition for the associated aircraft.

18 . The propeller system as set forth in claim 14 , wherein said lower power operation includes a cruise condition of the associated aircraft.

19 . The propeller system as set forth in claim 11 , wherein a clutch is opened for stopping rotation of said one of said first and second blade sets.

20 . The propeller system as set forth in claim 11 , wherein said drive to said first and second rotors and blade sets is provided by two separate drive inputs, and a control stopping drive input from a respective one of said two drive inputs.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Henze Chad M

Classifications

• B64D35/06

  the propellers or rotors being counter-rotating · CPC title

• B64C11/308 Primary

  automatic · CPC title

• B64C11/30

  Blade pitch-changing mechanisms · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D2027/005

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