US20120294719A1 - Vertical lift fan - Google Patents

Vertical lift fan Download PDF

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Publication number
US20120294719A1
US20120294719A1 US13/439,425 US201213439425A US2012294719A1 US 20120294719 A1 US20120294719 A1 US 20120294719A1 US 201213439425 A US201213439425 A US 201213439425A US 2012294719 A1 US2012294719 A1 US 2012294719A1
Authority
US
United States
Prior art keywords
fan
output gear
brake unit
vertical lift
rotors
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US13/439,425
Other languages
English (en)
Inventor
Russell G. PAYNE
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Assigned to ROLLS-ROYCE PLC reassignment ROLLS-ROYCE PLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Payne, Russell Geoffrey
Publication of US20120294719A1 publication Critical patent/US20120294719A1/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/001—Shrouded propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded

Definitions

  • the present invention relates to a vertical lift fan.
  • Vertical take-off and landing or short take-off and landing are desirable characteristics for an aircraft, and fixed vertical lift fan systems can be used for this purpose.
  • FIG. 1 shows schematically a conventional lift fan arrangement.
  • the fan has an upper air intake 1 and a lower exhaust nozzle 2 with one or more coaxial fan rotors 3 therebetween.
  • the fan rotors are driven by a gearbox 4 , which in turn receives drive from an aircraft main engine via a transmission shaft 5 .
  • a multi-plate friction clutch 6 located between the gearbox and the transmission shaft 5 allows the drive to the fan to be connected and disconnected. This enables the controlled selection and deselection of power to the lift fan, since the aircraft does not need vertical lift thrust at all times.
  • the clutch 6 can be oversized, but this leads to an overly large and heavy system.
  • the present invention provides a vertical lift fan having a switchable transmission system, the fan including:
  • a lift fan unit having one or more fan rotors
  • a differential gearbox having an input gear connectable to a transmission shaft for providing power to the fan, and first and second output gears, the first output gear driving the fan rotors,
  • a first brake unit for braking the first output gear
  • a second brake unit for braking the second output gear
  • the fan does not require wear-out friction components in the drive-line between the transmission shaft and the fan rotors.
  • the first and second brake units which may be wear-out friction components, can be located in accessible positions allowing them to be removed or serviced without removal of the lift fan unit from an aircraft.
  • the differential gearbox can, conveniently, replace the gearbox of the conventional lift fan arrangement to provide an appropriate gear ratio between the transmission shaft and the fan rotors. Further, the differential gearbox can turn the drive through, typically, 90° from the transmission shaft to the fan rotors.
  • the fan may have any one or, to the extent that they are compatible, any combination of the following optional features.
  • the second output gear can be an idler gear. That is, it can be a free-spinning “dead-end” for use in normal forward flight.
  • the brake units are configured such that only one of the brake units is active at any one time.
  • the brake units are allowed to act simultaneously and with variable amounts of slippage (i.e. to act as clutches) in order to vary the amount of lift fan thrust.
  • the first output gear drives a drive shaft which is coaxial with the fan rotors.
  • the vertical lift fan can further include a nose cone which houses one of the first and second brake units. Additionally or alternatively, the vertical lift fan can further include a sump fairing which houses one of the first and second brake units.
  • the nose cone and sump fairing of a vertical lift fan are typically relatively accessible.
  • the differential gearbox may be positioned below the lift fan unit (in which case the first brake unit can be housed in the nose cone and the second brake unit in the sump fairing).
  • FIG. 1 shows a schematic diagram of a conventional vertical lift fan arrangement
  • FIG. 2 shows a schematic diagram of a vertical lift fan arrangement according to the present invention.
  • FIG. 2 shows schematically a vertical lift fan arrangement according to the present invention.
  • the fan has an upper air intake 11 and a lower exhaust nozzle 12 with one or more coaxial fan rotors 13 therebetween.
  • the fan receives drive power from an aircraft main engine via a transmission shaft 15 .
  • the transmission shaft 15 enters the side of the vertical lift fan below the fan rotors 13 and meshes to an input gear 18 of a differential gearbox 17 .
  • the gearbox has a first output gear 19 which drives the fan rotors 13 via a coaxial drive shaft 20 , which is 90° to the transmission shaft.
  • the gearbox thus determines the gearing between the transmission shaft and the drive shaft.
  • the gearbox also has a second output gear 21 .
  • the drive shaft 20 terminates in a first brake unit 22 housed in a nose cone 23 of the fan.
  • the second output gear 21 drives a further shaft 24 which terminates in a second brake unit 25 housed in a gearbox sump fairing 26 of the fan.
  • the differential gearbox 17 and brake units 22 , 25 effectively provide a switchable transmission system for the vertical lift fan. Only one of the brake units is active at any one time.
  • the first brake unit 22 is deactivated and the second brake unit 25 activated.
  • the rotational action provided by the transmission shaft 15 is prevented from turning the further shaft 24 and is diverted into the drive shaft 20 and thence to the fan rotors 13 .
  • the first brake unit is activated and the second brake unit deactivated.
  • the rotational action is then prevented from turning the drive shaft and is diverted into the further shaft.
  • the second output gear 21 is an idler gear that spins freely during normal forward flight.
  • the brake units 22 , 25 are relatively easily accessible by virtue of being housed in the nose cone 23 and the sump fairing 26 .
  • worn out friction components of these units, such as brake pads can be replaced without having to split the transmission shaft 15 from the gearbox 17 , and thus without having to remove the fan from the aircraft. This greatly simplifies fan maintenance, reduces the cost of ownership of the aircraft, as well as potentially reducing the installed weight of the lift fan.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Retarders (AREA)
  • Structure Of Transmissions (AREA)
  • Gear Transmission (AREA)
  • Braking Arrangements (AREA)
US13/439,425 2011-05-18 2012-04-04 Vertical lift fan Abandoned US20120294719A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1108261.7 2011-05-18
GB1108261.7A GB2490915B (en) 2011-05-18 2011-05-18 Vertical lift fan

Publications (1)

Publication Number Publication Date
US20120294719A1 true US20120294719A1 (en) 2012-11-22

Family

ID=44260667

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/439,425 Abandoned US20120294719A1 (en) 2011-05-18 2012-04-04 Vertical lift fan

Country Status (3)

Country Link
US (1) US20120294719A1 (fr)
EP (1) EP2524868A3 (fr)
GB (1) GB2490915B (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9902493B2 (en) * 2015-02-16 2018-02-27 Hutchinson VTOL aerodyne with supporting axial blower(s)
AU2015349532B2 (en) * 2014-11-22 2019-03-21 Taiyuan University Of Technology Transmission apparatus for contra-rotating impeller ventilation
US10815900B2 (en) 2017-05-09 2020-10-27 Rolls-Royce Plc Geared gas turbine engine
US20210339855A1 (en) * 2019-10-09 2021-11-04 Kitty Hawk Corporation Hybrid power systems for different modes of flight
US20220073204A1 (en) * 2015-11-10 2022-03-10 Matternet, Inc. Methods and systems for transportation using unmanned aerial vehicles
US11859542B2 (en) * 2021-12-20 2024-01-02 Rolls-Royce North American Technologies, Inc. Dual power lift system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103047319B (zh) * 2012-12-28 2015-01-21 天津曙光敬业科技有限公司 无人驾驶旋翼直升机在空中刹车装置
CN111377059B (zh) * 2020-05-19 2022-11-04 重庆宇矛航空科技有限公司 高提升力无翼飞行器动力系统

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3810360A (en) * 1971-10-20 1974-05-14 Mtu Muenchen Gmbh Gas generator with selectively connectible turbine system

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126966A (en) * 1964-03-31 Agamian
US1846125A (en) * 1930-03-25 1932-02-23 Fon Alphonse F La Aircraft elevating and propelling mechanism
US1942888A (en) * 1933-02-16 1934-01-09 Paul F West Helicopter lifting screw and operating mechanism therefor
US2940691A (en) * 1958-11-24 1960-06-14 Ryan Aeronautical Co Vertical take-off power plant system
US5890441A (en) * 1995-09-07 1999-04-06 Swinson Johnny Horizontal and vertical take off and landing unmanned aerial vehicle
US6269627B1 (en) * 1998-12-16 2001-08-07 United Technologies Corporation Rapid thrust response control logic for shaft-driven lift fan STOVL engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3810360A (en) * 1971-10-20 1974-05-14 Mtu Muenchen Gmbh Gas generator with selectively connectible turbine system

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2015349532B2 (en) * 2014-11-22 2019-03-21 Taiyuan University Of Technology Transmission apparatus for contra-rotating impeller ventilation
US9902493B2 (en) * 2015-02-16 2018-02-27 Hutchinson VTOL aerodyne with supporting axial blower(s)
US20220073204A1 (en) * 2015-11-10 2022-03-10 Matternet, Inc. Methods and systems for transportation using unmanned aerial vehicles
US11820507B2 (en) * 2015-11-10 2023-11-21 Matternet, Inc. Methods and systems for transportation using unmanned aerial vehicles
US10815900B2 (en) 2017-05-09 2020-10-27 Rolls-Royce Plc Geared gas turbine engine
US20210339855A1 (en) * 2019-10-09 2021-11-04 Kitty Hawk Corporation Hybrid power systems for different modes of flight
US11787537B2 (en) * 2019-10-09 2023-10-17 Kitty Hawk Corporation Hybrid power systems for different modes of flight
US11859542B2 (en) * 2021-12-20 2024-01-02 Rolls-Royce North American Technologies, Inc. Dual power lift system

Also Published As

Publication number Publication date
EP2524868A2 (fr) 2012-11-21
GB201108261D0 (en) 2011-06-29
GB2490915B (en) 2013-04-03
GB2490915A (en) 2012-11-21
EP2524868A3 (fr) 2015-06-17

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Date Code Title Description
AS Assignment

Owner name: ROLLS-ROYCE PLC, GREAT BRITAIN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:PAYNE, RUSSELL GEOFFREY;REEL/FRAME:027993/0133

Effective date: 20120314

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION