GB2584381A - Use of spinning cylinders to achieve thrust reversal - Google Patents

Use of spinning cylinders to achieve thrust reversal Download PDF

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Publication number
GB2584381A
GB2584381A GB1901276.4A GB201901276A GB2584381A GB 2584381 A GB2584381 A GB 2584381A GB 201901276 A GB201901276 A GB 201901276A GB 2584381 A GB2584381 A GB 2584381A
Authority
GB
United Kingdom
Prior art keywords
cylinder
thrust reverser
flow
reverser according
fan
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.)
Withdrawn
Application number
GB1901276.4A
Other versions
GB201901276D0 (en
Inventor
Gregory Smith Anthony
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB1901276.4A priority Critical patent/GB2584381A/en
Publication of GB201901276D0 publication Critical patent/GB201901276D0/en
Publication of GB2584381A publication Critical patent/GB2584381A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/08—Influencing air flow over aircraft surfaces, not otherwise provided for using Magnus effect
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A cylinder 1 is positioned across a turbofan engine bypass duct 2. The duct 2 may be blocked using a blocker door 3, creating an aperture 4 in the nacelle. The cylinder spins, deflecting fan flow out of the aperture due to a Magnus effect, achieving thrust reversal. The cylinder can be electrically driven. Alternatively the fan flow, core flow, or free stream flow may rotate the cylinder. Vanes may be fitted to the cylinder to assist with flow driven rotation. Surface roughness may be added to increase skin friction between cylinder and fan flow. The cylinder may be shielded and only exposed where needed. The cylinder may be stowed out of the fan duct. Multiple spinning cylinders may be used. The cylinder may produce other thrust vector angles, used for pitch control, additional or reduced lift, or achieving the function of a variable area nozzle for the fan flow.

Description

Use of spinning cylinders to achieve thrust reversal This invention relates to the use of spinning cylinders to turn the exhaust flow from an engine in order to modify its direction (vector).
Many aircraft require thrust reversal from the engines when landing in order to be able to stop within the available length of the runway. Such thrust reverser systems turn some or all of the engine exhaust flow in a partially forward direction. Some use a bucket arrangement around the engine nozzle. On turbofan engines it is usual to put vents into the engine nacelle. On landing a blocker door is moved to open the vents and redirect the fan flow towards them. Within the vents multiple vane sets are then used to angle the flow towards the upstream direction producing a reverse thrust which slows the aircraft.
The Magnus effect is the phenomenon whereby a spinning cylinder will deflect the flow which approaches it. It has been used in the past to achieve a force similar to that of a sail on a ship.
In this invention described with reference to Figure 1, a cylinder, 1, is positioned across the bypass duct of turbofan engine, 2, through which flow from the engine's fan is travelling (the fan flow). During landing the duct, 2, can be blocked using the blocker door, 3, and creating an aperture, 4, in the engine nacelle. The cylinder, 1, is spun about its centre In such a way that the fan flow is deflected out of the aperture, 4, in an outward and forward direction as indicated by arrow, 5, thus producing reverse thrust.
The diameter of the cylinder, the speed at which it spins, and its position with the duct all influence the level of thrust reversal that is achieved.
The cylinder can be electrically driven. It could also be mechanically driven by an auxiliary shaft from the engine. Alternatively, the fan flow, core flow, or free stream flow could be used to rotate the cylinder. Vanes could be fitted to the cylinder to assist with the flow driven rotation.
The surface of the cylinder can be modified to enhance or optimise the thrust reverse flow direction. For example, surface roughness could be added to increase skin friction between the cylinder and the fan flow.
The cylinder could be operated within a shield which only exposes the surface of the cylinder to the fan flow where needed.
The cylinder could be tapered or waisted in the centre in order to vary the distribution of its interaction with the fan flow.
The cylinder could be stowed out the fan duct when not in use to reduce the blockage in the duct.
Multiple cylinders could be used to achieve flow reversal and hence thrust reversal around the circumference of the engine.
The cylinder could be positioned partly or completely outside the fan duct to redirect the flight stream and achieve force control using that flow.
The spinning cylinder could be used in combination with other flow control mechanisms such as static vanes and ejectors.
The spinning cylinder could be used to produce other thrust vector angles as well as reversed. This might be used for pitch control, or additional or reduced lift. This might include the ability to achieve the function of a variable area nozzle for the fan flow.

Claims (21)

  1. CLAIMS1. A thrust reverser in which Magnus effect is used to deflect the engine flow in a forward direction relative to flight.
  2. 2. A thrust reverser according to claim 1 in which a single cylinder is located within the bypass or fan flow of a turbofan engine and spun about its axis in order to deflect the fan flow.
  3. 3. A thrust reverser according to claim 1 in which more than one cylinder is located within the bypass duct of a turbofan engine and each is spun about their axes in order to deflect the fan flow.
  4. 4. A thrust reverser according to any of the preceding claims in which the speed at which each cylinder is rotated can be varied in order to control the angle of the flow deflection.
  5. 5. A thrust reverser according to any of preceding claims in which any cylinder has vanes on the surface to encourage rotation.
  6. 6. A thrust reverser according to any of preceding claims in which any cylinder has a ***** rough surface to increase skin friction between the cylinder and the fan flow. **** ** * * * *
  7. * ** 7. A thrust reverser according to any of preceding claims in which the diameter of any cylinder is varied along its length in order to optimise the flow deflection at each location. *
  8. 8. A thrust reverser according to any of preceding claims in which any cylinder is partially shrouded to allow only the required part of the cylinder to be exposed to the fan flow.
  9. * * 9. A thrust reverser according to any of preceding claims in which any cylinder can be stowed when not being used for thrust reversal so as to minimise resistance on the fan flow.
  10. 10. A thrust reverser according to any of preceding claims in which any cylinder is made up of a number of segments on a flexible shaft in order to allow the axis of rotation to be curved in the engine's circumferential direction.
  11. 11. A thrust reverser according to any of the preceding claims in which the spinning cylinders are used in conjunction with other flow turning devices within the bypass duct such as vanes.
  12. 12. A thrust reverser according to any of the preceding claims in which the flow can be controlled to provide additional or reduced lift.
  13. 13. A thrust reverser according to any of the preceding claims in which the flow can be controlled to assist the function of a variable area fan nozzle.
  14. 14. A thrust reverser according to any of the preceding claims in which any cylinder is exposed to the flight stream flow to influence its direction and create additional forces.
  15. 15. A thrust reverser according to any of the preceding claims in which any cylinder is driven directly from the engine using an auxiliary shaft.
  16. 16. A thrust reverser according to any of the preceding claims in which any cylinder is driven by the fan flow from the engine.
  17. 17. A thrust reverser according to any of the preceding claims in which any cylinder is driven by the free stream flow.
  18. 18. A thrust reverser according to any of preceding claims in which any cylinders is driven using a motor.
  19. 19. A thrust reverser according to claim 18 in which the motor is electrically powered.
  20. 20. A thrust reverser according to claim 18 in which the motor is hydraulically powered.
  21. 21. A thrust reverser according to claim 18 in which the motor is powered by compressed gas. * . * * * * * * * * * * * * * 00 * * * O060 * *
GB1901276.4A 2019-01-30 2019-01-30 Use of spinning cylinders to achieve thrust reversal Withdrawn GB2584381A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1901276.4A GB2584381A (en) 2019-01-30 2019-01-30 Use of spinning cylinders to achieve thrust reversal

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1901276.4A GB2584381A (en) 2019-01-30 2019-01-30 Use of spinning cylinders to achieve thrust reversal

Publications (2)

Publication Number Publication Date
GB201901276D0 GB201901276D0 (en) 2019-03-20
GB2584381A true GB2584381A (en) 2020-12-09

Family

ID=65997845

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1901276.4A Withdrawn GB2584381A (en) 2019-01-30 2019-01-30 Use of spinning cylinders to achieve thrust reversal

Country Status (1)

Country Link
GB (1) GB2584381A (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0830285B1 (en) * 1995-06-07 2002-03-27 JESWINE, William W. A fluid propulsion system for accelerating and directionally controlling a fluid
US20100281874A1 (en) * 2007-01-09 2010-11-11 Rolls-Royce Corporation Airflow vectoring member
US20130146675A1 (en) * 2011-12-13 2013-06-13 Eads Deutschland Gmbh Thrust vector control

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0830285B1 (en) * 1995-06-07 2002-03-27 JESWINE, William W. A fluid propulsion system for accelerating and directionally controlling a fluid
US20100281874A1 (en) * 2007-01-09 2010-11-11 Rolls-Royce Corporation Airflow vectoring member
US20130146675A1 (en) * 2011-12-13 2013-06-13 Eads Deutschland Gmbh Thrust vector control

Also Published As

Publication number Publication date
GB201901276D0 (en) 2019-03-20

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Legal Events

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WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)