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WO1988010210A1 - Plan de sustentation ameliore par venturi - Google Patents

Plan de sustentation ameliore par venturi Download PDF

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Publication number
WO1988010210A1
WO1988010210A1 PCT/US1988/002102 US8802102W WO8810210A1 WO 1988010210 A1 WO1988010210 A1 WO 1988010210A1 US 8802102 W US8802102 W US 8802102W WO 8810210 A1 WO8810210 A1 WO 8810210A1
Authority
WO
WIPO (PCT)
Prior art keywords
airfoil
venturi
recited
air
venturi assembly
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.)
Ceased
Application number
PCT/US1988/002102
Other languages
English (en)
Inventor
Mark T. Willis
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 BR888807113A priority Critical patent/BR8807113A/pt
Priority to KR1019890700365A priority patent/KR890701417A/ko
Publication of WO1988010210A1 publication Critical patent/WO1988010210A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/04—Boundary layer controls by actively generating fluid flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/28—Boundary layer controls at propeller or rotor blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the invention relates to an airfoil and more specifically to an airfoil having a venturi assembly incorporated therein adjacent the trailing edge of the airfoil to enhance its performance.
  • Applicant's novel venturi enhanced airfoil has application in both a fixed horizontal airfoil of an aircraft or its structure may be incorporated into the vertical rudder of the tail section of an aircraft or helicopter.
  • the leading edge of the airfoil causes airflow across both the upper and lower surface of the airfoil.
  • the velocity of the air passing over the upper surface of the airfoil is greater that that passing beneath its lower surface thereby causing a lower pressure on the top surface of the airfoil which results in lift of the airfoil itself in a static condition.
  • Applicant's novel venturi assembly is incorporated into the airfoil structure adjacent the trailing edge thereof.
  • the venturi has an entry port at its upper end, an exit port at its lower end, both of which have a greater circumference than the throat portion intermediate its top and bottom end.
  • a plurality of air nozzles are spaced around the circumference of the venturi at a position between the throat and the exit port thereof. These air nozzles are in communication with a plenum chamber within the airfoil that is supplied with pressurized air from either the engine of the aircraft or some auxiliary source. This produces an air driven venturi which creates a strong suction on the upper surface of the airfoil. This further increases the velocity of the air passing over the top surface of the airfoil to further decrease the pressure on the top side of the airfoil.
  • the air which has been sucked down through the venturi assembly further increases the high pressure force on the bottom of the airfoil and also slows the velocity of the air passing along the lower surface of the airfoil.
  • the combination of these different forces results in additional lift performance for the airfoil itself.
  • venturi assembly has a vertical axis and this axis can be incorporated into the airfoil at an angle with respect to the horizontal axis of the airfoil between a range of two degrees to twenty degrees. This inclination results in a vectored thrust in the forward direction that the wing would be traveling in.
  • the geometrical configuration of the venturi's aperture can be circular, elongated oval shaped, or other desired geometrical shapes. There may be more than one venturi assembly formed adjacent the trailing edge of an airfoil.
  • the venturi enhanced airfoil can also be incorporated into the rudder of the tail of an aircraft or helicopter.
  • the rudder can have either a single venturi assembly incorporated therein or multiple venturi assembly incorporated therein.
  • one venturi assembly could have its • entry port on one vertical side of the airfoil and the other venturi assembly could have its entry port on the opposite side of the airfoil.
  • they can create their suction effects on both sides of the airfoil, which in turn can move the airfoil in either direction in a static condition. This effect can be created by increasing and decreasing the pressurized airflow in the particularly desired venturi in order to move the airfoil in the direction so desired.
  • the exhaust gas from the turbine of the helicopter can be ducted to the front of the verticle venturi enhanced airfoil which will be mounted on the end of the helicopters tail boom.
  • the enhanced airfoil will act as a rudder with the enhanced pressure differential acting against the main rotor torque.
  • Figure 1 is a partial top plan view illustrating applicant's novel venturi enhanced airfoil
  • Figure 2 is a schematic cross-sectional elevation view taken along lines 2-2 of Figure 1 ;
  • Figure 3 is a partial top plan view illustrating a first alternative venturi enhanced airfoil
  • Figure 4 is a schematic cross-sectional elevational view taken along lines 4-4 of Figure 3;
  • Figure 5 is a schematic illustration that indicates how air is supplied to the venturi assemblies.
  • Figure 6 is a side elevation view of the venturi enhanced airfoil utilized in the tail of an aircraft
  • Figure 7 is a horizontal cross section taken along lines 7-7 of Figure 6;
  • Figure 8 is a first alternative embodiment " of the venturi enhanced airfoil utilized in the tail of an aircraft ;
  • Figure 9 is a horizontal cross-sectional view taken along lines 9-9 of Figure 8.
  • Figure 10 is a horizontal cross-sectional view taken along lines 10-10 of Figure 8.
  • Figure 11 is a partial cross-sectional view illustrating a modified venturi assembly in the horizontal fixed airfoil of an aircraft.
  • the fixed wing airfoil is generally designated numeral 16. It has a leading edge 17, a trailing edge 18, an upper surface 19, and a lower surface 20.
  • a deflector cap 22 is mounted adjacent and covering leading edge 17.
  • a venturi assembly 24 is located adjacent trailing edge 18.
  • SUBSTITUTE SHEET plenum chamber 21 is positioned in leading edge 17 and pressurized air is released through orifice 21a to travel over both the respective upper and lower surfaces 19 and 20.
  • Venturi assembly 24 has an entry port 25, an exit port 26, and a throat 27.
  • Venturi assembly 24 has a vertical x-axis with respect to the y-axis. The y-axis has a forward inclination with the x-axis and this may be designated between the range of two to twenty degrees.
  • Positioned slightly below throat 27 are a plurality of air nozzles 30 that are in communication with a plenum chamber 32. Conventional ducting (not shown) would be connected to plenum chamber 32 from a source of prsssurized air, such as the exhaust of the aircraft.
  • a schematic illustration of such a system is illustrated in Figure 5 where numeral 35 identifies a source of pressurized air.
  • the airfoil illustrated in Figure 3 is designated numeral 40. It has a leading edge 41, a trailing edge 42, an upper surface 43, and a lower edge 44. It has a plurality of venturi assemblies 45 and these have an elongated oval-shape. Each of them have an entry port 47, an exit port 48, and a throat 49. Air nozzles 50 are in communication with plenum chamber 52.
  • FIG. 6 an embodiment is illustrated that shows the venturi enhanced airfoil incorporated into the tail 53 of the fuselage 54 of an aircraft.
  • the aircraft may be a fixed airfoil type of conventional aircraft or it may be the tail of a helicopter.
  • Airfoil 56 functions as the rudder and it pivots about an axis 58. Utilizing the same descriptive designations to airfoil 56 as that of the horizontally oriented airfoils, it has a leading edge 60, a trailing edge 61, an upper surface 62, and a lower surface 63.
  • the venturi assembly 65 has an entry port 66, an exit port 67, and a throat 68.
  • a plurality of air nozzles 70 are in communication with a plenum chamber 72.
  • Plenum chamber 72 would have conventional ducting from a pressurized air supply source.
  • FIG. 8-10 a first alternative embodiment of the vertically oriented venturi airfoil is illustrated.
  • airfoil 75 has a leading edge 76, a trailing edge 77, an upper surface 78, and a lower surface 79.
  • An upper venturi assembly 80 has its entry port 81 on one side of airfoil 75 while the lower venturi assembly 90 has its entry port 91 on the opposite side.
  • Venturi assembly 80 also has an exit port 82, a throat 83, air nozzles 84 and a plenum chamber 85.
  • lower venturi assembly 90 also has an exit port 92, a throat 93, air nozzles 94, and a plenum chamber 95.
  • a modified structure of a venturi assembly 100 is illustrated in Figure 11 in a horizontal fixed wing. It has an entry port 101, an exit port 102, and a throat 103. A plurality of air nozzles 104 are in communication with a plenum chamber 105. Deflector vanes 107 are pivoted on hinge 108 and can be actuated together in coordinated travel to vary the direction of the air flow exiting venturi assembly 100.
  • applicant's novel airfoil construction could be used on a water vehicle to aid in lifting its hull partially or entirely out of the water. It would also provide forward thrust.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Toys (AREA)

Abstract

On améliore le fonctionnement d'un plan de sustentation usuel en ménageant une ou plusieurs ouvertures adjacentes au bord de fuite du plan de sustentation. Ces ouvertures (24) traversent le plan de sustentation, de sa surface supérieure (18) jusqu'à sa surface inférieure (20). L'entrée (25) et la sortie (26) de ces ouvertures ont une circonférence supérieure à celle de la gorge (27) intermédiaire. Cette structure forme un venturi avec un axe vertical. Une pluralité d'ajutages (30) d'air agencés au-dessous de la gorge (27) de l'ouverture sont en communication avec une chambre (32) d'air d'aspiration à l'intérieur du plan de sustentation. Une source d'air pressurisé (35) est reliée à la chambre (32). La structure de ce plan de sustentation amélioré par venturi peut être utilisée soit dans un plan de sustentation horizontal fixe soit dans le gouvernail (53) arrière d'une aéronef ou d'un hélicoptère. Le plan de sustentation amélioré par venturi peut être orienté dans n'importe quelle position entre les axes horizontal et vertical.
PCT/US1988/002102 1987-06-25 1988-06-23 Plan de sustentation ameliore par venturi Ceased WO1988010210A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
BR888807113A BR8807113A (pt) 1987-06-25 1988-06-23 Aerofolio intensificado por difusor
KR1019890700365A KR890701417A (ko) 1987-06-25 1988-06-23 벤츄리장치를 형성한 개선된 에어포일

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US6622387A 1987-06-25 1987-06-25
US066,223 1987-06-25

Publications (1)

Publication Number Publication Date
WO1988010210A1 true WO1988010210A1 (fr) 1988-12-29

Family

ID=22068096

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1988/002102 Ceased WO1988010210A1 (fr) 1987-06-25 1988-06-23 Plan de sustentation ameliore par venturi

Country Status (6)

Country Link
EP (1) EP0319574A4 (fr)
JP (1) JPH02501213A (fr)
KR (1) KR890701417A (fr)
AU (1) AU2325988A (fr)
BR (1) BR8807113A (fr)
WO (1) WO1988010210A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1991009776A1 (fr) * 1989-12-29 1991-07-11 Venturi Applications, Inc. Profil d'aile ameliore par un venturi
EP2031243A1 (fr) * 2007-08-31 2009-03-04 Lm Glasfiber A/S Moyens pour le maintien d'un flux fixe à l'extérieur d'un élément de contrôle de flux
US8573542B2 (en) 2009-08-26 2013-11-05 Airbus Operations Limited Aerofoil slot blowing
WO2018158634A1 (fr) * 2017-02-28 2018-09-07 Steering Financial Ltd. Système de levage aérodynamique
FR3132543A1 (fr) * 2022-02-07 2023-08-11 Safran Nacelles Aéronef comprenant au moins un dispositif de propulsion fluidique intégré à un élément de la cellule et procédé d’utilisation

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2020032938A (ja) * 2018-08-31 2020-03-05 幸福の科学 飛行体

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2631794A (en) * 1947-07-22 1953-03-17 Douglas K Warner Airfoil nose flap arrangement
US2840323A (en) * 1956-05-17 1958-06-24 Bell Aircraft Corp Hinged airfoil with jet nozzle means for aircraft flight control
US2946540A (en) * 1948-09-13 1960-07-26 Sebac Nouvelle Sa Jet propelled aircraft
US2990138A (en) * 1956-10-02 1961-06-27 Power Jets Res & Dev Ltd Aircraft with turbine driven lifting fans
FR1267920A (fr) * 1960-06-15 1961-07-28 Snecma Dispositif de sustentation pour aérodynes, et plus particulièrement pour aérodynes à décollage vertical sans changement d'assiette
US3029045A (en) * 1957-08-28 1962-04-10 Bertin & Cie Ejector systems applicable to thrust generation or augmentation
US3045947A (en) * 1959-04-24 1962-07-24 Bertin & Cie Ejectors, particularly for producing lift in aircraft
US3063658A (en) * 1960-03-01 1962-11-13 Ii Roger W Griswold Supersonic airfoil with boundary layer control
US3525474A (en) * 1968-12-09 1970-08-25 Us Air Force Jet pump or thrust augmentor
US3747874A (en) * 1971-08-25 1973-07-24 Rohr Corp Ejector nozzle having primary nozzles communicating with exhaust gases in plenum chamber
US3819134A (en) * 1972-11-30 1974-06-25 Rockwell International Corp Aircraft system lift ejector
US4442986A (en) * 1982-08-30 1984-04-17 The United States Of America As Represented By The Secretary Of The Navy Leading edge augmentor wing-in-ground effect vehicle

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2631794A (en) * 1947-07-22 1953-03-17 Douglas K Warner Airfoil nose flap arrangement
US2946540A (en) * 1948-09-13 1960-07-26 Sebac Nouvelle Sa Jet propelled aircraft
US2840323A (en) * 1956-05-17 1958-06-24 Bell Aircraft Corp Hinged airfoil with jet nozzle means for aircraft flight control
US2990138A (en) * 1956-10-02 1961-06-27 Power Jets Res & Dev Ltd Aircraft with turbine driven lifting fans
US3029045A (en) * 1957-08-28 1962-04-10 Bertin & Cie Ejector systems applicable to thrust generation or augmentation
US3045947A (en) * 1959-04-24 1962-07-24 Bertin & Cie Ejectors, particularly for producing lift in aircraft
US3063658A (en) * 1960-03-01 1962-11-13 Ii Roger W Griswold Supersonic airfoil with boundary layer control
FR1267920A (fr) * 1960-06-15 1961-07-28 Snecma Dispositif de sustentation pour aérodynes, et plus particulièrement pour aérodynes à décollage vertical sans changement d'assiette
US3525474A (en) * 1968-12-09 1970-08-25 Us Air Force Jet pump or thrust augmentor
US3747874A (en) * 1971-08-25 1973-07-24 Rohr Corp Ejector nozzle having primary nozzles communicating with exhaust gases in plenum chamber
US3819134A (en) * 1972-11-30 1974-06-25 Rockwell International Corp Aircraft system lift ejector
US4442986A (en) * 1982-08-30 1984-04-17 The United States Of America As Represented By The Secretary Of The Navy Leading edge augmentor wing-in-ground effect vehicle

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP0319574A4 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1991009776A1 (fr) * 1989-12-29 1991-07-11 Venturi Applications, Inc. Profil d'aile ameliore par un venturi
EP2031243A1 (fr) * 2007-08-31 2009-03-04 Lm Glasfiber A/S Moyens pour le maintien d'un flux fixe à l'extérieur d'un élément de contrôle de flux
WO2009026928A3 (fr) * 2007-08-31 2009-09-17 Lm Glasfiber A/S Pale d'éolienne équipée de moyens de commande de couche limite submergés
US8579594B2 (en) 2007-08-31 2013-11-12 Lm Glasfiber A/S Wind turbine blade with submerged boundary layer control means
US8573542B2 (en) 2009-08-26 2013-11-05 Airbus Operations Limited Aerofoil slot blowing
WO2018158634A1 (fr) * 2017-02-28 2018-09-07 Steering Financial Ltd. Système de levage aérodynamique
FR3132543A1 (fr) * 2022-02-07 2023-08-11 Safran Nacelles Aéronef comprenant au moins un dispositif de propulsion fluidique intégré à un élément de la cellule et procédé d’utilisation

Also Published As

Publication number Publication date
EP0319574A1 (fr) 1989-06-14
KR890701417A (ko) 1989-12-20
AU2325988A (en) 1989-01-19
BR8807113A (pt) 1989-10-17
JPH02501213A (ja) 1990-04-26
EP0319574A4 (en) 1990-09-05

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