WO1996020867A1 - Tuyere a commande fluidique d'orientation du vecteur poussee - Google Patents

Tuyere a commande fluidique d'orientation du vecteur poussee Download PDF

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Publication number
WO1996020867A1
WO1996020867A1 PCT/US1995/016135 US9516135W WO9620867A1 WO 1996020867 A1 WO1996020867 A1 WO 1996020867A1 US 9516135 W US9516135 W US 9516135W WO 9620867 A1 WO9620867 A1 WO 9620867A1
Authority
WO
WIPO (PCT)
Prior art keywords
control
exhaust
fluidic control
exhaust stream
nozzle
Prior art date
Application number
PCT/US1995/016135
Other languages
English (en)
Inventor
Barry L. Gilbert
Original Assignee
Grumman Aerospace Corporation
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 Grumman Aerospace Corporation filed Critical Grumman Aerospace Corporation
Priority to EP95943760A priority Critical patent/EP0796196A4/fr
Publication of WO1996020867A1 publication Critical patent/WO1996020867A1/fr

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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H25/00—Steering; Slowing-down otherwise than by use of propulsive elements; Dynamic anchoring, i.e. positioning vessels by means of main or auxiliary propulsive elements
    • B63H25/46—Steering or dynamic anchoring by jets or by rudders carrying jets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • F05D2270/173—Purpose of the control system to control boundary layer by the Coanda effect

Definitions

  • the present invention relates to exhaust thrust vectoring for aircraft and, more particularly, pertains to the fluidic control of pitch/yaw thrust vectoring of the jet engine exhaust.
  • Future aircraft will be required to possess the capability of being able to vector the thrust of their jet engines for the attainment of the improved attitude control.
  • a primary need which must be met is to improve the aircraft maneuverability via simultaneous pitch/yaw thrust vectoring of the engine exhaust.
  • a specific application of thrust vectoring is already being used to provide aircraft with Short Ta e-Off and Landing (STOL) characteristics.
  • An improvement in thrust vectoring technology has the potential of improving (shortening) the take-off requirements of conventional aircraft.
  • the greatest potential benefit of thrust vectoring resides in the development of future generations of attack and fighter aircraft, with increased emphasis being placed on stealth characteristics.
  • Such aircraft have increased requirements for low weight, reduced optical signatures and high maneuverability at low to moderate speeds in order to ensure their survival.
  • Thrust vectoring may be substituted for stability and aerodynamic control surfaces for reasons of low observability, with additional benefits derived through a decrease in mechanical complexities and structure, cost and savings in weight. 6
  • U.S. Patent No. 2,763,984 relates to a tangential injection system where the injection is implemented upstream into the flow in order to control the cross-section of the discharge nozzle. Consequently, this system is not a vectoring system.
  • U.S. Patent No. 2,793,493 illustrates a device for deflecting fluid jets without any discussion of offsets and curve type of the deflection or Coanda surface, or the positioning of the injection jet.
  • U.S. Patent No. 2,812,636 discloses a tangential injection system with injection into the boundary layer and not therethrough.
  • U.S. Patent No. 3,016,699 shows a modification of a normal injection system for a rectangular nozzle. Vectoring is controlled by jet injection angle to primary flow and not by strength.
  • U.S. Patent No. 3,740,003 pertains to a bistable fluid amplifier for a missile application. Reaction control jets are not fluid obstacles and no Coanda type surface is shown.
  • U.S. Patent No. 3,795,367 discloses an ejector which uses Coanda wall jet flow to induce a small additional amount of low energy flow through the device by entrainment.
  • U.S. Patent No. 4,069,977 discloses a system using injected flow through the boundary layer to separate the primary flow from the Coanda surface. Control is the reverse of the present invention and injection is on the same side as the deflection.
  • the present invention relates to a fluidic control thrust vectoring system that does not require any movable mechanical parts and which provides control of the exhaust thrust vector without significant weight, volume and cost increase.
  • the fluidic control thrust vectoring system of the present invention operates efficiently, effectively and reliably.
  • the system of the present invention is survivable to electrical power surges and electromagnetic interference.
  • the present invention further relates to a fluidic control thrust vectoring system capable of performing in an adverse environment that includes environmental insensitivity to radiation, temperature, shock and vibration.
  • the present invention is directed to a fluidic control thrust vectoring exhaust nozzle connected to an engine discharging an exhaust stream, the exhaust stream having a thrust vector direction
  • the fluidic control nozzle comprising: an exhaust nozzle having an input end connected to the engine, a spaced output end for discharging the exhaust stream, an enclosed cavity connecting said input end to said output end, and a Coanda surface connected to said output end, said Coanda surface extending from said output end; and at least one fluidic control injector having an input connected to a control gas source, and an output disposed near said output of said exhaust nozzle and being in communication with said enclosed cavity of said exhaust nozzle, said control injector selectively altering the exhaust stream thrust vector direction by injecting a control gas into said exhaust stream via said enclosed cavity.
  • the present invention is further directed to a fluidic control thrust vectoring nozzle comprising: an exhaust nozzle having an input end connected to an engine, a spaced output end for discharging an exhaust stream from the engine, and an enclosed cavity connecting said input end to said output end, said exhaust stream having a thrust vector direction, said output end having a Coanda surface; at least one fluidic control injector having an input connected to a control gas source, and an output disposed near said output of said exhaust nozzle and being in communication with said enclosed cavity of said exhaust nozzle, said fluidic control injector selectively altering the exhaust stream thrust vector direction by injecting a control gas into said exhaust stream via said enclosed cavity, said injection of control gas causing said exhaust stream to adhere to the Coanda surface at the output end of said exhaust nozzle.
  • Figure la is a schematic diagram of a normal jet exhaust through from a jet engine
  • Figure lb is a schematic diagram of the controlled jet flow of the fluidic control thrust vectoring nozzle of the invention.
  • FIG. 2 is a block diagram of an entire fluidic control system of the invention
  • Figure 3a is an embodiment of a boundary layer fluidic control thrust vectoring system of the invention
  • Figure 3b is a schematic diagram of the various separation points of the boundary layer control system of Figure 3a;
  • Figures 4a and 4b show two views of a rectangular cross-section exhaust nozzle with multi- axis deflectors
  • Figures 5a and 5b show two views of an elliptical cross-section exhaust nozzle with multiple injectors
  • Figures 6a and 6b, respectively, are schematic diagrams of exhaust nozzles with symmetric Coanda surfaces
  • Figure 6c is a schematic diagram of an exhaust nozzle with straight Coanda surfaces on one side of the nozzle
  • Figure 7 is a schematic diagram of an exhaust nozzle with asymmetric Coanda surfaces
  • Figure 8 is a schematic diagram of an exhaust nozzle with a tangential injection
  • Figures 9 and 10 are graphical representations of the offset versus the deflection angle due to the Coanda surfaces.
  • Figure la shows a normal exhaust jet 14 as it exits the exhaust nozzle 12.
  • the exhaust nozzle 12 is connected to the engine 16 and has Coanda surfaces 20 and 22 at the exit portion thereof.
  • a pair of fluidic control injectors 18a and 18b are disposed opposite each other and extend perpendicular to the normal exhaust flow near the exit portion of exhaust nozzle 12.
  • Figure lb shows the flow of a controlled exhaust jet 24 when fluidic control gas 26 is injected through control injector 18b.
  • Control injector 18a would be the control for diverting the exhaust flow to the opposite Coanda surface 22.
  • Figure 2 shows a fluidic control bypass 26 connected to the engine 16 at one side and to control injector 18b at the other side. Fluidic control bypass 26 receives the fluidic control gas 27 and uses a diverted engine exhaust flow to inject the control gas 27 into the nozzle 12.
  • Figures 3a and 3b show another manifestation of this invention. They show a boundary layer control system 30 of the present invention where the control injector 34 injects the secondary fluid tangent to and along the Coanda surface 32.
  • the amount and strength of the injection fluid from control injector 34 can control the separation point of the exhaust flow.
  • Exhaust flows 36a, 36b and 36c show examples of different separation points from the Coanda surface 32. A stronger injection will cause the flow to travel farther along the Coanda surface and separate later, as shown by flow 36a, whereas a weaker injection will cause the flow to travel less along the Coanda surface and separate sooner therefrom, as shown in flow 36c.
  • the shape of the exhaust nozzle is preferably rectangular but may be any shape of suitable known type.
  • Figures 4a and 4b shown a rectangular exhaust nozzle 40 with control injector slots 42a and 42b for injecting fluidic control gas into the exhaust flow.
  • Figures 5a and 5b show an embodiment of an elliptical exhaust nozzle 50 with control injector slots 52a and 52b.
  • Figures 6a-6c shown the normal injection embodiment of the invention with the output of injector 62 perpendicular to the exhaust flow and symmetrical offsets of the Coanda surfaces.
  • Figure 6b shows Coanda surfaces 66a and 66b symmetrically offset from exhaust nozzle 60. Offset 67 is the distance of the Coanda surface from exhaust nozzle 60. This step or offset 67 on the Coanda surface side of the nozzle creates a trapped vortex that assists the coanda flow formation.
  • Figure 6c shows an alternative embodiment with different configurations of Coanda surfaces as shown by dotted lines 65 and 69.
  • Curved Coanda surfaces have been tested and proven to be most efficient because straight wall Coanda surfaces limit the maximum angle to the physical angle at which they are mounted to the exhaust nozzle.
  • Figure 7 shows an example of asymmetric offsets of the control Coanda surfaces 72a and 72b with respect to the exhaust nozzle 70.
  • the backward facing offset step 73 assists in the Coanda flow formation along Coanda surface 72b.
  • a trapped vortex flow results from the primary flow over the backward facing step. As in the case of the normal fluidic injection, the result is a fluid obstacle that separates the primary flow from the wall.
  • the injection of the fluidic control gas tangent to the axial exhaust stream causes the exhaust flow stream from nozzle 80 to attach to Coanda surface 82b.
  • the injected wall jet from injector 84 produces a low pressure region that deflects the primary jet by suction. Once the primary jet is deflected, it remains attached to the Coanda surface 82b as in the normal injection flow. Because the injection is along the Coanda wall, a backward facing step offset 85 is mandatory. The low pressure created by the presence of the vortex behind the backward facing step 85 is lost, because the vortex is washed away by the injection flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ocean & Marine Engineering (AREA)
  • Exhaust Silencers (AREA)

Abstract

Une tuyère à commande fluidique d'orientation du vecteur poussée comprend un injecteur de commande fluidique (18a, 18b) en communication avec le jet d'échappement d'un moteur (16) et des surfaces à effet Coanda (20, 22) montées à la sortie de la tuyère d'échappement. En injectant un gaz de commande fluidique (26) dans le jet d'échappement (24), on modifie l'orientation du vecteur poussée du jet d'échappement (24).
PCT/US1995/016135 1994-12-30 1995-12-13 Tuyere a commande fluidique d'orientation du vecteur poussee WO1996020867A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP95943760A EP0796196A4 (fr) 1994-12-30 1995-12-13 Tuyere a commande fluidique d'orientation du vecteur poussee

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US36682194A 1994-12-30 1994-12-30
US08/366,821 1994-12-30

Publications (1)

Publication Number Publication Date
WO1996020867A1 true WO1996020867A1 (fr) 1996-07-11

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Family Applications (1)

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Country Status (2)

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EP (1) EP0796196A4 (fr)
WO (1) WO1996020867A1 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2750168A1 (fr) * 1996-06-24 1997-12-26 Short Brothers Plc Unite de propulsion pour avion, comportant un dispositif d'inversion de poussee
FR2847617A1 (fr) * 2002-11-13 2004-05-28 Gen Electric Actionnement fluidique pour des performances de diffuseur ameliorees.
WO2006049568A1 (fr) * 2004-11-05 2006-05-11 Volvo Aero Corporation Tuyere d'ejection de reacteur, avion ainsi equipe, et procede de commande du flux de gaz en sortie de moteur
WO2010001147A1 (fr) * 2008-07-04 2010-01-07 Bae Systems Plc Appareil d'orientation de poussée pour moteur à réaction, moteur à réaction correspondant, procédé d'orientation de poussée et procédé de mise à niveau pour un moteur à réaction
EP2163754A1 (fr) 2008-09-16 2010-03-17 BAE Systems PLC Dispositif de vectorisation pour un moteur à réaction, moteur à réaction associé, procédé de vectorisation et d'équipement d'un moteur à réaction
CN102991669A (zh) * 2012-12-12 2013-03-27 北京理工大学 一种飞行器射流推力矢量控制系统
KR101784349B1 (ko) 2016-01-29 2017-10-11 한국항공대학교산학협력단 On/off 밸브를 이용한 추력편향 제어 장치
US10207812B2 (en) 2015-09-02 2019-02-19 Jetoptera, Inc. Fluidic propulsive system and thrust and lift generator for aerial vehicles
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
JP2019196099A (ja) * 2018-05-10 2019-11-14 株式会社Ｓｕｂａｒｕ 航空機
USD868627S1 (en) 2018-04-27 2019-12-03 Jetoptera, Inc. Flying car
US10953829B2 (en) 2018-04-27 2021-03-23 Subaru Corporation Occupant protection device
US11491951B2 (en) 2018-04-27 2022-11-08 Subaru Corporation Occupant protection device

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
JP7155174B2 (ja) 2017-06-27 2022-10-18 ジェトプテラ、インコーポレイテッド 航空機の垂直離着陸システムの構成

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US2052869A (en) * 1934-10-08 1936-09-01 Coanda Henri Device for deflecting a stream of elastic fluid projected into an elastic fluid
US2702986A (en) 1948-08-11 1955-03-01 Snecma Device for deflecting a fluid from its normal direction of flow
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US2052869A (en) * 1934-10-08 1936-09-01 Coanda Henri Device for deflecting a stream of elastic fluid projected into an elastic fluid
US2702986A (en) 1948-08-11 1955-03-01 Snecma Device for deflecting a fluid from its normal direction of flow
US2793493A (en) 1950-04-28 1957-05-28 Snecma Devices for deflecting fluid jets
US2812636A (en) 1950-06-16 1957-11-12 Snecma Process and device for deflecting jets
US3016699A (en) 1952-10-10 1962-01-16 Snecma Aerodynamically acting jet deflecting device
US2763984A (en) 1954-09-17 1956-09-25 Snecma Device for regulating the effective cross-section of a discharge-nozzle
US3036430A (en) * 1958-06-19 1962-05-29 Snecma Jet control apparatus
US3759039A (en) * 1968-11-22 1973-09-18 Thiokol Chemical Corp Thrust control and modulation system
US3819117A (en) * 1970-05-25 1974-06-25 Martin Marietta Corp Thrust vector {13 {11 jet interaction vehicle control system
US3740003A (en) 1972-03-13 1973-06-19 Us Army Secondary injection/jet reaction control
US3795367A (en) 1973-04-05 1974-03-05 Src Lab Fluid device using coanda effect
US4069977A (en) 1976-05-11 1978-01-24 The United States Of America As Represented By The Secretary Of The Air Force Jet engine tail pipe flow deflector
US4448354A (en) * 1982-07-23 1984-05-15 The United States Of America As Represented By The Secretary Of The Air Force Axisymmetric thrust augmenting ejector with discrete primary air slot nozzles

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See also references of EP0796196A4 *

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6151883A (en) * 1996-06-24 2000-11-28 Short Brothers Plc Aircraft propulsive power unit thrust reverser with separation delay means
FR2750168A1 (fr) * 1996-06-24 1997-12-26 Short Brothers Plc Unite de propulsion pour avion, comportant un dispositif d'inversion de poussee
FR2847617A1 (fr) * 2002-11-13 2004-05-28 Gen Electric Actionnement fluidique pour des performances de diffuseur ameliorees.
US8327617B2 (en) 2004-11-05 2012-12-11 Volvo Aero Corporation Outlet nozzle for a jet engine, an aircraft comprising the outlet nozzle and a method for controlling a gas flow from the jet engine
WO2006049568A1 (fr) * 2004-11-05 2006-05-11 Volvo Aero Corporation Tuyere d'ejection de reacteur, avion ainsi equipe, et procede de commande du flux de gaz en sortie de moteur
EP1809888A1 (fr) * 2004-11-05 2007-07-25 Volvo Aero Corporation Tuyere d'ejection de reacteur, avion ainsi equipe, et procede de commande du flux de gaz en sortie de moteur
EP1809888A4 (fr) * 2004-11-05 2013-05-15 Volvo Aero Corp Tuyere d'ejection de reacteur, avion ainsi equipe, et procede de commande du flux de gaz en sortie de moteur
WO2010001147A1 (fr) * 2008-07-04 2010-01-07 Bae Systems Plc Appareil d'orientation de poussée pour moteur à réaction, moteur à réaction correspondant, procédé d'orientation de poussée et procédé de mise à niveau pour un moteur à réaction
AU2009265340B2 (en) * 2008-07-04 2012-09-06 Bae Systems Plc Thrust vectoring apparatus for a jet engine, corresponding jet engine, thrust vectoring method and upgrading method for a jet engine
US8887484B2 (en) 2008-07-04 2014-11-18 Bae Systems Plc Thrust vectoring apparatus for a jet engine, corresponding jet engine, thrust vectoring method and upgrading method for a jet engine
EP2163754A1 (fr) 2008-09-16 2010-03-17 BAE Systems PLC Dispositif de vectorisation pour un moteur à réaction, moteur à réaction associé, procédé de vectorisation et d'équipement d'un moteur à réaction
CN102991669A (zh) * 2012-12-12 2013-03-27 北京理工大学 一种飞行器射流推力矢量控制系统
US10207812B2 (en) 2015-09-02 2019-02-19 Jetoptera, Inc. Fluidic propulsive system and thrust and lift generator for aerial vehicles
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10800538B2 (en) 2015-09-02 2020-10-13 Jetoptera, Inc. Ejector and airfoil configurations
KR101784349B1 (ko) 2016-01-29 2017-10-11 한국항공대학교산학협력단 On/off 밸브를 이용한 추력편향 제어 장치
USD868627S1 (en) 2018-04-27 2019-12-03 Jetoptera, Inc. Flying car
US10953829B2 (en) 2018-04-27 2021-03-23 Subaru Corporation Occupant protection device
US11491951B2 (en) 2018-04-27 2022-11-08 Subaru Corporation Occupant protection device
JP2019196099A (ja) * 2018-05-10 2019-11-14 株式会社Ｓｕｂａｒｕ 航空機

Also Published As

Publication number Publication date
EP0796196A1 (fr) 1997-09-24
EP0796196A4 (fr) 1998-04-01

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