US3670994A - Variable deflection thrusters for jets - Google Patents

Variable deflection thrusters for jets Download PDF

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Publication number
US3670994A
US3670994A US63369A US3670994DA US3670994A US 3670994 A US3670994 A US 3670994A US 63369 A US63369 A US 63369A US 3670994D A US3670994D A US 3670994DA US 3670994 A US3670994 A US 3670994A
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jet
airfoil
centerbody
trailing edge
apertures
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US63369A
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Apostolos P Kizilos
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US Department of Navy
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US Department of Navy
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/38—Jet flaps

Definitions

  • VDT variable deflection thruster
  • the basic variable deflection thruster (VDT) concept is disclosed by Davidson US. Pat. No. 3,062,483 and comprises a curved two-dimensional surface and two nozzles for directing fluid streams tangent to the surface.
  • the streams attach to the surface due to the Coanda efiect, and flow around the surface to impinge on each other to form one stream which then exits from the surface in a direction determined by the relative momenta of the original two streams.
  • the net effect is a fluid stream whose direction and strength can be varied by fluid means without the use of mechanical swivels, etc..
  • Attachment also called the Coanda effect, is essential for the operation of the VDT, and was first described by Coanda in US. Pat. No. 2,052,869. It depends upon entrainment of flow along the jet, depletion of the ambient fluid between the jet and the attachment wall, and subsequent pressure differential across the jet which is directly responsible for the attachment.
  • FIG. 1 shows a conventional VDT design.
  • FIG. 2 shows pressure ratio vs. nozzle and VDT dimensions.
  • FIG. 3 shows a preferred embodiment of the invention using a biconvex VDT center body.
  • FIG. 4 shows a straight edge VDT center body.
  • the conventional VDT basic configuration shown in FIG. 1 consists of a cylindrical surface on which two jets, issuing from diametrically opposed spanwise-extending discharge apertures or nozzles 11 and 12, attach.
  • the two jets meet on the surface of cylinder 10 at a position determined by their pressure difference.
  • the jets subsequently form a single combined jet 14 which leaves cylinder surface 10 at some predetermined angle.
  • the exiting angle of the combined jet 14 changes as a result of the bending imposed by the unequal static pressures of the two half-jets.
  • a biconvex VDT can be used as shown in FIG. 3 to support a higher pressure ratio jet from apertures 11 and 12 than would be otherwise possible.
  • This biconvex centerbody 16 forms a sharp trailing edge which overcomes the stream detachment occurring with a cylindrical VDT at high mach numbers and high pressure ratios.
  • the biconvex VDT 16 is attached to plate 18 that separates the two plenum chambers within the airfoil 15, from which the high pressure jets are supplied. Jet pressure supply is provided to the plenum chambers on either side of plate 18. Jet pressure supplies 20 and 21 are controlled to vary the flow of the jet streams from apertures 11 and 12 relative to each other.
  • a variable deflection thruster center body 17 having two flat sides 19 which intersect to form a wedge can also be used to solve the stream detachment problems encountered with the conventional circular VDT surface.
  • the attached jets do not operate on the Coanda effect but rather follow the straight edges of the center body 17.
  • the straight walls 19 of this embodiment shown in FIG. 4 are a limiting case of increasing the radius of curvature until a straight line is approached.
  • the two jets of the straight edge VDT flow along the walls to meet with a pure momentum interchange type of stream interaction.
  • the Coanda effect is not present when a jet is flowing along side a flat surface.
  • Either a curved surface, or a recess or offset" such as is employed in the nozzle and interaction region of a fluid amplifier, is necessary for the Coanda effect. That is, there must be a bubble from which depletion of fluid occurs so as to generate a pressure differential.
  • the Coanda effect is not present, and operation of the invention depends upon stream interaction, also known as momentum interchange.
  • momentum interchange In conventional curved surface VDTs both the Coanda effect and the momentum interchange effects are utilized.
  • Both the biconvex design of FIG. 3 and straight edge design of FIG. 4 form a sharp wedge where the sides come together eliminating problems encountered with a conventional circular VDT surface.
  • the biconvex VDT device has good lift-production capability up to mach number 0.5.
  • the VDT configuration with straight surfaces (FIG. 4) can eliminate jet detachment problems at high transonic and supersonic speeds.
  • An improved variable deflection thruster at the rearward end of an airfoil for use at high subsonic speeds without jet detachment comprising:
  • said rearward sharp trailing edge being formed from one side edge of a biconvex centerbody
  • each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the surfaces of said biconvex centerbody
  • first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another.
  • An improved variable deflection thruster at the rearward end of an airfoil for use at high transonic and supersonic speeds without jet detachment comprising:
  • said rearward wedge shaped trailing edge being formed by a variable deflection thruster centerbody having two flat sides which intersect to fonn a wedge,
  • first and second spanwise-extending jet discharge apertures in said airfoil one said jet discharge aperture being on each side of said variable deflection thruster centerbody having two flat sides which intersect to form said wedge shaped trailing edge
  • each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the flat surfaces of said variable deflection thruster centerbody
  • first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second et discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Variable deflection thrusters center body of improved design for jets for overcoming stream detachment at high mach numbers and high pressure ratios.

Description

United States Patent Kizilos [4 1' June 20, 1972 [54] VARIABLE DEFLECTION THRUSTERS [56] References Cited F R TS 0 JE UNITED STATES PATENTS 1 A t l P. K M t M' [72] Invent 3,467,043 9/1969 Bowles ..244/42 cc x [73] Assignee: The United States of America as represented y Secremly y Primary Evaminer-Milton Buchler Assistant E.\'aminerCarl A. Rutledge F l A l 1970 [22] l ed ug 3 Attorney-R. S. Sclasma and J. M. St. Amand [2!] App]. N0.: 63,369
[57] ABSTRACT [52] US. Cl ..244/42 CC V i bl d fl tio thru ters center body of improved design 1 Int. Cl. t for jets for overcoming tream detachment at mach num. [58] Field of Search ..244/42 R, 42 CD, 42 CC, 42 C, bers and high pressure ratioi PLENUM CHAMBER PLENUM CHAMBER 2 Claims, 4 Drawing Figures CYLINDER SURFACE COMPOSITE JET WlNG PATEf-HEDJUHZO m2 3, 670,994
CYLINDER SURFACE .2
PLENUM CHAMBER DETACHED PLENUM CHAMBER COMPOSITE JET wme FIG PRESSURE RATIO FIG.2
{ JET PRESSURE SUPPLY AND CONTROL COMPOSITE JET t JET PRESSURE SUPPLY AND CONTROL STRAIGHT EDGES APOSTOLOS R KIZTLOS INVEN R.
ATTORNEY VARIABLE DEFLECTION TIIRUSTERS FOR JETS The invention herein described may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
The basic variable deflection thruster (VDT) concept is disclosed by Davidson US. Pat. No. 3,062,483 and comprises a curved two-dimensional surface and two nozzles for directing fluid streams tangent to the surface. The streams attach to the surface due to the Coanda efiect, and flow around the surface to impinge on each other to form one stream which then exits from the surface in a direction determined by the relative momenta of the original two streams. The net effect is a fluid stream whose direction and strength can be varied by fluid means without the use of mechanical swivels, etc.. Attachment, also called the Coanda effect, is essential for the operation of the VDT, and was first described by Coanda in US. Pat. No. 2,052,869. It depends upon entrainment of flow along the jet, depletion of the ambient fluid between the jet and the attachment wall, and subsequent pressure differential across the jet which is directly responsible for the attachment.
However, when the momentum of the jet is too great and the radius of curvature too small, the stream will not attach, but will flow straight past the curved surface. It is this problem which is encountered with conventional VDTs using circular cross-sectioned surfaces shown in FIG. 1. The present invention overcomes this problem with the biconvex VDT and straight edge VDT disclosed herein. A VDT surface shaped like a football cross-section has been found to overcome stream detachment at high mach numbers and high pressure ratios.
Other objects and many of the attendant advantages of this invention will become readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
FIG. 1 shows a conventional VDT design.
FIG. 2 shows pressure ratio vs. nozzle and VDT dimensions.
FIG. 3 shows a preferred embodiment of the invention using a biconvex VDT center body.
FIG. 4 shows a straight edge VDT center body.
The conventional VDT basic configuration shown in FIG. 1 consists of a cylindrical surface on which two jets, issuing from diametrically opposed spanwise-extending discharge apertures or nozzles 11 and 12, attach. The two jets meet on the surface of cylinder 10 at a position determined by their pressure difference. The jets subsequently form a single combined jet 14 which leaves cylinder surface 10 at some predetermined angle. The exiting angle of the combined jet 14 changes as a result of the bending imposed by the unequal static pressures of the two half-jets.
It is essential in the operation of this VDT configuration (which allows maximum jet deflection) that the two half-jets remain attached to the cylinder surface. Each one of these jets clings to the cylinder surface 10 by virtue of the Coanda effect. The limits of jet attachment are determined by the jet pressure and the geometry of the configuration. Large slots or nozzles, large pressures, and small-diameter Coanda cylinders tend to cause jet detachment.
Because of the importance of jet detachment upon VDT operation, tests were undertaken to determine the flow and geometrical parameters which control the detachment of a single Coanda jet. The VDT jet detaches when for a given geometry the pressure ratio of the jets is increased beyond a given value, thus spoiling the VDT effect. For a fixed nozzle width b", the greater the radius a of cylinder 10 the higher the pressure ratio that the jet can support before it detaches, see FIG. 2.
When the thickness t" of an airfoil 15 is limited it has been found that a biconvex VDT can be used as shown in FIG. 3 to support a higher pressure ratio jet from apertures 11 and 12 than would be otherwise possible. This biconvex centerbody 16 forms a sharp trailing edge which overcomes the stream detachment occurring with a cylindrical VDT at high mach numbers and high pressure ratios. The biconvex VDT 16 is attached to plate 18 that separates the two plenum chambers within the airfoil 15, from which the high pressure jets are supplied. Jet pressure supply is provided to the plenum chambers on either side of plate 18. Jet pressure supplies 20 and 21 are controlled to vary the flow of the jet streams from apertures 11 and 12 relative to each other.
A variable deflection thruster center body 17 having two flat sides 19 which intersect to form a wedge can also be used to solve the stream detachment problems encountered with the conventional circular VDT surface. The attached jets do not operate on the Coanda effect but rather follow the straight edges of the center body 17. The straight walls 19 of this embodiment shown in FIG. 4 are a limiting case of increasing the radius of curvature until a straight line is approached. The two jets of the straight edge VDT flow along the walls to meet with a pure momentum interchange type of stream interaction.
The Coanda effect is not present when a jet is flowing along side a flat surface. Either a curved surface, or a recess or offset" such as is employed in the nozzle and interaction region of a fluid amplifier, is necessary for the Coanda effect. That is, there must be a bubble from which depletion of fluid occurs so as to generate a pressure differential. In the embodiment of FIG. 4, the Coanda effect is not present, and operation of the invention depends upon stream interaction, also known as momentum interchange. In conventional curved surface VDTs both the Coanda effect and the momentum interchange effects are utilized. Both the biconvex design of FIG. 3 and straight edge design of FIG. 4 form a sharp wedge where the sides come together eliminating problems encountered with a conventional circular VDT surface.
The biconvex VDT device has good lift-production capability up to mach number 0.5. The VDT configuration with straight surfaces (FIG. 4) can eliminate jet detachment problems at high transonic and supersonic speeds.
What is claimed is:
1. An improved variable deflection thruster at the rearward end of an airfoil for use at high subsonic speeds without jet detachment, comprising:
a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a sharp trailing edge,
b. said rearward sharp trailing edge being formed from one side edge of a biconvex centerbody,
c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said biconvex centerbody which forms said trailing edge,
d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the surfaces of said biconvex centerbody,
e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another.
2. An improved variable deflection thruster at the rearward end of an airfoil for use at high transonic and supersonic speeds without jet detachment, comprising:
a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a wedge shaped trailing edge,
. said rearward wedge shaped trailing edge being formed by a variable deflection thruster centerbody having two flat sides which intersect to fonn a wedge,
c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said variable deflection thruster centerbody having two flat sides which intersect to form said wedge shaped trailing edge,
. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the flat surfaces of said variable deflection thruster centerbody,
e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second et discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another. 5

Claims (2)

1. An improved variable deflection thruster at the rearward end of an airfoil for use at high subsonic speeds without jet detachment, comprising: a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a sharp trailing edge, b. said rearward sharp trailing edge being formed from one side edge of a biconvex centerbody, c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said biconvex centerbody which forms said trailing edge, d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the surfaces of said biconvex centerbody, e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streAms discharged from said apertures relative to one another.
2. An improved variable deflection thruster at the rearward end of an airfoil for use at high transonic and supersonic speeds without jet detachment, comprising: a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a wedge shaped trailing edge, b. said rearward wedge shaped trailing edge being formed by a variable deflection thruster centerbody having two flat sides which intersect to form a wedge, c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said variable deflection thruster centerbody having two flat sides which intersect to form said wedge shaped trailing edge, d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the flat surfaces of said variable deflection thruster centerbody, e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another.
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Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4398687A (en) * 1981-02-25 1983-08-16 The United States Of America As Represented By The Secretary Of The Navy Thrust deflector and force augmentor
US4457480A (en) * 1981-02-25 1984-07-03 The United States Of America As Represented By The Secretary Of The Navy Mono-element combined supercritical high lift airfoil
US4463920A (en) * 1981-02-25 1984-08-07 The United States Of America As Represented By The Secretary Of The Navy Thrust deflector and force augmentor
US4555079A (en) * 1983-12-28 1985-11-26 The United States Of America As Represented By The Secretary Of The Air Force Multiple jet blowing around the blunt trailing edge of a circulation controlled airfoil
US4711414A (en) * 1986-03-31 1987-12-08 The Boeing Company Projectile with integrated propulsion system
US5529458A (en) * 1993-08-19 1996-06-25 Westland Helicopters Limited Circulation control aerofoils
US5863090A (en) * 1995-07-17 1999-01-26 Georgia Tech Research Corporation Pneumatic aerodynamic force-augmentation, control and drag-reduction devices for racing cars and high-performance sports cars
US5908217A (en) * 1995-07-17 1999-06-01 Georgia Tech Research Corporation Pneumatic aerodynamic control and drag-reduction system for ground vehicles
US7290738B1 (en) * 2004-10-28 2007-11-06 The United States Of America As Represented By The Secretary Of The Navy Dual jet emerging lift augmentation system for airfoils and hydrofoils
WO2008029095A1 (en) 2006-09-06 2008-03-13 Bae System Plc Flow control actuators
US8827212B1 (en) * 2012-06-18 2014-09-09 The Boeing Company Method and apparatus for supplying a gas jet over an aerodynamic structure
CN109850128A (en) * 2019-04-12 2019-06-07 西华大学 Multi-stage blowing circulation volume high-lift device and aircraft
US11142302B1 (en) 2020-03-28 2021-10-12 Textron Innovations Inc. Fluidic split flap systems for yaw control in forward flight

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3467043A (en) * 1966-11-18 1969-09-16 Bowles Eng Corp Pure fluid force generator

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3467043A (en) * 1966-11-18 1969-09-16 Bowles Eng Corp Pure fluid force generator

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4398687A (en) * 1981-02-25 1983-08-16 The United States Of America As Represented By The Secretary Of The Navy Thrust deflector and force augmentor
US4457480A (en) * 1981-02-25 1984-07-03 The United States Of America As Represented By The Secretary Of The Navy Mono-element combined supercritical high lift airfoil
US4463920A (en) * 1981-02-25 1984-08-07 The United States Of America As Represented By The Secretary Of The Navy Thrust deflector and force augmentor
US4555079A (en) * 1983-12-28 1985-11-26 The United States Of America As Represented By The Secretary Of The Air Force Multiple jet blowing around the blunt trailing edge of a circulation controlled airfoil
US4711414A (en) * 1986-03-31 1987-12-08 The Boeing Company Projectile with integrated propulsion system
US5529458A (en) * 1993-08-19 1996-06-25 Westland Helicopters Limited Circulation control aerofoils
US5863090A (en) * 1995-07-17 1999-01-26 Georgia Tech Research Corporation Pneumatic aerodynamic force-augmentation, control and drag-reduction devices for racing cars and high-performance sports cars
US5908217A (en) * 1995-07-17 1999-06-01 Georgia Tech Research Corporation Pneumatic aerodynamic control and drag-reduction system for ground vehicles
US7290738B1 (en) * 2004-10-28 2007-11-06 The United States Of America As Represented By The Secretary Of The Navy Dual jet emerging lift augmentation system for airfoils and hydrofoils
US7984879B2 (en) * 2006-09-06 2011-07-26 Bae Systems Plc Flow control actuators
US20090050734A1 (en) * 2006-09-06 2009-02-26 Bae Systems Plc Flow control actuators
EP2059441A1 (en) * 2006-09-06 2009-05-20 BAE Systems plc Flow control actuators
WO2008029095A1 (en) 2006-09-06 2008-03-13 Bae System Plc Flow control actuators
US8827212B1 (en) * 2012-06-18 2014-09-09 The Boeing Company Method and apparatus for supplying a gas jet over an aerodynamic structure
CN109850128A (en) * 2019-04-12 2019-06-07 西华大学 Multi-stage blowing circulation volume high-lift device and aircraft
CN109850128B (en) * 2019-04-12 2023-11-24 西华大学 Multistage blowing annular quantity lift-increasing device and aircraft
US11148797B1 (en) 2020-03-28 2021-10-19 Textron Innovations Inc. Low observable aircraft having trinary lift fans
US11167844B2 (en) 2020-03-28 2021-11-09 Textron Innovations Inc. Low observable aircraft having tandem longitudinal lift fans
US11167839B2 (en) 2020-03-28 2021-11-09 Textron Innovations Inc. Fluidic pitch control systems for use in forward flight
US11174020B2 (en) * 2020-03-28 2021-11-16 Textron Innovations Inc. Fluidic roll control systems for use in forward flight
US11180241B2 (en) 2020-03-28 2021-11-23 Textron Innovations Inc. Fluidic roll control systems for use in hover
US11279479B2 (en) 2020-03-28 2022-03-22 Textron Innovations Inc. Fluidic yaw control systems for use in hover
US11325699B2 (en) 2020-03-28 2022-05-10 Textron Innovations Inc. Ducted fans having edgewise flow augmentation
US11597510B2 (en) 2020-03-28 2023-03-07 Textron Innovations Inc. Ducted fans having fluidic thrust vectoring
US11142302B1 (en) 2020-03-28 2021-10-12 Textron Innovations Inc. Fluidic split flap systems for yaw control in forward flight

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