US2875578A - Device for controlling the flow direction of a reaction jet issuing from a nozzle - Google Patents

Device for controlling the flow direction of a reaction jet issuing from a nozzle Download PDF

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Publication number
US2875578A
US2875578A US396993A US39699353A US2875578A US 2875578 A US2875578 A US 2875578A US 396993 A US396993 A US 396993A US 39699353 A US39699353 A US 39699353A US 2875578 A US2875578 A US 2875578A
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US
United States
Prior art keywords
nozzle
controlling
jet
slots
flow direction
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Expired - Lifetime
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US396993A
Inventor
Kadosch Marcel
Francois G Paris
Raymond H Marchal
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Safran Aircraft Engines SAS
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SNECMA SAS
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Filing date
Publication date
Priority to GB19539/53A priority Critical patent/GB750622A/en
Priority to GB12829/55A priority patent/GB750687A/en
Priority to GB11054/51A priority patent/GB750601A/en
Priority to CH324032D priority patent/CH324032A/en
Priority claimed from US229772A external-priority patent/US2793494A/en
Application filed by SNECMA SAS filed Critical SNECMA SAS
Priority to US396993A priority patent/US2875578A/en
Application granted granted Critical
Publication of US2875578A publication Critical patent/US2875578A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
    • 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
    • F02K1/32—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 for reversing thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15C—FLUID-CIRCUIT ELEMENTS PREDOMINANTLY USED FOR COMPUTING OR CONTROL PURPOSES
    • F15C1/00—Circuit elements having no moving parts

Definitions

  • Patent No. 2,793,494 dated May 28, 1957. Divided and this application December 8, 1953, Serial No. 396,993
  • the present invention has for its object to provide means for deilecting a reaction jet issuing from a nozzle in an axial direction, Iaway from said axial direction, thus altering the axial component of the thrust and/or producing a steering or a braking action on the jet propelled aircraft.
  • a further object of this invention is to provide means for deecting a reaction jet issuing from a nozzle, in any one of several directions at an angle with the axis of said nozzle.
  • the nozzle is provided with opposed slots extending on the periphery of said nozzle and connected to a source of pressure substantially different from that obtaining in said nozzle, individual valve means being provided for controlling the connection of said source to each slot.
  • Fig. 1 is a diagrammatic axial section through a nozzle according to the invention.
  • Fig. 2 is an end view of this nozzle.
  • the nozzle 1 is formed, at its outlet, with an outwardly curved, convex extension 2 which is provided with opposed slots 3 4, 5 6 forming minor nozzles opening into the main nozzle 1 in a direction substantially perpendicular to the axis of the latter and preferably slightly inclined upstream. These slots extend, along the periphery of the nozzle 1, over arcs of a circle smaller than 90 (in the present example including 4 successive slots located in the same diametrical plane).
  • Each slot is connected both to a source ofizid under pressure (which may be a stage of the air lcompressor if the nozzle belongs to a jet turbine engine) and to a source of depression (which may be suction slots provided on the wings or elsewhere), Of course the overpressure of the former source and the depression of the latter one are relative to the normal pressure obtaining at the outlet of the nozzle 1.
  • a source of vad under pressure which may be a stage of the air lcompressor if the nozzle belongs to a jet turbine engine
  • a source of depression which may be suction slots provided on the wings or elsewhere
  • nozzle 1 Downstream of the outlet of nozzle 1 is mounted a series of spaced successive vanes 7 coaxial with nozzle 1 and forming lateral, annular, curved passages.
  • deflection can be obtained by operating only one of the opposed slots 3 4, i. e. by opening only one of the valves 3a 4b.
  • valves 3b4a are opened, the others remaining closed.
  • lateral deflection is produced by operating slots 5 6 in either of the two ways described.
  • the jet issuing from the nozzle 1 can be bent in any one of 4 directions perpendicular to each other. It can also be bent in the 4 directions bisecting the angles formed by the formed 4 directions in the following way:
  • the device described affords a very efficient and simple steering action.
  • the valves are of course operated by the pilot through any adequate transmission which can be conveniently under the control of the joy-stick.
  • the axial component of the thrust produced by the dellected jet is considerably decreased as compared with that of the non-deflected jet. If the deflection obtained is of about 90, the axial thrust is practically negligible; if this deilection is greater than 90, a lbraking elect will be produced, and the greater the angle of deflection beyond 90, the more powerful the braking effect.
  • the device of the invention can be operated so as to produce such a braking action without any steering eifect.
  • slots 3 4 are both connected to the pressure source, whereas slots 5 6 are both connected to the depression source.
  • the screen-like jets issuing from the opposed slots 3 4 form a kind of diametrical iluid obstacle which divides the main jet into two equal fractions which are laterally deflected, this lateral detlection being furthered by suction of the slots 5 6.
  • the two deected fractions of the jet being symmetrical, there will be no resultant lateral thrust, while the axial thrust will be considerably decreased and even cancelled or inverted (braking action).
  • This operation is carried out without aecting the output of the engine which may operate at normal rate, so that, in case of emergency, full axial thrust can be' had at once by closing all the valves.

Description

March 3, 1.959 M. KADoscH ETAL 2,875,578
DEV-ICE FOR CONTROLLING THE FLOW DIRECTION OF A REACTION JET ISSUING FROM A NOZZLE Original. Filed June 4, 1951 INVENTOR S United States PatentI DEVICE FOR CONTROLLING THE FLOW DIREC- S1111? A REACTION JET ISSUING'FROM A Marcel Kadosch, Paris, Francois G. Paris, Chaville, Jean Bertin, Neuilly-sur-Seine, and Raymond H. Marchal, Paris, France, assignors to Societe Nationale dEtude et de `Construction de Moteurs dAviation, Paris, France, a French company Original application June 4, 1951, Serial No. 229,772,
now Patent No. 2,793,494, dated May 28, 1957. Divided and this application December 8, 1953, Serial No. 396,993
Claims priority, application France June 16, 1950 2 Claims. (Cl. 60 35.54)
This application is a divisional application of our co-pending U. S. patent application Serial No. 229,772, filed June 4, 1951, now Patent No. 2,793,494 issued May 28, 1957. 4
The present invention has for its object to provide means for deilecting a reaction jet issuing from a nozzle in an axial direction, Iaway from said axial direction, thus altering the axial component of the thrust and/or producing a steering or a braking action on the jet propelled aircraft.
A further object of this invention is to provide means for deecting a reaction jet issuing from a nozzle, in any one of several directions at an angle with the axis of said nozzle.
According to the invention, the nozzle is provided with opposed slots extending on the periphery of said nozzle and connected to a source of pressure substantially different from that obtaining in said nozzle, individual valve means being provided for controlling the connection of said source to each slot.
Other objects and advantages of the invention will be apparent during the course of the following description.
In the accompanying drawing in which like reference characters are employed to designate like parts throughout the same,
Fig. 1 is a diagrammatic axial section through a nozzle according to the invention.
Fig. 2 is an end view of this nozzle.
.The nozzle 1 is formed, at its outlet, with an outwardly curved, convex extension 2 which is provided with opposed slots 3 4, 5 6 forming minor nozzles opening into the main nozzle 1 in a direction substantially perpendicular to the axis of the latter and preferably slightly inclined upstream. These slots extend, along the periphery of the nozzle 1, over arcs of a circle smaller than 90 (in the present example including 4 successive slots located in the same diametrical plane).
Each slot is connected both to a source of luid under pressure (which may be a stage of the air lcompressor if the nozzle belongs to a jet turbine engine) and to a source of depression (which may be suction slots provided on the wings or elsewhere), Of course the overpressure of the former source and the depression of the latter one are relative to the normal pressure obtaining at the outlet of the nozzle 1. Each slot is associated with two individual valves 3a 3b, 4a 4b, controlling respectively the connections to the source of pressure and to the source of depression.
Downstream of the outlet of nozzle 1 is mounted a series of spaced successive vanes 7 coaxial with nozzle 1 and forming lateral, annular, curved passages.
The arrangement described operates as follows:
If it is desired to deilect the jet vertically downwards,
2,875,578 y Patented Mar. 3, 1959 the valves 3a and 4b are opened, all the other valves remaining closed. An auxiliary screen-like jet will issue from slot 3 forming a kind of fluid obstacle which urges the main jet issuing from 1 towards the opposite side of the nozzle, i. e. towards the wall portion adjacent the slot 4. This deection is furthered by the sucking action produced by the slot 4. Thus the jet issuing from nozzle 1 is bent downwards and sticks to the curved walls 2 and 7 which, owing to their very curved shape, increase the detlection, so that the jet eventually issuesat au angle with the axis of the nozzle.
Obviously, deflection can be obtained by operating only one of the opposed slots 3 4, i. e. by opening only one of the valves 3a 4b.
Now, an opposite deflection (upwards) will be had if valves 3b4a are opened, the others remaining closed. Similarly lateral deflection is produced by operating slots 5 6 in either of the two ways described.
Therefore, the jet issuing from the nozzle 1 can be bent in any one of 4 directions perpendicular to each other. It can also be bent in the 4 directions bisecting the angles formed by the formed 4 directions in the following way:
Two adjacent slots, say 3 5 are connected to the pressure source,`whereas the opposite adjacent slots 4 6 are connected to the depression source.
Lastly any intermediate deflection can be obtained by adequately proportioning the blowing and/or sucking actions of the corresponding slots.
The device described affords a very efficient and simple steering action. The valves are of course operated by the pilot through any adequate transmission which can be conveniently under the control of the joy-stick.
`ICC
With this device, the conventional control surfaces of` aircraft can be done without, thus allowing considerable reduction in losses through air friction and turbulence, which is particularly important in high-speed flight.
It will be appreciated that the axial component of the thrust produced by the dellected jet is considerably decreased as compared with that of the non-deflected jet. If the deflection obtained is of about 90, the axial thrust is practically negligible; if this deilection is greater than 90, a lbraking elect will be produced, and the greater the angle of deflection beyond 90, the more powerful the braking effect.
Such a reduction in the axial thrust or even braking action are highly desirable in certain cases, e. g., when landing. However in this case, a steering eilect may -be undesirable.
The device of the invention can be operated so as to produce such a braking action without any steering eifect.
For that purpose, the opposed slots willl be similarly operated: for instance, slots 3 4 are both connected to the pressure source, whereas slots 5 6 are both connected to the depression source.
The screen-like jets issuing from the opposed slots 3 4 form a kind of diametrical iluid obstacle which divides the main jet into two equal fractions which are laterally deflected, this lateral detlection being furthered by suction of the slots 5 6. The two deected fractions of the jet being symmetrical, there will be no resultant lateral thrust, while the axial thrust will be considerably decreased and even cancelled or inverted (braking action).
This operation is carried out without aecting the output of the engine which may operate at normal rate, so that, in case of emergency, full axial thrust can be' had at once by closing all the valves.
What we claim is:
1. A device for steering a jet propelled aircraft having a propulsive nozzle opening towards the rear of said aircraft through a circular outlet, said device comprising two ypairs of lopposite"slot-like passages, at 90 with each other, extending lalong the periphery yof said outlet, in a plane perpendicular to the axis of said nozzle, each passage being in the form of an arc of a circle concentric with 'said circular outlet and facing substantially towards th'e 'center thereof, la source yat =a pressure `substantially higher 'than the 'pressure existing at said outlet, another source at a upressure substantially llowerthan the pressure existing at .said outlet, `and controllable means for selectively connecting the opposite passages of either pair respectively to said sources.
.2. kyDevice as claimed in claim l, wherein the slot-like passages of the two ,pairs are respectively vertically and horizontally directed.
4 References Cited in the le of this patent UNITED STATES PATENTS Goddard Mar. 5, Thompson Apr. 8, Price Nov. 8, lWoll Mar. 10, Thwaites June 30, Staui Nov. 23, Kadosch et al Mar. 1, Kadosch et al Sept. 25, Kadosch et a1. May 28,
FOREIGN PATENTS Great Britain Jan. 19,
US396993A 1950-06-16 1953-12-08 Device for controlling the flow direction of a reaction jet issuing from a nozzle Expired - Lifetime US2875578A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
GB19539/53A GB750622A (en) 1950-06-16 1951-05-10 Improvements in or relating to jet propulsion units for aircraft
GB12829/55A GB750687A (en) 1950-06-16 1951-05-10 Improvements in or relating to jet propulsion units for aircraft
GB11054/51A GB750601A (en) 1950-06-16 1951-05-10 Improvements in jet nozzles and jet propulsion units
CH324032D CH324032A (en) 1950-06-16 1951-05-17 Jet thruster
US396993A US2875578A (en) 1950-06-16 1953-12-08 Device for controlling the flow direction of a reaction jet issuing from a nozzle

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR324032X 1950-06-16
US229772A US2793494A (en) 1950-06-16 1951-06-04 Jet nozzles and jet propulsion units provided with means for deviating the jet
US396993A US2875578A (en) 1950-06-16 1953-12-08 Device for controlling the flow direction of a reaction jet issuing from a nozzle

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CH (1) CH324032A (en)
GB (3) GB750687A (en)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2932468A (en) * 1957-12-06 1960-04-12 Gen Electric Vtol aircraft
US2968149A (en) * 1957-04-26 1961-01-17 Chance Vought Aircraft Inc Flight control means
US3020714A (en) * 1956-07-03 1962-02-13 Snecma Device for controlling the jet of a reaction propulsion motor
US3022026A (en) * 1958-04-23 1962-02-20 Power Jets Res & Dev Ltd Air intake for jet sustained aircraft
US3039537A (en) * 1958-06-23 1962-06-19 Bolkow Entwicklungen Kg Propulsive means for aircraft
US3066485A (en) * 1957-12-11 1962-12-04 Bertin & Cie Steering device for rocket-propelled vehicles
US3070957A (en) * 1961-03-16 1963-01-01 Thompson Ramo Wooldridge Inc Liquid separator, vapor-gas injection steering system
US3101591A (en) * 1961-03-28 1963-08-27 Thompson Ramo Wooldridge Inc Vapor-gas injection thrust vector control system
US3122165A (en) * 1960-09-19 1964-02-25 Billy M Horton Fluid-operated system
US3127132A (en) * 1964-03-31 Jet-propelled dirigible airships
US3133413A (en) * 1960-09-12 1964-05-19 United Aircraft Corp Control and cooling of rocket motors
US3144752A (en) * 1961-10-02 1964-08-18 United Aircraft Corp Injection thrust vectoring
US3145531A (en) * 1961-07-28 1964-08-25 Alexander T Deutsch Automatic steering of space craft
US3147590A (en) * 1961-03-16 1964-09-08 Thompson Ramo Wooldridge Inc Reaction motor with nozzle vector control having ablative port means and cooled valve means
US3194512A (en) * 1961-09-06 1965-07-13 Saunders Walter Selden Jet-wing aircraft
US3240254A (en) * 1963-12-23 1966-03-15 Sonic Dev Corp Compressible fluid sonic pressure wave apparatus and method
US3320744A (en) * 1965-11-15 1967-05-23 Sonic Dev Corp Gas turbine engine burner
US4754927A (en) * 1986-12-08 1988-07-05 Colt Industries Inc. Control vanes for thrust vector control nozzle
EP0739291A1 (en) * 1994-01-13 1996-10-30 Bell Helicopter Textron Inc. Engine exhaust gas deflection system

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990905A (en) * 1957-05-13 1961-07-04 Lilley Geoffrey Michael Jet noise suppression means
US2968921A (en) * 1957-12-23 1961-01-24 Ryan Aeronautical Co Aerodynamic jet deflecting nozzle

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB103325A (en) * 1916-01-19 1917-01-19 Robert Owen King Improvements in and relating to Jet Propulsion for Aquatic Vessels.
US2395809A (en) * 1939-12-02 1946-03-05 Daniel And Florence Guggenheim Rocket directing apparatus
US2418488A (en) * 1944-07-29 1947-04-08 Westinghouse Electric Corp Power-plant apparatus
US2487588A (en) * 1943-05-22 1949-11-08 Lockheed Aircraft Corp Variable area propulsive nozzle means for power plants
US2630673A (en) * 1950-09-27 1953-03-10 Gen Electric Cooling means for variable area nozzles
US2643832A (en) * 1949-01-26 1953-06-30 Imp Trust For The Encouragemen Aerodynamic lift-producing device
US2694898A (en) * 1948-08-09 1954-11-23 France Etat Device for deflecting a high-speed jet of gas ejected through a nozzle
US2702986A (en) * 1948-08-11 1955-03-01 Snecma Device for deflecting a fluid from its normal direction of flow
US2763984A (en) * 1954-09-17 1956-09-25 Snecma Device for regulating the effective cross-section of a discharge-nozzle
US2793493A (en) * 1950-04-28 1957-05-28 Snecma Devices for deflecting fluid jets

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB103325A (en) * 1916-01-19 1917-01-19 Robert Owen King Improvements in and relating to Jet Propulsion for Aquatic Vessels.
US2395809A (en) * 1939-12-02 1946-03-05 Daniel And Florence Guggenheim Rocket directing apparatus
US2487588A (en) * 1943-05-22 1949-11-08 Lockheed Aircraft Corp Variable area propulsive nozzle means for power plants
US2418488A (en) * 1944-07-29 1947-04-08 Westinghouse Electric Corp Power-plant apparatus
US2694898A (en) * 1948-08-09 1954-11-23 France Etat Device for deflecting a high-speed jet of gas ejected through a nozzle
US2702986A (en) * 1948-08-11 1955-03-01 Snecma Device for deflecting a fluid from its normal direction of flow
US2643832A (en) * 1949-01-26 1953-06-30 Imp Trust For The Encouragemen Aerodynamic lift-producing device
US2793493A (en) * 1950-04-28 1957-05-28 Snecma Devices for deflecting fluid jets
US2630673A (en) * 1950-09-27 1953-03-10 Gen Electric Cooling means for variable area nozzles
US2763984A (en) * 1954-09-17 1956-09-25 Snecma Device for regulating the effective cross-section of a discharge-nozzle

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3127132A (en) * 1964-03-31 Jet-propelled dirigible airships
US3020714A (en) * 1956-07-03 1962-02-13 Snecma Device for controlling the jet of a reaction propulsion motor
US2968149A (en) * 1957-04-26 1961-01-17 Chance Vought Aircraft Inc Flight control means
US2932468A (en) * 1957-12-06 1960-04-12 Gen Electric Vtol aircraft
US3066485A (en) * 1957-12-11 1962-12-04 Bertin & Cie Steering device for rocket-propelled vehicles
US3022026A (en) * 1958-04-23 1962-02-20 Power Jets Res & Dev Ltd Air intake for jet sustained aircraft
US3039537A (en) * 1958-06-23 1962-06-19 Bolkow Entwicklungen Kg Propulsive means for aircraft
US3133413A (en) * 1960-09-12 1964-05-19 United Aircraft Corp Control and cooling of rocket motors
US3122165A (en) * 1960-09-19 1964-02-25 Billy M Horton Fluid-operated system
US3070957A (en) * 1961-03-16 1963-01-01 Thompson Ramo Wooldridge Inc Liquid separator, vapor-gas injection steering system
US3147590A (en) * 1961-03-16 1964-09-08 Thompson Ramo Wooldridge Inc Reaction motor with nozzle vector control having ablative port means and cooled valve means
US3101591A (en) * 1961-03-28 1963-08-27 Thompson Ramo Wooldridge Inc Vapor-gas injection thrust vector control system
US3145531A (en) * 1961-07-28 1964-08-25 Alexander T Deutsch Automatic steering of space craft
US3194512A (en) * 1961-09-06 1965-07-13 Saunders Walter Selden Jet-wing aircraft
US3144752A (en) * 1961-10-02 1964-08-18 United Aircraft Corp Injection thrust vectoring
US3240254A (en) * 1963-12-23 1966-03-15 Sonic Dev Corp Compressible fluid sonic pressure wave apparatus and method
US3320744A (en) * 1965-11-15 1967-05-23 Sonic Dev Corp Gas turbine engine burner
US4754927A (en) * 1986-12-08 1988-07-05 Colt Industries Inc. Control vanes for thrust vector control nozzle
EP0739291A1 (en) * 1994-01-13 1996-10-30 Bell Helicopter Textron Inc. Engine exhaust gas deflection system
EP0739291A4 (en) * 1994-01-13 1997-03-05 Bell Helicopter Textron Inc Engine exhaust gas deflection system

Also Published As

Publication number Publication date
GB750622A (en) 1956-06-20
CH324032A (en) 1957-08-31
GB750687A (en) 1956-06-20
GB750601A (en) 1956-06-20

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