US3201937A - Variable area orifice injector - Google Patents

Variable area orifice injector Download PDF

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US3201937A
US3201937A US155217A US15521761A US3201937A US 3201937 A US3201937 A US 3201937A US 155217 A US155217 A US 155217A US 15521761 A US15521761 A US 15521761A US 3201937 A US3201937 A US 3201937A
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valve
nozzle
fluid
seat
ports
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US155217A
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Mckee Richard Dean
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    • 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

Definitions

  • This invention relates to jet propulsion apparatus and more particularly to improvements for controlling the direction of thrust produced by a nozzle to thereby control the direction of movement of a missile or the like which is propelled by a jet motor.
  • the directional control of jet propelled missiles which operate only in the atmosphere presents a relatively simple problem in that movable surfaces may be provided on the missile which utilize aerodynamic forces for changing direction of the missile.
  • movable surfaces may be provided on the missile which utilize aerodynamic forces for changing direction of the missile.
  • the nozzle through which the gases issue may, for example, be universally swiveled and oriented as desired under some sort of guidance command. It has also been the practice to immovably aflix the nozzle to the missile and in some way disturb the nozzle blast to produce lateral forces which will effect directional control.
  • One of the recent innovations in controlling direction with afixed nozzle is to provide its discharge cone with a plurality of angularly spaced apertures through which a fluid may be selectively injected. When such fluid is injected through one ormore of these apertures the axis of thrust is moved away from the geometrical axis of the nozzle, producing the desired lateral force.
  • a fluid may be selectively injected.
  • the quantity of fluid flowing through one or more of the apertures be varied as desired and to produce guidance controlling forces in some proportion to the rate at which a turn of direction is desired. It has accordingly been the practice to provide throttling valves in the fluid supply conduits ahead of the fixed apertures. The fluid was thus delivered first through a throttling valve open to varying degree and thence through a fixed aperture in the wall of the nozzle.
  • One of the objects of the invention is to obviate disadvantages of injection systems of the type just referred to.
  • Another object is to control the direction of thrust of a propulsion nozzle by injection of fluid into a nozzle exhaust stream in a manner to obtain maximum effectiveness of the injected fluid.
  • Another object is to inject the fluid at maximum velocity regardless of its mass rate of flow.
  • a further object is to eliminate certain parts of a here-v tofore employed nozzle injection system and improve its performance.
  • FIG. 1 is a side elevation of a rocket propelled missile 3,201,937 Patented Aug. 24, 1965 embodying a thrust nozzle forming the subject of the invention
  • FIG. 2 is an enlarged section taken on line 2-2, FIG. 1,
  • FIG. 3 is a section taken on line 3-3, FIG. 2,
  • FIG. 4 is an enlarged cross section of the injection valve indicated by arrow 4, FIG. 2, and
  • FIG. 4A is a modified form of the valve shown in FIG. 4.
  • the subject of the invention comprises a conventional nozzle 10, such as of the converging-diverging De Laval type, having a longitu-- dinal axis 11 aligned with longitudinal axis 12 of a rocket propelled missile 13, and which is provided with a plurality of angularly spaced discharge orifices 14 in its divergent cone through which fluid may be selectively injected into the rocket discharge gases.
  • these orifices are of fixed area and their control valves (not shown) are remotely located, the valves communicating with the fixed orifices through suitable conduits.
  • the present invention differs from the prior art just referred to in that orifices 14 are of variable area, suitable valving apparatus being disposed directly adjacent the point of fluid discharge rather than remotely as in the prior art.
  • orifices 14 are of variable area, suitable valving apparatus being disposed directly adjacent the point of fluid discharge rather than remotely as in the prior art.
  • the fixed orifices are eliminated, along with the pressure drop which occurs across them, and only a single pressure drop, rather than two pressure drops, exists between the source of fluid pressure (not shown) and the discharge side of the variable area control valves.
  • Each variable area control valve V employed comprises a conical seat 15 and a conical valve .16 which may be suitably actuated by a valve stem 17 attached to a piston 18, disposed in a cylinder 19 and having conduits 20, 21 adapted to supply fluid pressure to opposite sides of the piston. By creating differential pressures the rate of movement and position of the piston may be controlled as desired.
  • Such type of valve actuator is exemplary, however, and any other type of actuator may be employed.
  • the fluid which is injected into the rocket nozzle by each valve V is delivered through a conduit 22 connected to a source of fluid under pressure (not shown).
  • missile 13 is provided with a conventional guidance system which senses directional changes which are necessary to guide the missile to a target or other destination.
  • differential pressure is applied to opposite sides of one of the valve actuating pistons which opens the valve to apply fluid into the rocket exhaust gases. This changes the direction of thrust and moves axes 11, 12 relatively, producing a transverse component of force which effects turning movement of the rocket.
  • four equi-angularly spaced valves are employed, each of which may change the direction in one of the four directions in space. If turns in two directions are required at the same time it is to be understood that two of the valves may be open at the same time and to different degree.
  • valve member 16a "as, shown 'in' FIGF4A to' produce linearly' 'a change in the direction of'thrustwith' linear'imov'ement While the vlocati'onof valye -16 directly. adjacent thepoint of discharge, as distinguished from remotely located, ,materially' improves the effectiveness 6f the system,--tl1is may be further improved by using a contoured :valvef of the valve member, As will be apparent, also, the valve may be command-1116 valve seat contouredinits stead.
  • the injected exitgvelocity :of the inj ectedfluid' be substantially fluid may be either a liquid. or ag as,
  • valve stemiafiixedito 1 6661 (c) a valve stemiafiixedito 1 6661; valve mountedsfor' (d) an actuator iaffixed' toeach valve stem forselec-T e independently of the others.
  • a source of. fluid under. pressure communicating I .said? actuator comprises apiston slidable; 'a c ylin-. der, and a source of fluid under pressure interconnected with said cylinder for mO ing'sai'dpiston.
  • each 'seat is spaced from the inner surface of the nozzle a sufiicient distance to protect it from erosion by the exhaustgases w
  • Referenfces'cited laythe Examiner "UNITED STATES PATENTS MARK NEWMAN, Prim/ Ei mmr.”
  • SAMUEL LEVINE Emmi/zen.

Description

Aug. 24, 1965 D, MCK 3,201,937
VARIABLE AREA ORIFICE INJECTOR Filed Nov. 27, 1961 RICHARD DEAN M EE ATTOR NEY.
United States Patent The invention described herein 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.
This invention relates to jet propulsion apparatus and more particularly to improvements for controlling the direction of thrust produced by a nozzle to thereby control the direction of movement of a missile or the like which is propelled by a jet motor.
The directional control of jet propelled missiles which operate only in the atmosphere presents a relatively simple problem in that movable surfaces may be provided on the missile which utilize aerodynamic forces for changing direction of the missile. When the missile must move beyond the atmosphere such type of guidance system is no longer feasible and it has been conventional practice to guide the missile by effecting movement of the direction of thrust away from the direction of move ment. The nozzle through which the gases issue may, for example, be universally swiveled and oriented as desired under some sort of guidance command. It has also been the practice to immovably aflix the nozzle to the missile and in some way disturb the nozzle blast to produce lateral forces which will effect directional control.
One of the recent innovations in controlling direction with afixed nozzle is to provide its discharge cone with a plurality of angularly spaced apertures through which a fluid may be selectively injected. When such fluid is injected through one ormore of these apertures the axis of thrust is moved away from the geometrical axis of the nozzle, producing the desired lateral force. With such type of directional control apparatus it is desirable, also, that the quantity of fluid flowing through one or more of the apertures be varied as desired and to produce guidance controlling forces in some proportion to the rate at which a turn of direction is desired. It has accordingly been the practice to provide throttling valves in the fluid supply conduits ahead of the fixed apertures. The fluid was thus delivered first through a throttling valve open to varying degree and thence through a fixed aperture in the wall of the nozzle.
It has been found that the method of control just referred to provides optimum results only when the throttling valve is at or near its wide open position; when operating near its closed position with low rates of flow the controlling forces are materially decreased or are nonexistent.
One of the objects of the invention is to obviate disadvantages of injection systems of the type just referred to.
Another object is to control the direction of thrust of a propulsion nozzle by injection of fluid into a nozzle exhaust stream in a manner to obtain maximum effectiveness of the injected fluid.
Another object is to inject the fluid at maximum velocity regardless of its mass rate of flow.
A further object is to eliminate certain parts of a here-v tofore employed nozzle injection system and improve its performance.
Further objects, advantages, and salient features will become more apparent from a consideration of the description to follow, the appended claims, and the accompanying drawing, in which:
FIG. 1 is a side elevation of a rocket propelled missile 3,201,937 Patented Aug. 24, 1965 embodying a thrust nozzle forming the subject of the invention,
FIG. 2 is an enlarged section taken on line 2-2, FIG. 1,
FIG. 3 is a section taken on line 3-3, FIG. 2,
FIG. 4 is an enlarged cross section of the injection valve indicated by arrow 4, FIG. 2, and
FIG. 4A is a modified form of the valve shown in FIG. 4.
Referring now to the drawing, the subject of the invention comprises a conventional nozzle 10, such as of the converging-diverging De Laval type, having a longitu-- dinal axis 11 aligned with longitudinal axis 12 of a rocket propelled missile 13, and which is provided with a plurality of angularly spaced discharge orifices 14 in its divergent cone through which fluid may be selectively injected into the rocket discharge gases. In the prior art referred to, these orifices are of fixed area and their control valves (not shown) are remotely located, the valves communicating with the fixed orifices through suitable conduits.
The present invention differs from the prior art just referred to in that orifices 14 are of variable area, suitable valving apparatus being disposed directly adjacent the point of fluid discharge rather than remotely as in the prior art. As a result of this arrangement the fixed orifices are eliminated, along with the pressure drop which occurs across them, and only a single pressure drop, rather than two pressure drops, exists between the source of fluid pressure (not shown) and the discharge side of the variable area control valves.
Each variable area control valve V employed comprises a conical seat 15 and a conical valve .16 which may be suitably actuated by a valve stem 17 attached to a piston 18, disposed in a cylinder 19 and having conduits 20, 21 adapted to supply fluid pressure to opposite sides of the piston. By creating differential pressures the rate of movement and position of the piston may be controlled as desired. Such type of valve actuator is exemplary, however, and any other type of actuator may be employed. The fluid which is injected into the rocket nozzle by each valve V is delivered through a conduit 22 connected to a source of fluid under pressure (not shown).
In the operation of the device it will be assumed that missile 13 is provided with a conventional guidance system which senses directional changes which are necessary to guide the missile to a target or other destination. When a turn in direction is required as dictated by the guidance system, differential pressure is applied to opposite sides of one of the valve actuating pistons which opens the valve to apply fluid into the rocket exhaust gases. This changes the direction of thrust and moves axes 11, 12 relatively, producing a transverse component of force which effects turning movement of the rocket. As illustrated, four equi-angularly spaced valves are employed, each of which may change the direction in one of the four directions in space. If turns in two directions are required at the same time it is to be understood that two of the valves may be open at the same time and to different degree. As will also be apparent, by locating the valve and its seat directly adjacent the point of fluid discharge into the nozzle, there is no conduit between the valve and the point of discharge, as in the prior art duces further turning of the missile after the guidance system has called for cessation ofthe'turn'by closing the valve and thus may produce hunting of the missile about the desired direction of guidance.
member 16a "as, shown 'in' FIGF4A to' produce linearly' 'a change in the direction of'thrustwith' linear'imov'ement While the vlocati'onof valye -16 directly. adjacent thepoint of discharge, as distinguished from remotely located, ,materially' improves the effectiveness 6f the system,--tl1is may be further improved by using a contoured :valvef of the valve member, As will be apparent, also, the valve may be command-1116 valve seat contouredinits stead.
In either case, the eifective area of the annular opening" will vary non-linearly with'incrinents 6f6pe1iingbu1 the linear. f The injected exitgvelocity :of the inj ectedfluid' be substantially fluid may be either a liquid. or ag as,
examples of the Fformerfwhichhave been effectively employed including various Freons, "such as Freon '12,
12B ,i-l'13;',114 idf ll4B or nitrogen tetroxide (N 0 and examples of the lafter-inclndingfnitrogenor air.-
-Obviously"many inodific'ation's' and variations of the present invention are possible in the light" of the above 1 teachings. "lt isthereforeto be understood that within" the scope of the appended claims the invention maybe;
practiced otherwise than 'as specifically described.
'What'is'clair'nedis: i I
1.;Afrocketpr'ope1led device 'having a converging diverging nozzle through which gasesfexhaust and which isjst eered b'y injecting*fluidflaterally into the exhaust through angularspaced ports around the inner surface of;
the divergent'jportion; of the nozzle, the improvements,
inf-combifiation,,comprising: r
"(a') a circul-ar inwardly tapering' valve seat disposed within the wall of thenozzle' directly adjacent each of saidports, 1
(b) 'a valve for each seat having a-n' end conforming": v
to the'shape of its seat,
(c) a valve stemiafiixedito 1 6661; valve mountedsfor' (d) an actuator iaffixed' toeach valve stem forselec-T e independently of the others.
rectilinear'movemenc', L
tively' moving a valv and to varying positions ofop'e'ning,
. (e) a source of. fluid under. pressure communicating I .said? actuator comprises apiston slidable; 'a c ylin-. der, and a source of fluid under pressure interconnected with said cylinder for mO ing'sai'dpiston.
3. A device. in "666 1661 61wiur claim -1 wherein the pressurizedfluid communicatingwith each valve port is Fr'eon. i
:4. A device inaccordance' with claim 1 wherein each 'seat "is spaced from the inner surface of the nozzle a sufiicient distance to protect it from erosion by the exhaustgases w Referenfces'cited laythe Examiner "UNITED STATES PATENTS MARK NEWMAN, Prim/ Ei mmr." SAMUEL LEVINE, Emmi/zen.

Claims (1)

1. A ROCKET PROPELLED DEVICE HAVING A CONVERGINGDIVERGING NOZZLE THROUGH WHICH GASES EXHAUST AND WHICH IS STEERED BY INJECTING FLUID LATERALLY INTO THE EXHAUST THRUGH ANGULAR SPACED PORTS AROUNDTHE INNER SURFACE OF THE DIVERGENT PORTION OF THE NOZZLE, THE IMPROVEMENTS, IN COMBINATIN COMPRISING: (A) A CIRCULAR INWARDLY TAPERING VALVE SEAT DISPOSED WITHIN THE WALL OF THE NOZZLE DIRECTLY ADJACENT EACH OF SAID PORTS. (B) A VALVE FOR EACH SEAT HAVING AN END CONFORMING TO THE SHAPE OF ITS SEAT, (C) A VALVE STEM AFFIXED TO EACH VALVE MONTED FOR RECTILINEAR MOVEMENT, (D) AN ACTUATOR AFFIXED TO EACH VALVE STEM FOR SELECTIVELY MOVING A VALVE INDEPENDENTLY OF THE OTHERS AND TO VARYING POSITIONS OF OPENING, WITH EACH OF SAID PORTS WHEREBY FLUID MAY BE DELIVERED TO EACH VALVE, AND LIVERED TO EACH VALVE, AND (F) THE PROXIMITY OF SAID VALVE SEATS TO SAID PORT BEING SO NEAR AS TO PRODUCE NO SUBSTANTIAL PRESSURE DROP THEREBETWEEN, SUBSTANTIALLY ALL PRESSURE DROP BETWEEN THE SOURCE OF PRESSUR AND THE NOZZLE OCCURFING ACROSS EACH VALVE, THE FLUID DISCHARGE FROM A VALVE FLOSING DIRECTLY INTO THE NOZZLE AND SUBSTANTIALLY NO FLUID REMAINGING BETWEEN EACH VALVE AND ITS PORT AFTER IT CLOSES ON ITS SEAT.
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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3583439A (en) * 1966-02-16 1971-06-08 Semperit Osterrachisch Amerika Device for dosing fluid or pasty synthetic substance
US4530486A (en) * 1983-02-09 1985-07-23 City Of Hope National Medical Center Valve
US4637788A (en) * 1982-10-13 1987-01-20 Cadbury Limited Apparatus for making a confection including a depositing means and conveyor carried molds
US5154050A (en) * 1990-12-14 1992-10-13 Herup Eric J Thrust vector control using internal airfoils

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2114858A (en) * 1936-08-12 1938-04-19 Gen Electric Throttle valve
US2916873A (en) * 1958-10-22 1959-12-15 Advanced Res Associates Inc Jet deflecting apparatus
US2943821A (en) * 1950-12-30 1960-07-05 United Aircraft Corp Directional control means for a supersonic vehicle
US2952123A (en) * 1956-05-25 1960-09-13 Lockheed Aircraft Corp Directional controls for propulsive jets
US2984968A (en) * 1953-06-22 1961-05-23 North American Aviation Inc Automatic control of oxidizer and fuel turbopump system for a rocket engine
US3000178A (en) * 1957-09-16 1961-09-19 Snecma Ejection nozzles having variable cross-sectional area
US3010280A (en) * 1958-03-25 1961-11-28 United Aircraft Corp Variable-expansion nozzle
US3016699A (en) * 1952-10-10 1962-01-16 Snecma Aerodynamically acting jet deflecting device
US3024596A (en) * 1955-03-16 1962-03-13 Strato Missiles Inc Propulsion system with automatic control of fuel and air
US3058304A (en) * 1959-03-02 1962-10-16 Thompson Ramo Wooldridge Inc Steering control for rocket
US3101591A (en) * 1961-03-28 1963-08-27 Thompson Ramo Wooldridge Inc Vapor-gas injection thrust vector control system
US3128602A (en) * 1960-12-30 1964-04-14 Bendix Corp Thrust vector control

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2114858A (en) * 1936-08-12 1938-04-19 Gen Electric Throttle valve
US2943821A (en) * 1950-12-30 1960-07-05 United Aircraft Corp Directional control means for a supersonic vehicle
US3016699A (en) * 1952-10-10 1962-01-16 Snecma Aerodynamically acting jet deflecting device
US2984968A (en) * 1953-06-22 1961-05-23 North American Aviation Inc Automatic control of oxidizer and fuel turbopump system for a rocket engine
US3024596A (en) * 1955-03-16 1962-03-13 Strato Missiles Inc Propulsion system with automatic control of fuel and air
US2952123A (en) * 1956-05-25 1960-09-13 Lockheed Aircraft Corp Directional controls for propulsive jets
US3000178A (en) * 1957-09-16 1961-09-19 Snecma Ejection nozzles having variable cross-sectional area
US3010280A (en) * 1958-03-25 1961-11-28 United Aircraft Corp Variable-expansion nozzle
US2916873A (en) * 1958-10-22 1959-12-15 Advanced Res Associates Inc Jet deflecting apparatus
US3058304A (en) * 1959-03-02 1962-10-16 Thompson Ramo Wooldridge Inc Steering control for rocket
US3128602A (en) * 1960-12-30 1964-04-14 Bendix Corp Thrust vector control
US3101591A (en) * 1961-03-28 1963-08-27 Thompson Ramo Wooldridge Inc Vapor-gas injection thrust vector control system

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3583439A (en) * 1966-02-16 1971-06-08 Semperit Osterrachisch Amerika Device for dosing fluid or pasty synthetic substance
US4637788A (en) * 1982-10-13 1987-01-20 Cadbury Limited Apparatus for making a confection including a depositing means and conveyor carried molds
US4530486A (en) * 1983-02-09 1985-07-23 City Of Hope National Medical Center Valve
US5154050A (en) * 1990-12-14 1992-10-13 Herup Eric J Thrust vector control using internal airfoils

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