US3025669A - Methods of and devices for stabilizing turbine rating, notably in power missiles - Google Patents

Methods of and devices for stabilizing turbine rating, notably in power missiles Download PDF

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Publication number
US3025669A
US3025669A US751539A US75153958A US3025669A US 3025669 A US3025669 A US 3025669A US 751539 A US751539 A US 751539A US 75153958 A US75153958 A US 75153958A US 3025669 A US3025669 A US 3025669A
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pressure
liquid
pilot pressure
liquids
devices
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US751539A
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Fischoff Etienne
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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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/56—Control
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/2496—Self-proportioning or correlating systems
    • Y10T137/2499—Mixture condition maintaining or sensing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/2496—Self-proportioning or correlating systems
    • Y10T137/2559—Self-controlled branched flow systems
    • Y10T137/2564—Plural inflows
    • Y10T137/2572—One inflow supplements another
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/7722—Line condition change responsive valves
    • Y10T137/7758—Pilot or servo controlled
    • Y10T137/7762—Fluid pressure type
    • Y10T137/7764—Choked or throttled pressure type
    • Y10T137/7768—Pilot controls supply to pressure chamber

Definitions

  • This invention relates in general to power missiles and has specific reference to improvements in the methods of and the devices for stabilizing the velocity or rating of turbines, notably in power missiles.
  • the method of this invention consists essentially in applying a strictly identical pressure to the different liquids fed to the gas generator of the turbine or to the thrust chambers, this pressure being more particularly the same as a so-called pilot pressure of fixed or variable or adjustable value; preferably, this pilot pressure is variable either under the operators control or according to a predetermined program.
  • liquid designates simple liquids proper as well as solutions, liquid mixtures or gases.
  • the device for carrying out this method comprises essentially as many pressure regulators as there are separate liquids, each regulator comprising an inlet and an outlet for the liquid concerned, and an inlet for the pilo pressure, a generator for generating this pilot pressure and possibly a device for varying the value of this pilot pressure either under the operators control or according to a predetermined program.
  • the pilot pressure utilized is the pressure of one of the liquids concerned as obtaining at the outlet of a conventional-type by-pass valve inserted in the circuit of the liquid concerned.
  • a more advantageous form of embodiment of this invention consists in generating the pilot pressure in a separate device, this pilo pressure being transmitted to the different regulators by a chemically inert liquid, means being provided for varying the value of this pilot pressure.
  • a regulator according to this invention comprises a flexible diaphragm receiving the pilot pressure on one face and responsive to the delivery pressure of the liquid on the other face, this diaphragm being connected to a movable member of which the movements are adapted to modify the cross-sectional area of the passage interconnecting the inlet and outlet ports for the liquid concerned in the regulator.
  • FIGURE 1 is an axial sectional view showing a regulator constructed according to the teachings of this invention.
  • FIGURE 2 is a modified embodiment of this regulator.
  • FIGURE 3 is a further modification of the regulator of this invention.
  • FIGURE 4 is a diagrammatic illustration of a first form of embodiment of an installation according to this invention.
  • FIGURE 5 is a diagrammatic view illustrating another form of embodiment of this invention.
  • FIGURE 6 is a diagram illustrating a complete rocket powered aircraft control arrangement according to this invention.
  • FIGURE 7 is an explanatory diagram
  • FIGURES 8 and 9 are diagrams illustrating two further cases of application of the method and device con stituting the subject matter of this invention.
  • one of the essential component elements in an installation according to this invention is the pressure regulator, that is, the device which, when subjected to the action of the pilot pressure as defined hereinabove, limits to this value the liquid pressure obtained in the downstream portion of the circuit in which this regulator is inserted.
  • the regulator comprises a body 1 in which an axial bore 2 is formed; this bore comprises an inlet 3 for the liquid to be controlled and an outlet 4 for the same liquid.
  • these inlet and outlet are off-set along the axis of the body 1 so that a piston 5 slidably mounted in the bore 2 may modify the cross-sectional area available for the liquid between the inlet 3 and outlet 4, thereby creating a loss of pressure that may be used for modifying the pressure of this liquid at the outlet orifice 4.
  • the piston 5 is connected by a rod 6 to a diaphragm 7 closing the bore 2 beneath the outlet orifice 4; preferably, this diaphragm is flexible, that is, adapted to be deformed without its elasticity or its rigidity interfering with this movement.
  • the inner face 8 of the diaphragm 7 is responsive to the outlet pressure of the liquid to be controlled, and its outer face is responsive to the pilot 3 pressure required for a liquid properly introduced through the orifice 10.
  • the pressure obtained at the outlet is higher than the pilot pressure; in this case, due to the pressure differential, the diaphragm 7 moves downwards, carries along the piston 5 during its movement and thus the piston 5 will throttle the passage which, in the bore 2, connects the inlet orifice 3 to the outlet orifice 4; thus, the liquid pressure at the outlet will be reduced.
  • the pressure obtained at the outlet is lower than the pilot pressure; under these conditions, the pilot pressure becomes preponderant and moves the diaphragm 7 in the opposite direction, thereby increasing the crossasectional passage available for the liquid to be controlled and therefore the output pressure of this liquid.
  • this device cannot operate with a sufiicient degree of accuracy unless the piston 5 is free from influences other than those transmitted through the diaphragm 7; it is essential, notably, that the piston 5 moves without encountering any resistance under the control of this diaphragm and consequently that the pressure existing in the chamber situated between the piston and the bottom 11 of the bore be constantly equal to the output pressure of the liquid to be controlled. Under these conditions, it is advantageous to pierce through the piston at least one passage such as 12 to interconnect the two faces of the piston.
  • the liquid to be controlled is delivered radially through the orifice 3.
  • the piston receives a radial dynamic thrust which urges it against the wall of bore 2 with a variable force, this force generating a frictional resistance also of variable value which interferes with the free displacement of the piston.
  • the liquid to be controlled may be fed to the regulators in an axial direction as illustrated in the form of embodiment of FIGURE 2.
  • the piston 5 and rod 6 are co-axial with the orifice 3 constituting the inlet for the liquid to be controlled.
  • This piston 5 is displaceable in a bore 13 of member 14, this member 14 being supported in the body 1 by arms such as 15, 16.
  • an annular space 46 may be provided around the piston 5, this annular space 46 communicating only through orifices 47 with the piston. 5; these orifices 47 are disposed symmetrically and pierced through the wall of a cylindrical sleeve 48 force-fitted in the body 1.
  • the device of FIGURE 2 and that of FIGURE 3 are similar to that illustrated in FIGURE 1; more particularly, the operation is exactly the same.
  • FIGURE 4 A first form of embodiment of this combination is illustrated in FIGURE 4.
  • the liquids delivered to the gas generator of the turbine are supplied by pumps 17, I8, 19 and circulate through distributors 20, 21, 22 of known type.
  • regulators 25, 26 for example either of the type illustrated in FIGURE 1 or of the type shown in FIGURES 2 or 3.
  • the pilot pressure is that of the liquid supplied by pump 19 after this liquid has circulated through the by-pass valve 27 which may be adjustable if it is desired to vary the pressure of the gas generator.
  • This form of embodiment of the invention is characterized by many advantages, notably that of requiring a number of regulators which is inferior by one unit to the number of liquids utilized, a consequent advantage being the reduction in the length of piping.
  • the drawbacks characterizing the use of separate by-pass valves inserted in each pipe line are definitely avoided.
  • this arrangement is attended by certain inconveniences.
  • the difierent liquids are responsive to the law set up by the by-pass valve generating the pilot pressure, which is not an ideal law; as a result, a certain uncertainty still remains as to the point of stabilization of the turbine, due notably to the frictional contacts introduced by the guiding of the spring and its valve, as well as by the possible modification of the spring characteristics, due to the frequent presence of corrosive liquids.
  • FIGURE 5 The form of embodiment illustrated in FIGURE 5 is particularly advantageous in that it avoids the drawbacks still holding in the preceding form of embodiment, and that it derives from the invention all the advantages likely to be obtained therefrom.
  • a regulator 2, 29, 30 is inserted in each pipe line 31, 32, 33 connected to the outlet of the feed pumps, respectively.
  • the pilot pressure is supplied by a specific device comprising a bell-shaped member 34 containing a liquid 35 fed through ducts 36, 37, 38 to regulators 28, 29, 30 respectively.
  • a reserve of air or other gas 39 is provided at the top of the bell shaped member 34 to permit varia tions in the pilot pressure by displacing the piston 40 obturating this bell-shaped member with the assistance of a lever 41; this pressure may be read on the dial of a pressure gauge 42.
  • FIGURE 6 shows diagrammatically another form of embodiment wherein the invention is applied not only to the feed of a gas generator for the pump-driving turbine but also to the main injectors supplying the main thrust chamber of the missiles.
  • the pumps 48, 49 and 50 supply at the same time the main distributors 51, 52 associated with the main thrust chamber 53 and, through adequate branch lines, the distributors 54, 55 and 56 connected to the gas generator 57 of the turbine.
  • regulators 58, 59 and 60 Similar to those already described and to which the pilot pressure from the device 61 is applied .through ducts 62, 6'3 and 64. This assembly operates in the manner already described hereinabove.
  • regulators 62' and 63' to which the pilot pressure of another device 64' is applied through ducts 65, 66.
  • the generator 57 actuates the turbine 67 which drives in turn the three pumps 48, 49 and 50.
  • pilot pressures may be adjusted separately by acting independently upon the corresponding control levers. If desired, anyone of these control levers may be interlocked with another lever according to any suitable servo-action law.
  • pilot device 64' and of the relevant regulators 62, 63' permits of varying the maximum reaction torque and in this case this torque is designated by line such as 72, 73, etc. and therefore by varying the values of the two pilot pressures it becomes possible to stabilize at any point of the plane situated between the curve 71 and the straight 7 4 designating the maximum permissible speed of the turbine. Consequently, a thrust notably as close as possible to zero may be obtained in the main chamber 53 while maintaining a pressure in the generator which is substantially equal to the minimum pressure ensuring the proper operation of said generators.
  • an additional loss of pressure may be introduced in each fluid circuit leading to the generator, this additional pressure drop resulting for example from the provision of needle-valves such as 43, 44 and 45 (FIG- URE 5).
  • the displacements of piston 40 for varying the pilot pressure may be efiected automatically according to a predetermined law by substituting a cam of adequate contour, driven by a servo-motor, for the aforesaid lever 41; in this case, a remotecontrol action may also be provided without difficulty.
  • pipe lines 36, 37 and 38 may be replaced by a single line supplying the pilot" pressure to all the regulators such as 28, 29, 30, etc.
  • FIGURE 8 there is illustrated another form of embodiment of the device of this invention in the case of a remote-controlled variable-output valve.
  • the adjustable pilot pressure is supplied by the device 34 of which the piston 40 is connected by a rod 80 to a crank-handle 81, adequate means such as a screw 82 permitting the adjustment of the position of this piston 40 and consequently the value of the pilot pressure delivered by the device 34 through the pipe line 83.
  • the latter leads to a device 84 according to the invention which is connected on the other hand at 85 to an upstream source of pressure 86 and on the other hand at 87 to a downstream source of pressure 88.
  • FIGURE 9 another example is shown wherein it is assumed that there are three sources of pressure 89, 9t] and 91 of which two (90 and 91) are connected through pipe lines 92, 93 to a pair of devices 94, 95 according to the invention, the third source (89) being connected on the one hand through pipe lines 96, 97 to the inlets of devices 94, for the liquid at the pilot pressure.
  • the assembly leads into a chamber 98.
  • a variable thrust liquid propellant rocket motor for jet propelled vehicles including at least one combustion chamber with exhaust nozzle for generating said thrust, a gas generator producing burnt gases, three storage tanks for two combustion-supporting liquids (fuel and oxidizer) to be burnt in said combustion chamber and in said gas generator and for a third coolant liquid to be mixed in said gas generator with said burnt gases to limit the temperature thereof to a maximum permissible value, and injectors provided in said combustion chamber and in said gas generator to inject said liquids therein, a fluid supply circuit system comprising three rotary supply pumps provided each with an inlet and an outlet and adapted to feed said liquids from said tanks respectively to said combustion chamber and to said gas generator, a single gas turbine operatively coupled to said pumps to drive same simultaneously whereby the ratios of their speeds remain invariable at all turbine ratings, said gas generator producing said burnt gases to operate said turbine, suction lines connecting said tanks to said inlets of the relevant said pumps, discharge lines connecting said outlets of said two pumps for said combustion-supporting liquids respectively to the relevant
  • variable thrust liquid propellant rocket motor for jet propelled vehicles including at least one combustion chamber with exhaust nozzle for generating said thrust, a gas generator producing burnt gases, three storage tanks for two combustion-supporting liquids (fuel and oxidizer) to be burnt in said combustion chamber and in said gas generator and for a third coolant liquid to :be mixed in said gas generator with said burnt gases to limit the temperature thereof to a maximum permissible value, and injectors provided in said combustion chamber and in said gas generator to inject said liquids therein, a fluid supply circuit system comprising three rotary supply pumps provided each with an inlet and an outlet and adapted to feed said liquids from said tanks respectively to said combustion chamber and to said gas gen erator, a single gas turbine operatively coupled to said pumps to drive same simultaneously whereby the ratios of their speeds remain invariable at all turbine ratings, said gas generator producing said burnt gases to operate said turbine, suction lines connecting said tanks to said inlets of the relevant said pumps, discharge lines connecting said outlets of said two pumps for said combustion-supporting
  • each of said regulating devices comprises a casing formed with an inner closed cavity consisting of a substantially cylindrical bore closed at one end and expanding at the opposite end into a short coaxial transversely enlarged substantially circular chamber closed by a coaxial bottom of substantially frustoconical shape, a tubular inlet orifice and a tubular outlet orifice in said casing adapted for detachable connection within said discharge line and axially off-set along and opening in said cylindrical bore in perpendicular relationship to the axis thereof, whereby a flow passage is provided across said cylindrical bore from said inlet orifice to said outlet orifice, said inlet orifice being spaced from said closed end of said bore and said outlet orifice being iii) near said opposite end of said bore, a tubular inlet port in said frusto-conical bottom of said casing coaxially disposed therewith and with said cylindrical bore and opening through a counter-bore in said circular chamber,
  • any difference between said pressures causes a deflection of said diaphragm which moves unconstrainedly within said chamber, an integral stem directly and rigidly connecting said diaphragm to said rear end face of said piston whereby the latter is caused to move according to the actual deflection of said diaphragm, and a stop means provided on that side of said diaphragm which faces said bottom, said stop means registering with said counter-bore which is adapted to accommodate said stop means to limit the deflection of said diaphragm when said pilot pressure is released whereby said diaphragm is allowed to be backed by and to conform to said bottom to prevent undue stresses therein.
  • each of said regulating devices comprises a casing formed with an inner closed cavity consisting of a substantially cylindrical bore closed at one end and expanding at the opposite end into a short coaxial transversely enlarged substantially circular chamber closed by a coaxial bottom of substantially frustoconical shape, a tubular inlet orifice and a tubular outlet orifice in said casing adapted for detachable connection within said discharge line and axially off-set along and opening in said cylindrical bore in perpendicular relationship to the axis thereof, whereby a flow passage is provided across said cylindrical bore from said inlet orifice to said outlet orifice, said inlet orifice being spaced from said closed end of said bore and said outlet orifice being near said opposite end of said bore, a tubular inlet port in said frusto-conical bottom of said casing coaxially disposed therewith and with said cylindrical bore and opening through a counter-bore in said circular chamber, said inlet port being
  • each of said control means comprises a contained gas for generating said pilot pressure, a contained chemically inert liquid in contact with said gas, ducts connecting said control means with said inlet ports of said regulating devices respectively associated therewith, said inert liquid filling said ducts and the relevant halves of said circular chambers in said regulating devices for transmitting thereby said pilot pressure from said gas to said diaphragms and means for varying the value of said pilot pressure according to requirements.
  • a fluid supply circuit system comprising a contained gas for generating said pilot pressure, a contained chemically inert liquid in contact with said gas, ducts connecting said control means with said inlet ports of said regulating devices respectively associated therewith, said inert liquid filling said ducts and the relevant halves of said circular chambers in said regulating devices for transmitting thereby said pilot pressure from said gas to said diaphragrns and means for varying the value of said pilot pressure according to requirements.
  • a fluid supply circuit system in a rocket motor, a fluid supply circuit system according to claim 3, wherein adjustable restriction means are provided in each of said discharge lines down-stream of each of said regulating devices to permit of locally modifying the cross-section of the flow passage hence the pressure drop in said discharge lines between said regulating devices and said injectors to compensate for casual pressure drop decreases due to wear of said injectors and for casual pressure drop increases due to obstruction of said injectors in order to restore the actual pressure losses to their initial values and means being provided to operate said restriction means according to requirements. 7
  • adjustable restriction means are provided in each of said discharge lines including said regulating devices and down-stream thereof to permit of locally modifying the cross-section of the flow passage hence the pressure drop in said discharge lines between said regulating devices and said injectors to compensate for casual pressure drop decreases due to wear of said injectors and for casual pressure drop increases due to obstruction of said injectors in order to restore the actual pressure losses to their initial values and means being provided to operate said restriction means according to requirements.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
US751539A 1957-07-31 1958-07-28 Methods of and devices for stabilizing turbine rating, notably in power missiles Expired - Lifetime US3025669A (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3134425A (en) * 1961-02-08 1964-05-26 Thompson Ramo Wooldridge Inc Gas generation system and metering valve mechanism
US3746037A (en) * 1971-10-06 1973-07-17 Ibm Flow control and monitoring system
US4166084A (en) * 1978-03-24 1979-08-28 Shea Melvin E Bubble maker
US20040217212A1 (en) * 2003-04-19 2004-11-04 Oskar Frech Gmbh + Co. Kg Spray element for a spray head

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US623934A (en) * 1899-04-25 Fluid-actuated regulator
US1273466A (en) * 1917-04-28 1918-07-23 Doble Lab Fuel-burner.
US2127172A (en) * 1938-08-16 Fcknace bukner
US2195242A (en) * 1938-05-10 1940-03-26 Walter K Dow High and low pressure regulator or reducing valve
US2270304A (en) * 1938-12-17 1942-01-20 Oxweld Acetylene Co Gas regulation and pressure control apparatus
US2397659A (en) * 1942-07-29 1946-04-02 Daniel And Florence Guggenheim Control mechanism for rocket apparatus
US2397657A (en) * 1941-06-23 1946-04-02 Daniel And Florence Guggenheim Control mechanism for rocket apparatus
US2470564A (en) * 1944-11-15 1949-05-17 Reaction Motors Inc Reaction motor control system
US2487650A (en) * 1947-08-29 1949-11-08 Fluid Control Engineering Co Pressure regulator
US2606066A (en) * 1947-04-03 1952-08-05 Bendix Aviat Corp Automatic flow regulator
US2705047A (en) * 1949-08-18 1955-03-29 Bendix Aviat Corp Fuel control system for gas turbine engines
US2786331A (en) * 1948-08-10 1957-03-26 Bendix Aviat Corp Fuel feed and power control for gas turbine engines
US2930187A (en) * 1956-11-23 1960-03-29 Charles W Chillson Variable thrust rocket engine

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US623934A (en) * 1899-04-25 Fluid-actuated regulator
US2127172A (en) * 1938-08-16 Fcknace bukner
US1273466A (en) * 1917-04-28 1918-07-23 Doble Lab Fuel-burner.
US2195242A (en) * 1938-05-10 1940-03-26 Walter K Dow High and low pressure regulator or reducing valve
US2270304A (en) * 1938-12-17 1942-01-20 Oxweld Acetylene Co Gas regulation and pressure control apparatus
US2397657A (en) * 1941-06-23 1946-04-02 Daniel And Florence Guggenheim Control mechanism for rocket apparatus
US2397659A (en) * 1942-07-29 1946-04-02 Daniel And Florence Guggenheim Control mechanism for rocket apparatus
US2470564A (en) * 1944-11-15 1949-05-17 Reaction Motors Inc Reaction motor control system
US2606066A (en) * 1947-04-03 1952-08-05 Bendix Aviat Corp Automatic flow regulator
US2487650A (en) * 1947-08-29 1949-11-08 Fluid Control Engineering Co Pressure regulator
US2786331A (en) * 1948-08-10 1957-03-26 Bendix Aviat Corp Fuel feed and power control for gas turbine engines
US2705047A (en) * 1949-08-18 1955-03-29 Bendix Aviat Corp Fuel control system for gas turbine engines
US2930187A (en) * 1956-11-23 1960-03-29 Charles W Chillson Variable thrust rocket engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3134425A (en) * 1961-02-08 1964-05-26 Thompson Ramo Wooldridge Inc Gas generation system and metering valve mechanism
US3746037A (en) * 1971-10-06 1973-07-17 Ibm Flow control and monitoring system
US4166084A (en) * 1978-03-24 1979-08-28 Shea Melvin E Bubble maker
US20040217212A1 (en) * 2003-04-19 2004-11-04 Oskar Frech Gmbh + Co. Kg Spray element for a spray head
US7032842B2 (en) * 2003-04-19 2006-04-25 Oskar Frech Gmbh & Co. Kg Spray element for a spray head

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GB896966A (en) 1962-05-23
FR1180431A (fr) 1959-06-04

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