US3456667A - Bistable fluid device - Google Patents

Bistable fluid device Download PDF

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Publication number
US3456667A
US3456667A US3456667DA US3456667A US 3456667 A US3456667 A US 3456667A US 3456667D A US3456667D A US 3456667DA US 3456667 A US3456667 A US 3456667A
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Prior art keywords
pressure
exhaust port
output
point
port
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English (en)
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Endre A Mayer
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Bendix Corp
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Bendix Corp
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    • 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
    • F15C1/18—Turbulence devices, i.e. devices in which a controlling stream will cause a laminar flow to become turbulent ; Diffusion amplifiers
    • 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
    • F15C1/16—Vortex devices, i.e. devices in which use is made of the pressure drop associated with vortex motion in a fluid
    • 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
    • Y10T137/206—Flow affected by fluid contact, energy field or coanda effect [e.g., pure fluid device or system]
    • Y10T137/2087—Means to cause rotational flow of fluid [e.g., vortex generator]
    • Y10T137/2109—By tangential input to axial output [e.g., vortex amplifier]
    • Y10T137/2115—With means to vary input or output of device

Definitions

  • This invention pertains to a bistable fluid device and more particularly to a vortex device wherein supply iluid is admitted to a cylindrical chamber and control iluid, admitted to the chamber through control ports, imparts a vortical ow to the supply fluid which emerges from an exhaust port at the center of the cylinder.
  • FIGURE 1 is a section taken at 1-1 of FIGURE 2 and shows a schematic View of a preferred embodiment
  • FIGURE la is an enlarged section of a modied stepped exhaust port
  • FIGURE 2 is a section taken at 2 2 of FIGURE l;
  • FIGURE 3 is a graph showing three hysteresis loops with the abscissa being supply pressure PS and with the ordinate being output pressure PO with the three hysteresis loops being for three different control pressures;
  • FIGURE 4 is an enlarged sectional view showing the chamber provided about the exhaust port at the area where the reduced pressure is formed.
  • FIGURE 7 is an enlarged section taken at 7-7 of FIGURE 6.
  • FIGURE l is shown vortex device 20 having cylin- ICC drical housing 22 with a plate 23 covering one end thereof.
  • a supply port 24 is formed in housing 20 and is connected to a fluid supply 25.
  • a button 26 is inserted in housing 22 and is spaced from wall 23 thereby forming a chamber 27 therebetween. Also, button 26 is spaced from walls of housing 22 to form an annular clearance 28 therebetween.
  • a control inlet 29 is formed centrally of button 26 ,and is connected to radial passages 30 each of which terminate in a nozzle 32 which, under suflicient control pressure from source 31, will direct fluid into annular space 28 causing uid supply passing through port 24 to swirl or assume a vortical flow which increases in rate as it moves towards exhaust port 44 which is formed centrally of wall 23 within annular extension 45.
  • a signal tube 34 is provided through housing 22 and through button 26 and is connected to passage 36 and jet 38 and introduces fluid flow from signal generator 35 which aids the ow from jets or nozzles 32.
  • a second signal tube 40 also connected to signal generator 35 passes through the wall of housing 22 and through button 26 connecting to passage 42 and nozzle 43 to introduce a dlow in annular space 28 which opposes the ow from nozzles 32.
  • Exhaust port 44 increases in diameter in the direction of exhaust ow to form a conical like surface 46. As can be seen in FIGURE 1, the exhaust port length is greater than its inlet diameter D. This surface could also be increased as shown in the cross section of FIGURE la where exhaust port 44 has two diameters; a smaller diameter and a stepped larger diameter 44a. As will become apparent, it is this increase in diameter which provides structure for developing the bistable nature of this invention.
  • Vent port 56 connects chamber 54 to a pressure less than the supply pressure Ps, which may be atmospheric pressure in this embodiment.
  • a pickoif tube 58 is axially aligned with exhaust port 44 and axially spaced therefrom.
  • the pressure in tube 58 corresponds to the ow emerging from port 44.
  • the flow emerging from port 44 has an axial portion which is surrounded by a conical portion with the axial portion diminishing and the conical portion increasing as the amount of swirl in chamber 27 is increased due to increased control pressure PC.
  • control pressure PC is increased, the output ow is decreased and the axial portion of the stream is decreased thereby decreasing the pressure in tube 58 and the reading on pressure gauge 59.
  • the swirl is decreased due to a decreased pressure control PC, the axial flow and the total ilow from port 44 is increased and the pressure in tube 58 is correspondingly increased.
  • a pressure control bias Pc Bias
  • passage 29 to establish an operatingrange which may be increased or decreased by applying a signal flow to jets 38, 43 respectively.
  • Pc Bias a pressure control bias
  • the output pressure will follow line A in the hysteresis loop marked PC Bias which is the center loop in the graph of FIGURE 3.
  • PC Bias which is the center loop in the graph of FIGURE 3.
  • point B there will be a sudden increase as shown by line C to point C online D where an increase in supply pressure will result in a gradual increase in output pressure P0.
  • FIGURE 4 shows the flow from exhaust port 44 during the operation on line A in the graph of FIGURE 3 and it is seen that the flow is close against the ared walls ⁇ 46 with a slight recirculation flow R, R taking place. Recirculation ilow R, R' tends to reduce the amount of ow coming from port 44.
  • FIGURE 5 shows the flow from port 44 at point B on line A in the graph of FIGURE 3 and here it is seen that the flow has separated from the ilared walls 46 and there is created an annular region of reduced pressure V which increases the pressure drop through port 44 thereby increasing the flow therethrough which accounts for the jump in output pressure to line D in the graph of FIGURE 3. Also aiding in this sudden increase of output pressure is the fact that the recirculation ilow R, R', has been largely eliminated thereby reducing resistance to output flow from port 44.
  • PC Bias-APC can be obtained by supplying a duid signal to tube 40 which will cause a ow APC from nozzle 43 which opposes and hence reduces the PC Bias flow from nozzles 32.
  • PC Bias-i-APC loop can be obtained by causing a fluid signal APC to pass through tube 34 and out nozzle 38 aiding the swirl caused by the PC Bias iiow from nozzles 32.
  • FIGURE l If the embodiment of FIGURE l is operating at state 1 and a APC is applied by a iiuid signal through nozzle 43, the operating point will go from 1 to 4 and upon removal of the -APC signal, the operating point will return to 1 resulting in no output pressure P0 change. However, if the operating point is at 2 and a APC is initiated, the operating point will again go to 4 and when the APC signal is removed, the operating point will go to 1 resulting in a substantial output pressure P0 change signifying that the stable state was at point 2.
  • output iiow can be plotted against supply pressure in the graph of FIGURE 3 and this could be done by modifying the device of FIGURE l to eliminate the pickol tube 58 and by applying a iiowmeter to passage 56.
  • the output flow would vary in the same manner as shown in the hysteresis loops in the graph of FIGURE 3 although the output pressures obtainable would be some- -what lower than those obtainable with the use of pickoi tube 38.
  • FIG. 6 Another embodiment for obtaining a pressure indication of the stable state to which the vortex device is operating is shown in FIGURES 6 and 7.
  • FIGURE 6 is shown a section of exhaust passage 44 wherein a plurality of radial passages 62 are formed at that point on wall 46 where the area of reduced pressure V occurs.
  • Annulus 64 connects each of the passages 62 to output port 66 which is connected to pressure gauge 68.
  • the pressure at gauge ⁇ 68 will be substantially reduced.
  • the pressure in gauge 68 will be relativel high.
  • An apparatus comprising:
  • housing means providing a chamber for containing vortical ow
  • means including a supply port adapted to be connected to a source of fluid for providing a preselected first vortical iiow rate of said iluid in said -chamber and a preselected second vortical ow rate of said huid in said chamber, said first vortical ow rate being greater than said second vortical flow rate;
  • said housing having an exhaust port for egress of said fluid, said exhaust port having means including a predetermined divergence in the direction of iiuid tiow for providing a first stable pressure distribution downstream of said exhaust port at said iirst vortical flow rate characterized by having a iirst pressure central of said exhaust port and further which provides a second stable pressure distribution downstream of said exhaust port at said second vortical flow rate characterized by having a second pressure central of said exhaust port being greater than said lirst pressure; and
  • pressure responsive means operably associated with said exhaust port for providing an output signal indicative of said rst and second stable pressure distributions.
  • said means for providing said first and second vortical oW rate includes a uid port substantially tangentially oriented with respect to said vortex chamber for incrementally influencing the rate of vortex flow in said chamber.
  • said means for providing said tirst and second vortical tlow rates further includes a second fluid port substantially tangentially oriented with respect to said vortex chamber in a direction for incrementally influencing said vortical ow rate in an opposite rotational direction than said rst fluid port.
  • said means for providing said rst and second vortical rates includes means for incrementally varying the ow rate of said uid into said chamber.
  • said pressure responsive means includes a pick olf tube axially lined with and axially spaced from said exhaust port to receive the flow therefrom thereby providing a pressure in said tube being indicative of said first and second stable pressure distribution.
  • said pressure responsive means includes a fluid passage substantially radially communicating with said exhaust port thereby providing a pressure in said passage being indicative of said rst and second stable pressure distribution.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Theoretical Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • Control Of Fluid Pressure (AREA)
  • Nozzles (AREA)
  • Jet Pumps And Other Pumps (AREA)
US3456667D 1966-05-13 1966-05-13 Bistable fluid device Expired - Lifetime US3456667A (en)

Applications Claiming Priority (1)

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US54990866A 1966-05-13 1966-05-13

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US3456667A true US3456667A (en) 1969-07-22

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US (1) US3456667A (de)
DE (1) DE1600389C3 (de)
GB (1) GB1134489A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3507296A (en) * 1968-06-25 1970-04-21 Philco Ford Corp Fluid flow control apparatus
US3692036A (en) * 1971-04-08 1972-09-19 Philco Ford Corp Fluid flow control apparatus

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075227A (en) * 1960-04-14 1963-01-29 Romald E Bowles Vacuum cleaner
US3213682A (en) * 1961-03-06 1965-10-26 Aerojet General Co Fluid turbulence detector
US3219048A (en) * 1963-05-22 1965-11-23 Palmisano Rosso Richard Vortex flow control valve
US3276259A (en) * 1965-02-23 1966-10-04 Romald E Bowles Fluid amplifier
US3324891A (en) * 1961-04-18 1967-06-13 Gen Electric Flow regulator
US3342196A (en) * 1966-01-04 1967-09-19 Stephen J Przybylko Vortex analog speed sensor
US3343790A (en) * 1965-08-16 1967-09-26 Bowles Eng Corp Vortex integrator

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075227A (en) * 1960-04-14 1963-01-29 Romald E Bowles Vacuum cleaner
US3213682A (en) * 1961-03-06 1965-10-26 Aerojet General Co Fluid turbulence detector
US3324891A (en) * 1961-04-18 1967-06-13 Gen Electric Flow regulator
US3219048A (en) * 1963-05-22 1965-11-23 Palmisano Rosso Richard Vortex flow control valve
US3276259A (en) * 1965-02-23 1966-10-04 Romald E Bowles Fluid amplifier
US3343790A (en) * 1965-08-16 1967-09-26 Bowles Eng Corp Vortex integrator
US3342196A (en) * 1966-01-04 1967-09-19 Stephen J Przybylko Vortex analog speed sensor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3507296A (en) * 1968-06-25 1970-04-21 Philco Ford Corp Fluid flow control apparatus
US3692036A (en) * 1971-04-08 1972-09-19 Philco Ford Corp Fluid flow control apparatus

Also Published As

Publication number Publication date
DE1600389C3 (de) 1973-09-13
DE1600389A1 (de) 1969-12-18
GB1134489A (en) 1968-11-27
DE1600389B2 (de) 1973-02-15

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