WO1983000721A1 - Systeme de commande et tuyere pour turbines a action - Google Patents

Systeme de commande et tuyere pour turbines a action Download PDF

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Publication number
WO1983000721A1
WO1983000721A1 PCT/US1980/000116 US8000116W WO8300721A1 WO 1983000721 A1 WO1983000721 A1 WO 1983000721A1 US 8000116 W US8000116 W US 8000116W WO 8300721 A1 WO8300721 A1 WO 8300721A1
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WO
WIPO (PCT)
Prior art keywords
fluid
flow
nozzle
section
neck
Prior art date
Application number
PCT/US1980/000116
Other languages
English (en)
Inventor
John M Bailey
Original Assignee
Bailey, John, M.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Bailey, John, M. filed Critical Bailey, John, M.
Priority to PCT/US1980/000116 priority Critical patent/WO1983000721A1/fr
Publication of WO1983000721A1 publication Critical patent/WO1983000721A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/06—Arrangement of sensing elements responsive to speed
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03B—MACHINES OR ENGINES FOR LIQUIDS
    • F03B1/00—Engines of impulse type, i.e. turbines with jets of high-velocity liquid impinging on blades or like rotors, e.g. Pelton wheels; Parts or details peculiar thereto
    • F03B1/04—Nozzles; Nozzle-carrying members
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03B—MACHINES OR ENGINES FOR LIQUIDS
    • F03B15/00—Controlling
    • F03B15/02—Controlling by varying liquid flow
    • F03B15/20—Controlling by varying liquid flow specially adapted for turbines with jets of high-velocity liquid impinging on bladed or like rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/20—Hydro energy

Definitions

  • the present invention relates generally to speed control systems for impulse turbines and more par ⁇ ticularly to the nozzle structure used to provide a fluid drive jet for such turbines.
  • Impulse turbines may often be effectively employed to drive power generators, particularly in regions where natural supplies of flowing water exist.
  • the basic impulse turbines are quite small and relatively inexpensive per horsepower produced.
  • the governing system becomes quite expensive. This is because considerable work is required to vary the nozzle area or deflect the drive fluid jet, and a hydro-mechanical power assisted governor is required which may cost as much as the turbine and generator combined. Consequently, many small impulse turbine units are used only to produce DC current for which close speed control is not re ⁇ quired.
  • Many speed control systems for turbines and water wheels known to the prior art employ mechanical
  • OMPI governors in combination with complex mechanical deflection units to deflect the flow of fluid from a nozzle to the turbine wheel when an overspeed condi ⁇ tion occurs.
  • These mechanical deflection units such as the ones shown in United States Patent Nos. 580,098 to H.D. Williams, 929,198 to R. McF. Doble et al, 1,017,438 to T. McAuley, and 1,035,082 to J. Cachin physically intersect and divert a fluid jet, thereby requiring the use of considerable force for effective operation.
  • One aspect, of the present invention is to pro ⁇ vide a novel fluid impulse turbine system wherein a diverter operative in response to a very low con ⁇ trol force effectively diverts a jet of power fluid away from a turbine wheel to control an overspeed condition.
  • Another aspect of the present invention is to provide a novel fluid directing nozzle having a jet •forming neck portion and diverging section.
  • the present invention is directed to overcoming one or more problems related to the above-mentioned known prior art.
  • Figure 1 is a diagrammatic view of the fluid impulse turbine system of the present invention show ⁇ ing a vertical, longitudinal sectional view of the fluid nozzle;
  • Figure 2 is a sectional view taken along lines 2-2 of Figure 1;
  • Figure 3 is a diagrammatic view of a second embodiment of the fluid impulse turbine system of - the present invention showing a vertical, longitu ⁇ dinal sectional view of the fluid nozzle;
  • Figure 4 is a sectional view taken along lines 4-4 of Figure 3)
  • Figure 5 is a vertical, longitudinal sectional view of a second embodiment of the nozzle of Figure 3;
  • Figure 6 is a vertical, longitudinal sectional view of a third embodiment of the fluid impulse tur ⁇ bine system of the present invention;
  • Figure 7 is a vertical, longitudinal sectional view of a second embodiment of a nozzle of the present invention.
  • Figure 8 is a vertical, longitudinal sectional view of a portion of a third embodiment of a nozzle of the present invention.
  • Figure 9 is a sectional view of a portion of the nozzle of Figure 8.
  • Figure 10 is a vertical, longitudinal sectional view of a fourth embodiment of a nozzle of the present invention.
  • OMPI Figure 11 is a vertical, longitudinal sectional view of a fifth embodiment of a nozzle of the present invention.
  • Figure 12 is a vertical, longitudinal sectional view of a portion of the nozzle of Figure 11 in the power off mode
  • Figure 13 is a vertical, longitudinal sectional view of a sixth embodiment of a nozzle of the present invention.
  • Figure 14 is a vertical, longitudinal sectional view of a portion of the nozzle of Figure 13 in the power off mode.
  • an impulse turbine indicated generally at 10 includes a turbine or bucket wheel 12 and a nozzle 14 through which water is supplied to the turbine wheel.
  • the turbine wheel 12 rotates on a central shaft and includes a plurality of peripherally mounted cup shaped buckets 16 of the type conventionally used in Pelton water- wheels. These buckets receive the driving fluid from the nozzle 14 which is used to drive the tur ⁇ bine wheel 12.
  • the central axis of the nozzle is aligned to extend through the surface of the buckets at the periphery of the turbine wheel, so that nor ⁇ mally a jet of fluid from the nozzle impinges di ⁇ rectly on the buckets 16 as they rotate into the fluid stream.
  • the nozzle 14 is connected to a fluid source and receives fluid through high pressure flow passage 18 which, at the nozzle end, tapers inwardly to form a rectangular shaped neck 20 of reduced cross-section. This neck, which shapes the high pressure in passage
  • OMPI 18 to a fluid jet issuing from the nozzle terminates at a point 22 where the nozzle tapers outwardly to form a diverging section 24.
  • the diverging section terminates at a nozzle opening 26 ⁇ which is much wider than the cross section of the neck 20.
  • the angle 28 formed by the outwardly tapering walls of the diverging section 24 is important, and ideally con ⁇ stitutes an angle of close to 30°. This angle should normally be within the range of from 20-40°.
  • a small fluid bypass line 30 is provided having an inlet port 32 which communicates with the flow passage 18 at a point before the flow passage tapers inwardly to form the rectangular shaped neck 20.
  • bypass line 30 extends between the inlet port and an outlet port 34 which is positioned at the point 22 where the neck 20 terminates and the outwardly tapered diverging section 24 begins. It should be noted that the bypass line 30 includes an outlet line section 36 which terminates at the outlet port 34 and which has a central axis that is oriented transversely to the central axis of the rectangu ⁇ lar neck section 20.
  • valve 38 The flow of fluid through the bypass line 30 from the flow passage 18 is controlled by a valve 38 in the bypass line.
  • This valve may be an elec ⁇ trically or mechanically actuated valve which is controlled by a speed sensing device 40 responsive to the speed of the turbine wheel 12.
  • a speed sensing device 40 responsive to the speed of the turbine wheel 12.
  • Any speed sensing means known to the art capable of mechani- cally or electrically controlling the valve 38 may be employed.
  • a conventional flyweight governor could be used to directly actuate the valve.
  • the valve 38 is an electric ⁇ ally operated valve, such as a solenoid valve, the
  • OMPI speed sensing device 40 will constitute a means for effecting an electrical signal as a function of tur ⁇ bine speed. This can be a centrifugal switch which closes at a predetermined speed to provide power to the valve 38, or an oscillator, alternator, or similar frequency or voltage generating device which is driven by the turbine wheel and coupled to a fre ⁇ quency or voltage sensor to provide power to the valve when the received frequency or voltage exceeds a predetermined level.
  • the fluidic switching structure is of a conventional two dimensional type, where all functions occur in a two dimensional plane.
  • This requires that a rec ⁇ tangular flow passage of the type shown by the neck 20 be employed, and such flow passages are not ideally suited for use with the usual Pelton type impulse turbine which is best driven by jets of circular cross-section. Consequently, it is more desirable to employ a fluidic switching system that will ef ⁇ fectively divert a cir ular jet, and this requires a form of three dimensional fluidic switch.
  • FIGS 3, 4, and 5 illustrate a quasi three dimensional flow diverting nozzle which is readily adaptable for use with the circular flow of a Pelton type impulse tu ⁇ bine.
  • fluid flowing through the flow passage 18 of a Pelton type nozzle 14 passes into a circular shaped neck 46 of reduced cross- section.
  • This circular shape neck terminates at a circular line 48 where the walls of the nozzle 14 taper outwardly to form the diverging section 24.
  • the walls of the diverging section pref ⁇ erably taper to form an angle of 30° or an angle within the range of from 20-40°.
  • the bypass line 30 begins at the inlet port 32, but instead of terminating at an outlet port 34 as shown in Figure 1, the bypass line of Figure 3 terminates in an arcuate shaped slot 50 which ex- tends along the line 48.
  • the arcuate slot like the outlet port 34, is located on or near the transition between the circular neck 46 and the coni- cally shaped diverging section 24.
  • Figure 5 illustrates another embodiment of the flow diverting nozzle of Figure 3 wherein the outlet slot 50 is replaced by a plurality of outlet aper ⁇ tures 52 extending along an arc positioned on the line 48 as shown in Figure 5.
  • Fluid from the outlet section 36 of the bypass line is provided to a chamber 54 formed in a collar 56 which extends around the end of the circular shaped neck 46.
  • the chamber 54 is positioned over the outlet apertures 52 and supplies fluid from the bypass line 30 which flows through the apertures 52 to provide diverting jets transverse to the central axis of the circular shaped neck 46.
  • FIG. 3 The structures of Figures 3, 4 and 5 operate substantially in the same manner as described in connection with the structure of Figures 1 and 2, with the exception that a circular jet of fluid from the nozzle 14 is effectively diverted thereby. It will be noted in Figure 3 that a filter 58 is pro ⁇ vided in the bypass line 34 before the valve 38 to prevent any foreign matter from clogging the valve, the bypass line, or the outlet slot 50.
  • Diversion of the circular jet of driving fluid for a Pelton type impulse turbine need not always be accomplished by a control fluid stream directed transversely to the flow direction of the driving fluid.
  • the actual driving fluid through the circular shaped neck 46 is selectively employed to create a conical fluid flow through the nozzle opening 26 which reduces the driving power applied to the tur ⁇ bine wheel 12.
  • tube 58 is mounted so that an open end 60 of the tube is located at or very near the transition line 48 between circular shaped neck 46 ' and the conical
  • the tube is mounted so that the central axis thereof extends along the central axis of the circular shaped neck 46. The remaining, outermost end of the tube is closed at 62 to prevent fluid flow therethrough.
  • the tube 58 is mounted in position by a very thin, hollow, streamlined strut 64 which is secured to the wall of the diverging section 24 by a threaded nut 66, or other suitable mounting means.
  • the por- tion of the strut which extends outwardly from the diffuser section wall is tubular in configuration as illustrated at 68, and is connected to a fluid exit line 70 which conducts fluid to a suitable re ⁇ DC.
  • the valve 38 which is controlled in re- sponse to the speed of the turbine wheel 12, is connected to control fluid flow through the fluid exit line 70, and normally this valve is open to permit fluid flow.
  • the speed sensing device 40 closes the valve 38, and fluid now fills or discontinues flowing through the tube 58.
  • the previously open end of the tube now acts in the same manner as would a solid pin, and causes the flow of fluid through the diverg ⁇ ing section 24 to leave the normal flow path 42 and fan outwardly in a conical shaped flow against the walls of the diverging section.
  • This alternate coni- cal path, indicated at 72 causes a large portion of the flow exiting from the nozzle opening 26 to completely miss the cup' shaped buckets 16 of the turbine wheel 12. That portion of the outgoing flow which does contact the cup shaped buckets does so at an angle different from the normal drive angle and is therefore inefficient for driving purposes. Consequently, the driving power to the turbine wheel 12 is decreased until the speed of the wheel drops to a point equal to or below the desired speed, at which time the speed sensing device 40 reopens the valve 38.
  • An inner closed end of the tube 78 is positioned within the flow passage 18 while the outermost closed end 80 of the tube is positioned within the diverging section 24.
  • This outermost closed end is of tapered, conical configu ⁇ ration and terminates at a pointed apex 82 positioned along the central axis of the circular neck 46 and extending toward the nozzle opening 26.
  • This tapered closed end creates a good solid jet of fluid around the outermost end of the tube during normal flow operation of the nozzle 14.
  • the tube 74 is provided with a termerality of radial holes 84 located substantially in line with the juncture 48 between the neck 46 and the diverging section 24.
  • the bypass line 30 is connected between the flow passage 18 and the hollow strut 76, so that when the valve -38 is opened by the speed sensing device 40 upon the occurrence of an overspeed condi ⁇ tion of the turbine wheel 12, fluid is provided from the outlet 34, the strut 76 and the tube 74 to the radial holes 84. Fluid jets pass outwardly from the radial holes to drive the fluid stream from the neck 46 outwardly against the walls of the diverging section. The resultant conical fluid stream 72 re- Jerusalem the driving power for the turbine wheel in the manner previously described.
  • the nozzle structure of Figure 7 controls the fluid jet from the nozzle opening 26 with substan ⁇ tially no loss of- power fluid and minimal disruption of the jet. This is due to the fact that the strut 76 is positioned in the flow passage 18 where the fluid flow is low in velocity compared to flow in the neck 46 and the diverging section 24. The smaller area of the neck causes the velocity of the fluid.
  • the normal power fluid stream from the nozzle 14 may be diverted mechanically to alleviate a tur ⁇ bine wheel overspeed condition, although fluid from the flow passage 18 may be employed to power a me ⁇ chanical flow diverting structure.
  • a simple, me ⁇ chanical flow diverting unit is illustrated at 86 in Figure 8.
  • a sliding plate 88 is connected to a solenoid core 90 which is positioned within a chamber 92 formed in the nozzle housing.
  • a sole ⁇ noid coil 94 is electrically connected to the speed sensing device 40, and 'is energized ⁇ thereby when the turbine wheel 12 exceeds a predetermined speed.
  • a spring 96 normally biases the solenoid core 90 away from the coil 94, and serves to position the plate 88 so that the end thereof is flush with the inside dimension of the circular neck 46 and the diverging section 24. It will be noted from the side view of Figure 8 that the end 98 of the plate is angled upwardly to conform with the angle of the walls of the diverging section, while in Figure 9, a consideration of the front view of the plate shows that the end 98 thereof is concave in configuration to conform with the outer circumference of the neck 46.
  • the end 98 of the plate will cause no disruption in fluid flow through the nozzle 14.
  • the solenoid coil 94 is energized from the speed sensing device 40, and the end 98 of the plate now projects into the fluid stream at the juncture 48. This deflects the fluid jet from a normal flow path 100 to a flow path 102 along the bottom wall of the diverging section 24. The deflected flow path causes substantially all of the fluid issuing from the nozzle opening 26 to miss the buckets 16 of the turbine wheel 12.
  • fluid from the flow passage 18 is employed to power the mechanical flow diverter structure within the nozzle.
  • an open ended tube 104 is mounted within the diverging section 24 by a streamlined strut 106 secured to the wall of the diverter section.
  • the •'central axis ⁇ of the tube 104 lies along the common central axis of the neck 46 and the diverging section 24, and during the normal operation of the nozzle, fluid passes both through and around the tube with little disruption of the power fluid jet 108.
  • the tube 104 is positioned so that the inner end thereof is aligned with the juncture 48 between the neck 46 and the diverging section 24.
  • a second tubular structure 110 of rubber or similar resilient material is inserted within the tube 104, and the ends of this internal tube are sealed at 112 and 114 to the tube 104.
  • the speed sensing device 40 activates the valve 38 to permit fluid to enter the fluid bypass line 30 from the flow passage 18. Fluid now passes through the valve 38 which is intended to also boost the hydraulic pressure to some value above that within passage 18 and the outlet port 34 which is positioned to - admit fluid between the tube 104 and the resilient inner tube 110. This results in expansion of the resilient inner tube away from the wall of the tube 104 until this tube is substantially closed to fluid flow.
  • a stagnation zone is now created at the en ⁇ trant end to the tube 104, and the power fluid flow is diverted outwardly to follow a conically shaped flow path 112 along the walls of the diverging sec ⁇ tion 24. This conical flow reduces the power to the turbine wheel 12 in the manner previously de ⁇ scribed.
  • valve 38 in Figure 10 is a three way valve having a drain line 116.
  • the ⁇ drain line 116 is closed.
  • the drain line is connected to the outlet port 34 so that fluid may be drained from the space between the resilient tube 110 and the tube 104.
  • an effec ⁇ tive mechanical flow diverter for the nozzle 14 which is powered by fluid from the flow passage 18.
  • This unit includes a probe 118 which is mounted at end of the piston shaft 120 for axial movement to effect control of the drive fluid jet from the nozzle opening 26.
  • the forward end of the probe is conically tapered to a terminal apex 122 which lies along the central axis of the neck 46 and the diverging section 24.
  • the rear end of the probe is formed to provide a rear surface 124 which extends outwardly and laterally from the piston shaft 120.
  • the piston shaft 120 is connected to a piston 125 which is slidably enclosed within a cylinder 126. Normally the piston is suitably biased toward the rear of the cylinder by biasing means, such as
  • OMPI a spring 128, so that the probe 118 is maintained in the position shown in Figure 11.
  • the rear surface 124 of the probe is spaced well behind the juncture line 48 between the neck 46 and the diverging section 24. With the probe positioned in this manner, some disruption in the fluid flow within the neck 46 will occur, but this disruption does not occur at a point which will cause the fluid jet issuing from the nozzle 26 to switch to a hollow concial form. Instead, fluid flows over the surface of the probe and down over the pointed apex 122 to form a circular drive fluid jet 130 which issues centrally from the nozzle opening 26.
  • the cylinder 126 is mounted upon a streamlined strut 132 which extends from the wall of the flow passage 18 and includes a portion of the bypass line 30 terminating at the outlet port 34.
  • the outlet port is positined behind the piston 125, so that when the valve 38 is opened in response tQ the speed sensing device 40, fluid will pass from the fluid passage 18 through the bypass line 30 and the valve 38 to a point in the chamber 126 behind the' piston 125. This fluid forces the piston outwardly against the bias of the spring 128, so that the piston rod 120 moves the probe 118 to the position shown in Figure 12.
  • the valve 38 of Figure 11 is a three-way valve which is connected to a drain line 116, and during normal speed operation of the turbine wheel 12, the valve prevents fluid flow from the fluid passage 18 through the bypass line 30 while permitting fluid to drain from the cylinder 126 into the drain line 116.
  • the valve 38 When the valve 38 is open to fluid flow through the bypass line 30, the path from the cylinder 126 to the drain line 116 is blocked.
  • the normal fluid flow disruption through the nozzle 14 which is caused by the probe 118 of Figure 11 may be substantially eliminated through the use of the structure illustrated in Figures 13 and 14.
  • the piston shaft 120 is encased in a fixed sleeve 136 which may be secured to the cylinder 126 or otherwise mounted within the flow passage 18.
  • the end of the sleeve adjacent the probe 118 is struc ⁇ turally configured to mate with the rear surface 124. of the probe.
  • both the end surface 138 of the sleeve 136 and the rear surface 124 of the probe 118 are preferably angled rearwardly.
  • the outer diameter of the sleeve 136 is equal to the outer diameter of the probe 118 at the peri ⁇ pheral edge of the rear wall 124 thereof, so that the probe tapers from a point flush with the outer wall of the sleeve down to the apex 122.
  • the probe causes no disruption of the fluid power jet 130 when the turbne wheel 12 is running at the de ⁇ sired speed.
  • the probe 118 is moved outwardly away
  • turbines are often arranged with two or more jets striking the same wheel, or with one or more jets striking two or more wheels. If multiple jets are employed, it is apparent that all jets will have to be controlled by devices of the type described. For example, if two jets are used, they can be simultaneously switched from a power on to a power off mode as the turbine reaches the desired maximum speed. However, improved control might be obtained if each jet is switched from a power on to a power off mode at different speed. Thus, both jets would produce full power at turbine speeds slightly below the desired speed, while only one jet would produce full power beginning at a turbine speed slightly below the desired speed and ending at a turbine speed slightly above the desired speed. At the point slightly above the
  • the diverg ⁇ ing section 24 described in connection with the various embodiments herein tends to cause the fluid leaving the necks 20 or 46 to act in accordance with the "Coanda Effect.” Consequently, the fluid jet from the nozzle opening 26 may be easily diverted at points 22 and 48.
  • the diverging section 24 need not be in the form of a closed conical surface, but must include a surface which diverges away from the ori- ginal axis of the water jet through the necks 20 or 46.
  • the surface of the diverging section 24 may "include only a portion of a frustum of a cone.
  • the impulse turbine 10 may be operated and main ⁇ tained at a controlled speed for electrical AC power generation or other applictions where speed control is required.
  • the direction of the driving fluid jet issuing from the nozzle opening 26 of the nozzle 14 may be effectively controlled with a very low control force and without the need for complex mech ⁇ anical control devices.
  • the speed sensing device 40 senses an overspeed condition of the turbine wheel 12
  • the valve 38 or the solenoid coil 96 is activated thereby to cause disruption of the fluid flow through the neck 20 or the neck 46 at the juncture between the neck and the diverging section 24. Disruption of the flow at this point is accomplished by either
  • OMPI a fluid jet or a simple flow diverter, and minimal energy is required to cause the fluid stream to flow along the inclined wall of the diverging section.
  • the creation of a fluid flow along the diverging section wall results in a fluid jet from the nozzle opening 26 which either misses the turbine wheel 12 or does not provide an effective driving force thereto.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Hydraulic Turbines (AREA)

Abstract

Un système de turbine à action (10) comprend une roue de turbine montée de manière rotative (12) et un système de détection de vitesse (40) pour détecter la vitesse de la roue de turbine (12). Une tuyère de déviation (14) de l'écoulement assure normalement un jet de fluide d'entraînement pour actionner la roue de turbine (12). Cette tuyère (14) comprend un dispositif intérieur de déviation de l'écoulement (30, 38, 58, 74, 76, 88, 90, 94, 104, 110, 118) qui fonctionne sous la commande du système de détection de vitesse (40) lorsque la roue de turbine (12) atteint une condition de survitesse pour dévier angulairement le jet de fluide d'entraînement sortant par l'ouverture (26) de la tuyère.
PCT/US1980/000116 1980-02-04 1980-02-04 Systeme de commande et tuyere pour turbines a action WO1983000721A1 (fr)

Priority Applications (1)

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PCT/US1980/000116 WO1983000721A1 (fr) 1980-02-04 1980-02-04 Systeme de commande et tuyere pour turbines a action

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Application Number Priority Date Filing Date Title
PCT/US1980/000116 WO1983000721A1 (fr) 1980-02-04 1980-02-04 Systeme de commande et tuyere pour turbines a action

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WO1983000721A1 true WO1983000721A1 (fr) 1983-03-03

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2944460A1 (fr) * 2009-04-21 2010-10-22 Ass Pour La Rech Et Le Dev De Buse apte a maximaliser la quantite de mouvement produite par un ecoulement diphasique provenant de la detente d'un debit saturant
EP2479386A1 (fr) * 2011-01-20 2012-07-25 MBDA France Dispositif pour commander le passage d'un jet gazeux dans une tuyère d'engin volant, et engin volant comportant de tels dispositifs
EP2407663A3 (fr) * 2010-07-13 2015-07-15 SOLARFOCUS Holding GmbH Appareil de commande d'une turbine hydraulique
AT14883U1 (de) * 2014-07-07 2016-08-15 Solarfocus Holding Gmbh Turbine mit Steuerkörper

Citations (8)

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US976174A (en) * 1910-03-22 1910-11-22 Pelton Water Wheel Co Standardizing device for governors.
US1035082A (en) * 1908-09-25 1912-08-06 Jean Cachin Automatic regulator for impact water-wheels.
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Cited By (8)

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Publication number Priority date Publication date Assignee Title
FR2944460A1 (fr) * 2009-04-21 2010-10-22 Ass Pour La Rech Et Le Dev De Buse apte a maximaliser la quantite de mouvement produite par un ecoulement diphasique provenant de la detente d'un debit saturant
WO2010122251A1 (fr) * 2009-04-21 2010-10-28 Association Pour La Recherche Et Le Developpement De Methodes Et Processus Industriels "Armines" Buse apte a maximaliser la quantite de mouvement produite par un ecoulement diphasique provenant de la detente d'un debit saturant
EP2421657A1 (fr) * 2009-04-21 2012-02-29 Association Pour La Recherche Et Le Développement De Méthodes Et Processus Industriels "Armines" Buse apte a maximaliser la quantite de mouvement produite par un ecoulement diphasique provenant de la detente d'un debit saturant
EP2407663A3 (fr) * 2010-07-13 2015-07-15 SOLARFOCUS Holding GmbH Appareil de commande d'une turbine hydraulique
EP2479386A1 (fr) * 2011-01-20 2012-07-25 MBDA France Dispositif pour commander le passage d'un jet gazeux dans une tuyère d'engin volant, et engin volant comportant de tels dispositifs
WO2012098315A1 (fr) * 2011-01-20 2012-07-26 Mbda France Dispositif pour commander le passage d'un iet gazeux dans une tuyère d'engin volant, et engin volant comportant de tels dispositifs
FR2970742A1 (fr) * 2011-01-20 2012-07-27 Mbda France Dispositif pour commander le passage d'un jet gazeux dans une tuyere d'engin volant, et engin volant comportant de tels dispositifs
AT14883U1 (de) * 2014-07-07 2016-08-15 Solarfocus Holding Gmbh Turbine mit Steuerkörper

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