EP0589338A1 - Hélice à pas variable, spécialement pour bateaux de sport - Google Patents

Hélice à pas variable, spécialement pour bateaux de sport Download PDF

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Publication number
EP0589338A1
EP0589338A1 EP93114801A EP93114801A EP0589338A1 EP 0589338 A1 EP0589338 A1 EP 0589338A1 EP 93114801 A EP93114801 A EP 93114801A EP 93114801 A EP93114801 A EP 93114801A EP 0589338 A1 EP0589338 A1 EP 0589338A1
Authority
EP
European Patent Office
Prior art keywords
core tube
hub
pitch propeller
variable pitch
adjusting
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
EP93114801A
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German (de)
English (en)
Other versions
EP0589338B1 (fr
Inventor
Peter Müller
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Landolt Alexander Dr
Original Assignee
Landolt Alexander Dr
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Filing date
Publication date
Application filed by Landolt Alexander Dr filed Critical Landolt Alexander Dr
Publication of EP0589338A1 publication Critical patent/EP0589338A1/fr
Application granted granted Critical
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Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H3/00—Propeller-blade pitch changing
    • B63H3/008—Propeller-blade pitch changing characterised by self-adjusting pitch, e.g. by means of springs, centrifugal forces, hydrodynamic forces

Definitions

  • the invention relates to an adjustable propeller, in particular for sports boats, with a hub that can be placed on a drive shaft, wings held thereon, adjustable about radial axes, and adjusting tappets engaging on the wings, the free ends of which are connected to an adjusting device in the region of an end face of the hub.
  • the adjusting device includes a handwheel which is accessible from the free end face of the hub and with which the adjusting plunger and thus the blades can be adjusted in such a way that the pitch of the blades can be precisely adapted to the respective requirements.
  • variable pitch propellers have already been proposed in which the pitch of the wing is adjusted according to the centrifugal force (US Pat. No. 4,792,279) or the wing load (US Pat. No. 3,403,735).
  • the centrifugal force is only speed-dependent and the wing load can be subject to greater fluctuations, such systems do not work very precisely.
  • the object of the invention is to provide a self-adjusting propeller, in which the wing pitch changes independently of centrifugal forces and wing load.
  • a core tube attachable to the drive shaft is provided, that the hub is mounted on the core tube and rotatable between stops relative to the core tube, that a return spring is arranged between the core tube and the hub, and that a between the core tube and the adjusting plunger Gear is provided that adjusts the adjustment plunger and thus the wing according to the relative rotation between the core tube and the hub.
  • the speed of the drive shaft with the core tube attached to it increases faster than the speed of the variable pitch propeller, which is braked by water resistance and inertia.
  • the resulting relative movement between the core tube and the hub is then used to reduce the pitch of the wing for the purpose of improving boat acceleration. If the engine speed and thus the speed of the drive shaft are reduced while driving, there is also a relative rotation between the core tube and the hub with a corresponding change in the pitch of the wing.
  • a preferred embodiment of the invention is characterized in that the core tube carries a gear at its free end, the adjusting tappets carry pinions at their free ends which are in engagement with the gear, and that each adjusting tappet carries a worm in the area of the associated wing which is engaged with a worm wheel of the wing.
  • the maximum possible change in the pitch of the wing can be set by appropriate design of the gear and worm gear and the stops determining the maximum size of the relative rotation.
  • a return spring acting in the circumferential direction between the core tube and the hub can be arranged.
  • Another embodiment of the invention is characterized in that the hub is also axially displaceably mounted on the core tube, that a link guide is provided between the hub and the core tube and that the core tube carries a circumferential groove at its free end for guiding the adjusting plunger.
  • This version is particularly suitable for variable pitch propellers in which the adjusting plungers are arranged to be displaceable in the axial direction (US Pat. No. 4,897,056) and are set up at their free ends in the region of an end face of the hub for the connection of an adjusting device.
  • the link guide can in particular be designed as a thread guide between the hub and the core tube.
  • the return spring can be a helical spring acting in the axial direction between the core tube and the hub.
  • a damping device acting between the core tube and the hub can have two working spaces filled with pressure medium with an associated piston arrangement, which are connected to one another via a bypass line, a throttle being arranged in the bypass line.
  • the throttle should preferably be adjustable.
  • the damping device makes it possible to optimize the timing of the change in gradient with a view to quickly reaching the maximum boat speed.
  • bypass line can be closed with a valve element which is supported on a spring in the radial direction, i.e. works dependent on centrifugal force, it is possible, by appropriate design of the system of valve element and spring, to set up the conditions so that the self-adjusting properties of the variable pitch propeller become apparent can become active above a certain speed of the drive shaft.
  • the return spring between the core tube and the hub, because if a strong return spring is used, a significant relative rotation between the core tube and the hub only occurs when the drive shaft has a correspondingly high rotational acceleration.
  • the return spring also serves to return the wing pitch back to its starting position when the engine is switched off or at low driving speed. In order to accelerate this, a further bypass line can be provided between the work rooms, which has a check valve.
  • FIG. 1 shows a drive shaft 1 which can be driven by a motor (not shown) and on which a core tube 2 is fastened in a manner known per se.
  • a hub 3 of the adjustable propeller is rotatably and axially displaceable between stops, not shown.
  • the hub 3 has recesses 4 arranged on its outer circumference with the same mutual spacing for wing feet 5 of wings 6 arranged thereon.
  • the wings 6 are adjustable about radial axes for the purpose of changing the slope.
  • the wing feet 5 are screwed by screws 7 to the associated adjustment plates 8, which in their assigned recesses 4 With the help of screwed retaining rings 9 are rotatably held and guided.
  • Each adjustment plate 8 has on its underside a guide groove 10, in which a pin 12 provided with a sliding block 11 engages.
  • the pin 12 is part of an adjusting plunger 13 which is slidably guided in an axial bore 14 of the handle 3.
  • the adjusting plungers 13 carry seals 16 for sealing the space around the adjusting plates 8 and are connected to one another at their end 17 protruding from the bore 14 by a synchronous flange 17 which is fastened to the ends 16 with nuts 18.
  • the core tube 2 has at its free end an external thread 19 for a nut 20 and a counter nut 21 braced therewith.
  • the nut 20 and the counter nut 21 define a circumferential groove 22 in which the synchronous flange 17 is held axially immovable but rotatable. Accordingly, when the hub 3 is axially displaced relative to the core tube 2, the adjusting plungers 13 are moved axially, which in the process change the pitch of their associated vanes 6.
  • the hub 3 which is rotatably and axially displaceably mounted on the core tube 2, is supported on the core tube 2 via a return spring 23.
  • the return spring 23 is a helical spring surrounding the core tube 2 in the embodiment shown, which is accommodated in circumferential recesses 24 of the core tube 2 and the hub 3 and the free ends of which are held in associated axial bores 25 of the hub 3 or the core tube 2, so that the Return spring 23 can apply restoring forces both in the axial direction and in the circumferential direction.
  • a link guide is provided between the core tube 2 and the hub 3, to which in the illustrated Execution include an external thread 26 of the core tube and an associated internal thread 27 of the hub 3.
  • the end 28 of the core tube 2 lying to the right of the external thread 26 in FIG. 2 has an external diameter that is reduced compared to the external thread 26.
  • a radial flange 29 is screwed to the corresponding end face of the hub 3 and carries a seal 30 which cooperates with the outer circumference of the end 28.
  • a hydraulic damping device is arranged between the external thread 26 of the core tube 2 and its end 28, which includes two working spaces 31, 32 which are designed as circumferential grooves and are filled with a hydraulic fluid and which are connected to one another via a bypass line 33.
  • the bypass line 33 can be closed more or less with the aid of an adjustable throttle element 34.
  • the throttle element 34 is accommodated in an axial bore 35 of the hub 3 and held therein with the aid of a threaded section which is not shown for reasons of scale.
  • the throttle element 34 can be adjusted in the direction of the bypass line 3 by inserting a suitable tool into the axial bore 35.
  • the radial flange 29 penetrates into the working space 32 and displaces the hydraulic fluid therein into the other working space 31 and / or the thread sections adjoining it, which functionally relate to the working space 31 belong.
  • the throttle element 34 controls the flow rate of the hydraulic fluid through the bypass line 33.
  • the bypass line 33 is closed by a valve element 36 which is supported in the radial direction on a spring 37.
  • the valve element 36 and its spring 37 are designed so that the bypass line 33 is only opened above a certain speed.
  • bypass line 38 is intended to enable the hub 3 and thus the pitch of the wing to be quickly returned to the starting position under the action of the return spring 23.
  • variable pitch propeller so far works as follows: At low speeds, the system remains inactive. Only above a certain speed, which can be determined by the action of centrifugal force on the valve element 36, is a sudden increase in the speed of the drive shaft 1 a relative movement between the core tube 2 and the hub 3, because the hub 3 due to its inertia and to the vanes 6 acting hydrodynamic forces of the rotational acceleration of the drive shaft 1 can not follow.
  • the relative rotation of the hub 3 with respect to the core tube and the resulting axial displacement of the hub 3 also leads to a change in the pitch of the vanes 6 because the adjusting plungers 13 are held on the core tube 2.
  • the adjustment speed is optimized by the damping device. When resetting under the influence of the return spring 23, the adjustment speed can be greater because the hydraulic fluid can flow off via the bypass line 38 with the check valve 39.
  • the hub 3 need only be relatively rotatable relative to the core tube 2, but not axially adjustable, so that the gear arrangement 26, 27 between the core tube 2 and the hub 3 can be omitted.
  • the core tube 2 carries at its free end a gear 40 which engages with pinions 41 at the free ends of the adjusting plungers 13.
  • the adjusting plungers 13 are rotatably mounted and carry at their ends facing the wing feet a worm 42 which are connected to a worm wheel 43 formed on the outer circumference of the adjusting plate 8 or connected to the adjusting plate 8.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Fluid-Damping Devices (AREA)
EP93114801A 1992-09-23 1993-09-15 Hélice à pas variable, spécialement pour bateaux de sport Expired - Lifetime EP0589338B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4231814 1992-09-23
DE4231814A DE4231814C1 (de) 1992-09-23 1992-09-23 Verstellpropeller, insbesondere für Sportboote

Publications (2)

Publication Number Publication Date
EP0589338A1 true EP0589338A1 (fr) 1994-03-30
EP0589338B1 EP0589338B1 (fr) 1997-04-02

Family

ID=6468612

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93114801A Expired - Lifetime EP0589338B1 (fr) 1992-09-23 1993-09-15 Hélice à pas variable, spécialement pour bateaux de sport

Country Status (3)

Country Link
US (1) US5366343A (fr)
EP (1) EP0589338B1 (fr)
DE (1) DE4231814C1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19936948C1 (de) * 1999-08-05 2001-01-25 Peter Mueller Verstellpropeller für Motorboote und Sportboote
KR101045044B1 (ko) 2009-08-20 2011-06-29 주식회사 디.에스.케이 가변피치 프로펠러의 개선된 에어 체크 밸브 조립 구조
WO2024079265A1 (fr) 2022-10-12 2024-04-18 Rotors, Drones & More Multicoptère et dispositif de robot pour un multicoptère

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5810561A (en) * 1997-04-21 1998-09-22 Cossette; Thomas C. Variable pitch propeller apparatus
US5967753A (en) * 1998-09-28 1999-10-19 Muller; Peter Controllable-pitch propeller, especially for sport boats and other watercraft
DE19906661C1 (de) * 1999-02-18 2000-06-29 Peter Mueller Verstellpropeller, insbesondere für Motor- und Sportboote
US8790081B1 (en) 2007-11-02 2014-07-29 Auburn University Constant torque propeller mechanism

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1864045A (en) * 1931-11-02 1932-06-21 Bert F Kellogg Variable speed propeller
US3145780A (en) * 1962-01-12 1964-08-25 Angelo J Roncari Variable pitch propeller
GB1106586A (en) * 1965-10-24 1968-03-20 Robert Frias Apparatus for automatic propeller pitch control
GB2145479A (en) * 1983-08-23 1985-03-27 John Raymond Roat Load sensing marine propellor
WO1992019493A1 (fr) * 1991-04-26 1992-11-12 Nautical Development, Inc. Helice de navire a changement de pas automatique amorti

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1765091A (en) * 1929-03-11 1930-06-17 Morris Louis Automatic variable-pitch propeller blade for airplanes
US1980248A (en) * 1930-09-27 1934-11-13 Bendix Res Corp Automatic variable pitch propeller
US1980249A (en) * 1931-04-23 1934-11-13 Bendix Res Corp Propeller
US2075682A (en) * 1935-03-08 1937-03-30 C L W Aviat Company Ltd Screw propeller
US2468004A (en) * 1944-04-01 1949-04-19 Robert Brooks Keller Automatic propeller pitch changing mechanism
BE475628A (fr) * 1946-07-18
DE834207C (de) * 1950-01-15 1952-03-17 Wilhelm Wels Umsteuer- und Verstellschraube mit Fluegelverstellung durch die Kraft der Antriebsmaschine
US3362479A (en) * 1965-10-19 1968-01-09 Avco Corp Drive shaft assembly
US3403735A (en) * 1967-03-10 1968-10-01 Henrik G. Langhjelm Adjustable variable pitch propeller
DE2346912A1 (de) * 1973-09-18 1975-03-27 Hans Bals Bootsschraube
US3915590A (en) * 1974-08-12 1975-10-28 Prime Mover Controls Ltd Propeller pitch control apparatus
US4140434A (en) * 1975-12-29 1979-02-20 Massimiliano Bianchi Feathering propeller especially for sailing boats
EP0297162B1 (fr) * 1987-07-03 1991-09-18 Peter Müller Hélice à pas variable pour engins flottants
US4792279A (en) * 1987-09-04 1988-12-20 Bergeron Robert M Variable pitch propeller

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1864045A (en) * 1931-11-02 1932-06-21 Bert F Kellogg Variable speed propeller
US3145780A (en) * 1962-01-12 1964-08-25 Angelo J Roncari Variable pitch propeller
GB1106586A (en) * 1965-10-24 1968-03-20 Robert Frias Apparatus for automatic propeller pitch control
GB2145479A (en) * 1983-08-23 1985-03-27 John Raymond Roat Load sensing marine propellor
WO1992019493A1 (fr) * 1991-04-26 1992-11-12 Nautical Development, Inc. Helice de navire a changement de pas automatique amorti

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19936948C1 (de) * 1999-08-05 2001-01-25 Peter Mueller Verstellpropeller für Motorboote und Sportboote
EP1074463A2 (fr) 1999-08-05 2001-02-07 Peter Müller Hélice à pas variable pour bateaux de loisirs à moteur
US6352410B1 (en) 1999-08-05 2002-03-05 Nasyc Holding S.A. Variable-pitch boat propeller with easy-change vanes
EP1074463A3 (fr) * 1999-08-05 2002-12-18 Nasyc Holding S.A. Hélice à pas variable pour bateaux de loisirs à moteur
KR101045044B1 (ko) 2009-08-20 2011-06-29 주식회사 디.에스.케이 가변피치 프로펠러의 개선된 에어 체크 밸브 조립 구조
WO2024079265A1 (fr) 2022-10-12 2024-04-18 Rotors, Drones & More Multicoptère et dispositif de robot pour un multicoptère
DE102022126535A1 (de) 2022-10-12 2024-04-18 Universität Stuttgart, Körperschaft Des Öffentlichen Rechts Multicopter, sowie Rotoreinrichtung für einen Multicopter

Also Published As

Publication number Publication date
US5366343A (en) 1994-11-22
DE4231814C1 (de) 1994-01-20
EP0589338B1 (fr) 1997-04-02

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