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EP2292510A1 - Jet propulsion - Google Patents

Jet propulsion Download PDF

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Publication number
EP2292510A1
EP2292510A1 EP10015423A EP10015423A EP2292510A1 EP 2292510 A1 EP2292510 A1 EP 2292510A1 EP 10015423 A EP10015423 A EP 10015423A EP 10015423 A EP10015423 A EP 10015423A EP 2292510 A1 EP2292510 A1 EP 2292510A1
Authority
EP
European Patent Office
Prior art keywords
rotor
bearing
housing
drive according
ring
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.)
Withdrawn
Application number
EP10015423A
Other languages
German (de)
French (fr)
Inventor
Dirk Büchler
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.)
Voith Turbo Advanced Propeller Technologies GmbH and Co KG
Original Assignee
Air Fertigung Technologie GmbH and Co KG
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 Air Fertigung Technologie GmbH and Co KG filed Critical Air Fertigung Technologie GmbH and Co KG
Publication of EP2292510A1 publication Critical patent/EP2292510A1/en
Withdrawn legal-status Critical Current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
    • B63H11/00—Marine propulsion by water jets
    • B63H11/02—Marine propulsion by water jets the propulsive medium being ambient water
    • B63H11/04—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps
    • B63H11/08—Marine propulsion by water jets the propulsive medium being ambient water by means of pumps of rotary type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H1/00—Propulsive elements directly acting on water
    • B63H1/02—Propulsive elements directly acting on water of rotary type
    • B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
    • B63H1/14—Propellers
    • B63H1/16—Propellers having a shrouding ring attached to blades
    • B63H2001/165—Hubless propellers, e.g. peripherally driven shrouds with blades projecting from the shrouds' inside surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H23/00—Transmitting power from propulsion power plant to propulsive elements
    • B63H2023/005—Transmitting power from propulsion power plant to propulsive elements using a drive acting on the periphery of a rotating propulsive element, e.g. on a dented circumferential ring on a propeller, or a propeller acting as rotor of an electric motor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H23/00—Transmitting power from propulsion power plant to propulsive elements
    • B63H23/22—Transmitting power from propulsion power plant to propulsive elements with non-mechanical gearing
    • B63H23/24—Transmitting power from propulsion power plant to propulsive elements with non-mechanical gearing electric

Definitions

  • the invention relates to a jet propulsion, in particular for watercraft.
  • WO 2005/049420 will be referred.
  • Such jet drives a plurality of rotor blades are arranged on the inner circumference of the rotor, which extend up to the region of the axis of rotation of the rotor and leave there a space. The free ends of the rotor blades thus do not touch, and there is no hub provided. Furthermore, such a jet drive comprises a housing in which the rotor is rotatably mounted. The rotor is associated with an electric motor with rotor ring and stator ring. Rotor ring and stator are arranged coaxially with the rotor, and the rotor ring is rotatably connected to the rotor.
  • jet drives have numerous advantages over conventional jet drives. They are of relatively simple construction, therefore inexpensive to manufacture, and also have a relatively low efficiency. Nevertheless, such jet drives can be improved, in particular with regard to the efficiency,
  • the invention has for its object to design a jet drive of the type mentioned in such a way that the efficiency compared to previously known jet drives of this type is improved.
  • a jet drive of the known type is carried out in a tandem arrangement, two rotors are used and two electric motors, which are each arranged axially adjacent to each other as a unit. It can be provided a single housing that encloses the two units in the axial direction.
  • tandem arrangement results in a higher energy yield during operation.
  • the efficiency is thus greater than in a single jet propulsion with only a single unit of rotor and electric motor.
  • tandem design according to the invention is more flexible in operation. So you do not have to operate both units at the same time. Rather, one or the other unit can be switched off or then switched on.
  • a special rule is provided. This allows the speeds of the rotors of individual units to be controlled independently of each other. It can thus be selected for any driving conditions, the rotational speeds of the rotors of individual units, that is guaranteed for the overall system torque. This makes it possible to optimize the efficiency for any driving conditions. It is possible to achieve an efficiency maximum for the entire system.
  • a load shift from a front to a rear rotor can be made with increasing speed.
  • the increase in pressure experienced by the rear propeller minimizes the risk of cavitation.
  • FIG. 1 shows the leaves 1 of the rotor of the first of the two units. In this case, there are seven leaves. But it could also be more or less. As you can see, the free ends of the leaves point to the center of the jet unit, leaving a space between the free ends.
  • FIG. 2 you realize that these are two units. It can also be seen from some of the leaves of the two jet units, namely again leaves 1 of the first unit and leaves 2 of the second unit
  • Each unit comprises the following components: a rotor 3 or 4, on which the blades 1 and 2 are fixed, a rotor ring 5 and 6 and a stator 7 and 8, respectively, which is embedded in a housing 9 and 10 respectively.
  • a rotor 3 or 4 on which the blades 1 and 2 are fixed
  • a rotor ring 5 and 6 and a stator 7 and 8, respectively, which is embedded in a housing 9 and 10 respectively.
  • the two housings 9, 10 could also consist of a single part.
  • a spacer flange 11 is provided between the two units.
  • a bearing flange 12 and 13 is provided at the outer ends of the two housings.
  • the axial distance between the two rotors should be as small as possible. It is therefore desirable to dimension the said spacer flange 11 in the axial direction as small as possible. It could for example consist of a very thin sheet, which is only a few millimeters thick, for example 1 to 3 mm, or less than 1 mm, for example 0.5 to 1.0 mm.
  • the axial distance should generally be less than 10 percent of the axial rotor size.
  • the two electric motors are designed so that they rotate in opposite directions. This is structurally well feasible in the design of the jet propulsion system chosen here, because this unit is hullless.
  • tandem design according to the invention has great advantage in terms of efficiency. This is much higher than with a correspondingly sized single jet propulsion.
  • FIG. 3 shows details of another embodiment of the jet propulsion system according to the invention somewhat more precisely.
  • the rotor blades are omitted for greater clarity. It can be seen again the two rotors 3 and 4, with these rotatably connected rotor rings 5 and 6 and the stator 7 and 8, respectively. The whole is enclosed by a housing 9 and 10 respectively.
  • the bearings play an important role.
  • the jet engine is completely flooded.
  • the bearings are made of seawater-proof carbide.
  • the structure of the bearings can be identified FIG. 4 , See there the bearing segments 14, 15 which are embedded in the housing 9 and 10 respectively.
  • the bearing segments 14, 15 are dovetail-shaped in cross-section, and the housing has corresponding recesses.
  • the bearing segments 14, 15 can be arranged at a certain mutual distance d.
  • Two or more units can be connected axially in series. There are therefore also three or four or more units into consideration.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Surgical Instruments (AREA)
  • Percussion Or Vibration Massage (AREA)

Abstract

The jet propulsion comprises two or more units which are arranged axially one behind the other. The unit has a rotor (3,4) without a hub, on which internal circumference rotor blades (1,2) are fixed. A housing (9,10) is provided in which the rotor is mounted such that it can rotate. The rotor is surrounded by an electric motor with a rotor ring (5,6) and a stator ring (7,8). The rotor ring is connected to the rotor such that they rotate together. The bearing between the rotor and the housing has carbide e.g. silicon carbide or aluminum carbide.

Description

Die Erfindung betrifft einen Strahlantrieb, insbesondere für Wasserfahrzeuge. Auf WO 2005/049420 wird verwiesen.The invention relates to a jet propulsion, in particular for watercraft. On WO 2005/049420 will be referred.

Bei solchen Strahlantrieben sind am Innenumfang des Rotors mehrere Rotorblätter angeordnet, die sich bis zum Bereich der Drehachse des Rotors hin erstrecken und dort einen Raum freilassen. Die freien Enden der Rotorblätter berühren sich somit nicht, und es ist auch keine Nabe vorgesehen. Ferner umfasst ein solcher Strahlantrieb ein Gehäuse, in dem der Rotor drehbar gelagert ist. Dem Rotor ist ein Elektromotor mit Läuferring und Statorring zugeordnet. Läuferring und Statorring sind koaxial zu dem Rotor angeordnet, und der Läuferring ist mit dem Rotor drehfest verbunden.In such jet drives a plurality of rotor blades are arranged on the inner circumference of the rotor, which extend up to the region of the axis of rotation of the rotor and leave there a space. The free ends of the rotor blades thus do not touch, and there is no hub provided. Furthermore, such a jet drive comprises a housing in which the rotor is rotatably mounted. The rotor is associated with an electric motor with rotor ring and stator ring. Rotor ring and stator are arranged coaxially with the rotor, and the rotor ring is rotatably connected to the rotor.

Solche Strahlantriebe haben gegenüber konventionellen Strahlantrieben zahlreiche Vorteile. Sie sind von verhältnismäßig einfachem Aufbau, daher kostengünstig in der Herstellung, und haben außerdem einen relativ günstigen Wirkungsgrad. Gleichwohl sind derartige Strahlantriebe verbesserungsfähig, insbesondere was den Wirkungsgrad anbetrifft,Such jet drives have numerous advantages over conventional jet drives. They are of relatively simple construction, therefore inexpensive to manufacture, and also have a relatively low efficiency. Nevertheless, such jet drives can be improved, in particular with regard to the efficiency,

Der Erfindung liegt die Aufgabe zugrunde, einen Strahlantrieb der genannten Bauart derart zu gestalten, dass der Wirkungsgrad gegenüber bisher bekannten Strahlantrieben dieser Bauart verbessert wird.The invention has for its object to design a jet drive of the type mentioned in such a way that the efficiency compared to previously known jet drives of this type is improved.

Diese Aufgabe wird durch die Merkmale von Anspruch 1 gelöst.This object is solved by the features of claim 1.

Demgemäß wird ein Strahlantrieb der bekannten Bauart in einer Tandemanordnung ausgeführt, Dabei werden zwei Rotoren verwendet sowie zwei Elektromotoren, die jeweils als eine Einheit axial nebeneinander angeordnet sind. Es kann ein einziges Gehäuse vorgesehen werden, dass die beiden Einheiten in axialer Richtung umschließt.Accordingly, a jet drive of the known type is carried out in a tandem arrangement, two rotors are used and two electric motors, which are each arranged axially adjacent to each other as a unit. It can be provided a single housing that encloses the two units in the axial direction.

Durch die Tandemanordnung ergibt sich während des Betriebes eine höhere Energieausbeute. Der Wirkungsgrad ist somit größer, als bei einem Einzel-Strahlantrieb mit nur einer einzigen Einheit aus Rotor und Elektromotor. Außerdem ist die erfindungsgemäße Tandem-Bauart flexibler im Betrieb. So müssen nicht beide Einheiten gleichzeitig betrieben werden. Vielmehr kann die eine oder die andere Einheit abgeschaltet beziehungsweise sodann zugeschaltet werden.The tandem arrangement results in a higher energy yield during operation. The efficiency is thus greater than in a single jet propulsion with only a single unit of rotor and electric motor. In addition, the tandem design according to the invention is more flexible in operation. So you do not have to operate both units at the same time. Rather, one or the other unit can be switched off or then switched on.

Gemäß einem weiteren Gedanken wird eine besondere Regelung vorgesehen. Hiermit lassen sich die Drehzahlen der Rotoren einzelner Einheiten unabhängig voneinander regeln. Es können damit für beliebige Fahrzustände die Drehzahlen der Rotoren einzelner Einheiten derart gewählt werden, dass für das Gesamtsystem Drehmomentenfreiheit gewährleistet ist. Damit lässt sich für beliebige Fahrzustände der Wirkungsgrad optimieren. Es lässt sich für das gesamte System ein Wirkungsgrad-Maximum erzielen.According to another idea, a special rule is provided. This allows the speeds of the rotors of individual units to be controlled independently of each other. It can thus be selected for any driving conditions, the rotational speeds of the rotors of individual units, that is guaranteed for the overall system torque. This makes it possible to optimize the efficiency for any driving conditions. It is possible to achieve an efficiency maximum for the entire system.

Dies ist insbesondere vorteilhaft für ein Schiff, dessen Betriebsbedingungen stark verändert werden.This is particularly advantageous for a ship whose operating conditions are greatly changed.

Bei schnell fahrenden Wasserfahrzeugen ist auch die folgende Regelung möglich: Es lässt sich eine Lastverschiebung von einem vorderen auf einen hinteren Rotor mit zunehmender Geschwindigkeit vornehmen. Durch den Druckzuwachs, den der hintere Propeller damit erfährt, lässt sich die Kavitationsgefahr minimieren.In the case of fast-moving vessels, the following control is also possible: A load shift from a front to a rear rotor can be made with increasing speed. The increase in pressure experienced by the rear propeller minimizes the risk of cavitation.

Auch ist es möglich, das hintere Axiallager eines in Fahrtrichtung gesehen vorderen Rotors gegen das vordere Axiallager eines in Fahrtrichtung hinteren Rotors laufen zu lassen. Hierdurch lässt sich eine höhere Relativgeschwindigkeit im Lager erzielen. Lagergröße und baulicher Aufwand lassen sich damit reduzieren.It is also possible to run the rear thrust bearing of a front rotor seen in the direction of travel against the front thrust bearing of a rear rotor in the direction of travel. As a result, a higher relative speed can be achieved in the camp. Bearing size and construction costs can be reduced.

Die Erfindung ist anhand der Zeichnung näher erläutert. Darin ist im einzelnen folgendes dargestellt:

Figur 1
zeigt einen Strahlantrieb in einer achssenkrechten Ansicht,
Figur 2
zeigt den Gegenstand von Figur 1 in einem Axialschnitt, und zwar gemäß der Schnittlinie A - A in Figur 1.
Figur 3
zeigt wiederum einen Axialschnitt durch einen Strahlantrieb mit zwei Einheiten im Ausschnitt.
Figur 4
zeigt in einer perspektivischen, vergrößerten Darstellung einen Ausschnitt aus dem Lagerbereich.
The invention is explained in more detail with reference to the drawing. The following is shown in detail:
FIG. 1
shows a jet propulsion in an axially perpendicular view,
FIG. 2
shows the item of FIG. 1 in an axial section, according to the section line A - A in FIG. 1 ,
FIG. 3
again shows an axial section through a jet drive with two units in the cutout.
FIG. 4
shows in a perspective, enlarged view a section of the storage area.

Figur 1 zeigt die Blätter 1 des Rotors der ersten der beiden Einheiten. Im vorliegenden Falle handelt es sich um sieben Blätter. Es könnten aber auch mehr oder weniger sein. Wie man sieht, weisen die freien Enden der Blätter auf das Zentrum der Strahleinheit, so dass zwischen den freien Enden ein Freiraum verbleibt. FIG. 1 shows the leaves 1 of the rotor of the first of the two units. In this case, there are seven leaves. But it could also be more or less. As you can see, the free ends of the leaves point to the center of the jet unit, leaving a space between the free ends.

Aus Figur 2 erkennt man, dass es sich um zwei Einheiten handelt. Hieraus sind auch einige der Blätter der beiden Strahleinheiten zu erkennen, nämlich wiederum Blätter 1 der ersten Einheit und Blätter 2 der zweiten EinheitOut FIG. 2 you realize that these are two units. It can also be seen from some of the leaves of the two jet units, namely again leaves 1 of the first unit and leaves 2 of the second unit

Jede Einheit weist die folgenden Bauteile auf: einen Rotor 3 beziehungsweise 4, an dem die Blätter 1 beziehungsweise 2 fixiert sind, einen Läuferring 5 beziehungsweise 6 sowie einen Statorring 7 beziehungsweise 8, der jeweils in ein Gehäuse 9 beziehungsweise 10 eingelassen ist. Außerdem erkennt man den Fuß 1.1 beziehungsweise 2.1 des einzelnen Blattes.Each unit comprises the following components: a rotor 3 or 4, on which the blades 1 and 2 are fixed, a rotor ring 5 and 6 and a stator 7 and 8, respectively, which is embedded in a housing 9 and 10 respectively. In addition, one recognizes the foot 1.1 or 2.1 of the single sheet.

Alle diese Bautelle, somit Fuß des Blattes, Rotor 3 beziehungsweise 4, Läuferring 5 beziehungsweise 6 und Statorring 7 beziehungsweise 8 sind koaxial zueinander angeordnet. Der Läuferring ist mit dem Rotor drehfest verbunden. Zwischen dem Läuferring und dem Statorring herrscht ein Luftspalt von minimaler Weite.All of these construction cell, thus foot of the blade, rotor 3 or 4, rotor ring 5 or 6 and stator 7 and 8 are arranged coaxially with each other. The rotor ring is rotatably connected to the rotor. There is an air gap of minimal width between the rotor ring and the stator ring.

Die beiden Gehäuse 9, 10 könnten auch aus einem einzigen Teil bestehen.The two housings 9, 10 could also consist of a single part.

Zwischen den beiden Einheiten ist ein Abstandsflansch 11 vorgesehen, An den äußeren Enden der beiden Gehäuse ist wiederum ein Lagerflansch 12 beziehungsweise 13 vorgesehen.Between the two units, a spacer flange 11 is provided, At the outer ends of the two housings, in turn, a bearing flange 12 and 13 is provided.

Der axiale Abstand zwischen den beiden Rotoren sollte so klein wie möglich sein. Es ist daher wünschenswert, den genannten Abstandsflansch 11 in axialer Richtung möglichst klein zu bemessen. Er könnte beispielsweise aus einem ganz dünnen Blech bestehen, das nur wenige Millimeter stark ist, beispielsweise 1 bis 3 mm, oder kleiner als 1 mm, beispielsweise 0,5 bis 1,0 mm.The axial distance between the two rotors should be as small as possible. It is therefore desirable to dimension the said spacer flange 11 in the axial direction as small as possible. It could for example consist of a very thin sheet, which is only a few millimeters thick, for example 1 to 3 mm, or less than 1 mm, for example 0.5 to 1.0 mm.

Der axiale Abstand sollte ganz allgemein kleiner als 10 Prozent des axialen Rotormaßes sein.The axial distance should generally be less than 10 percent of the axial rotor size.

Die beiden Elektromotoren sind derart ausgelegt, dass sie in gegenläufigem Drehsinn umlaufen. Dies ist bei der hier gewählten Bauweise des Strahlantriebes konstruktiv gut verwirklichbar, weil diese Baueinheit nämlich nabenlos ist.The two electric motors are designed so that they rotate in opposite directions. This is structurally well feasible in the design of the jet propulsion system chosen here, because this unit is hullless.

Die erfindungsgemäße Tandem-Bauart hat große Vorteil bezüglich des Wirkungsgrades. Dieser ist wesentlich höher, als bei einem entsprechend bemessenen Einzel-Strahlantrieb.The tandem design according to the invention has great advantage in terms of efficiency. This is much higher than with a correspondingly sized single jet propulsion.

Figur 3 zeigt Einzelheiten einer weiteren Ausführungsform des erfindungsgemäßen Strahlantriebes etwas genauer. Dabei sind die Rotorblätter der größeren Klarheit wegen weggelassen. Man erkennt wiederum die beiden Rotoren 3 beziehungsweise 4, die mit diesen drehfest verbundenen Läuferringe 5 beziehungsweise 6 sowie die Statorringe 7 beziehungsweise 8. Das Ganze ist von einem Gehäuse 9 beziehungsweise 10 umschlossen. FIG. 3 shows details of another embodiment of the jet propulsion system according to the invention somewhat more precisely. The rotor blades are omitted for greater clarity. It can be seen again the two rotors 3 and 4, with these rotatably connected rotor rings 5 and 6 and the stator 7 and 8, respectively. The whole is enclosed by a housing 9 and 10 respectively.

Eine wichtige Rolle spielen die Lager. Der Strahlantrieb ist völlig geflutet. Die Lager bestehen aus seewasserfestem Carbid. Den Aufbau der Lager erkennt man aus Figur 4. Siehe dort die Lagersegmente 14, 15 die in das Gehäuse 9 beziehungsweise 10 eingelassen sind. Die Lagersegmente 14, 15 sind im Querschnitt schwalbenschwanzförmig, und das Gehäuse hat entsprechende Aussparungen.The bearings play an important role. The jet engine is completely flooded. The bearings are made of seawater-proof carbide. The structure of the bearings can be identified FIG. 4 , See there the bearing segments 14, 15 which are embedded in the housing 9 and 10 respectively. The bearing segments 14, 15 are dovetail-shaped in cross-section, and the housing has corresponding recesses.

Je nachdem, ob eine Durchspülung am Gehäuselager vorgesehen ist oder nicht, können die Lagersegmente 14, 15 in einem gewissen gegenseitigen Abstand d angeordnet werden.Depending on whether a flushing is provided on the housing bearing or not, the bearing segments 14, 15 can be arranged at a certain mutual distance d.

Ist dies der Fall, so werden die Nuten zwischen den Lagersegmenten ständig durchspült, was eine zusätzliche Kühlung der Lagerung des Elektromotores bedeutet.If this is the case, the grooves between the bearing segments are constantly flushed through, which means additional cooling of the bearing of the electric motor.

Es können zwei oder mehrere Einheiten axial hintereinander geschaltet werden. Es kommen somit auch drei oder vier oder noch mehr Einheiten In Betracht.Two or more units can be connected axially in series. There are therefore also three or four or more units into consideration.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Rotorblattrotor blade
1.11.1
Fuß des RotorblattesFoot of the rotor blade
22
Rotorblattrotor blade
2.12.1
Fuß des RotorblattesFoot of the rotor blade
33
Rotorrotor
44
Rotorrotor
55
Läuferringrotor ring
88th
Läuferringrotor ring
77
Statorringstator
88th
Statorringstator
99
Gehäusecasing
1010
Gehäusecasing
1111
Abstandsflanschspacer flange
1212
LagerflanschLagerflansch
1313
LagerflanschLagerflansch
1414
Lagersegmentebearing segments
1515
Lagersegmentebearing segments

Claims (6)

Strahlantrieb 1.1 umfassend zwei oder mehrere axial hintereinander angeordnete Einheiten; 1.2 jede Einheit weist die folgenden Bauteile beziehungsweise Merkmale auf: - einen nabenlosen Rotor (3, 4), an dessen Innenumfang Rotorblätter (1, 2) fixiert sind; - ein Gehäuse (9, 10), in dem der Rotor (3, 4) drehbar gelagert ist; - jeder Rotor (3, 4) ist von einem Elektromotor mit Läuferring (5, 6) und Statorring (7, 8) umschlossen; - der Läuferring (5, 6) ist mit dem Rotor (3, 4) drehfest verbunden; 1.3 die beiden Elektromotoren sind für einander entgegengesetzte Drehrichtungen ausgelegt. jet propulsion 1.1 comprising two or more axially successively arranged units; 1.2 each unit has the following components or characteristics: - A hubless rotor (3, 4), on whose inner circumference rotor blades (1, 2) are fixed; - A housing (9, 10) in which the rotor (3, 4) is rotatably mounted; - Each rotor (3, 4) by an electric motor with rotor ring (5, 6) and stator ring (7, 8) enclosed; - The rotor ring (5, 6) is rotatably connected to the rotor (3, 4); 1.3 the two electric motors are designed for opposite directions of rotation. Strahlantrieb nach Anspruch 1, dadurch gekennzeichnet, dass die Lagerung zwischen Rotor (3, 4) und Gehäuse (9, 10) seewasserfestes Carbid, bevorzugt Siliciumcarbid oder Aluminiumcarbid, aufweist.Jet drive according to claim 1, characterized in that the bearing between the rotor (3, 4) and housing (9, 10) seawater-solid carbide, preferably silicon carbide or aluminum carbide having . Strahlantrieb nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass die Lagerung zwischen Rotor (3, 4) und Gehäuse (9, 10) ausschließlich aus Carbid besteht.Jet drive according to one of claims 1 to 2, characterized in that the bearing between the rotor (3, 4) and housing (9, 10) consists exclusively of carbide. Strahlantrieb nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Lagerung aus Gleitlagern gebildet ist.Jet drive according to one of claims 1 to 3, characterized in that the bearing is formed of plain bearings. Strahlantrieb nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Drehzahlen der Rotoren (3, 4) der Einheiten unabhängig voneinander regelbar sind.Jet drive according to one of claims 1 to 4, characterized in that the rotational speeds of the rotors (3, 4) of the units are independently controllable. Strahlantrieb nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das hintere Axiallager eines in Fahrtrichtung gesehen vorderen Propellers gegen das vordere Lager eines in Fahrtrichtung gesehen hinteren Propellers läuft.Jet drive according to one of claims 1 to 5, characterized in that the rear thrust bearing seen in the direction of travel front Propellers running against the front bearing of a seen in the direction of travel rear propeller.
EP10015423A 2007-01-17 2008-01-16 Jet propulsion Withdrawn EP2292510A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007002519A DE102007002519A1 (en) 2007-01-17 2007-01-17 Strahlantireb
EP08707069A EP2109565B1 (en) 2007-01-17 2008-01-16 Jet propulsion

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP08707069.4 Division 2008-01-16

Publications (1)

Publication Number Publication Date
EP2292510A1 true EP2292510A1 (en) 2011-03-09

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP10015423A Withdrawn EP2292510A1 (en) 2007-01-17 2008-01-16 Jet propulsion
EP08707069A Not-in-force EP2109565B1 (en) 2007-01-17 2008-01-16 Jet propulsion

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Application Number Title Priority Date Filing Date
EP08707069A Not-in-force EP2109565B1 (en) 2007-01-17 2008-01-16 Jet propulsion

Country Status (4)

Country Link
EP (2) EP2292510A1 (en)
AT (1) ATE492466T1 (en)
DE (2) DE102007002519A1 (en)
WO (1) WO2008087020A1 (en)

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Publication number Priority date Publication date Assignee Title
ES2650986T3 (en) * 2008-05-27 2018-01-23 Siemens Aktiengesellschaft Turbomachine with at least two rotors
DE102009021548A1 (en) 2009-05-15 2010-11-25 Voith Patent Gmbh Jet drive with at least one drive unit
DE102010049493B4 (en) 2010-10-27 2020-12-10 Voith Patent Gmbh Tilting pad bearings
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EP2109565B1 (en) 2010-12-22
WO2008087020A1 (en) 2008-07-24
DE102007002519A1 (en) 2008-07-31
DE502008002069D1 (en) 2011-02-03
EP2109565A1 (en) 2009-10-21

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