EP3953588B1 - Jet pump - Google Patents

Jet pump Download PDF

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Publication number
EP3953588B1
EP3953588B1 EP20719576.9A EP20719576A EP3953588B1 EP 3953588 B1 EP3953588 B1 EP 3953588B1 EP 20719576 A EP20719576 A EP 20719576A EP 3953588 B1 EP3953588 B1 EP 3953588B1
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EP
European Patent Office
Prior art keywords
propellant
wall
medium
speed
jet pump
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.)
Active
Application number
EP20719576.9A
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German (de)
French (fr)
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EP3953588A1 (en
Inventor
Daniel Kintea
Lukasz Gabrys
Christian Kahl
Gerrit Von Breitenbach
Michal Sajdak
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Norma Germany GmbH
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Norma Germany GmbH
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Publication of EP3953588A1 publication Critical patent/EP3953588A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
    • F04F5/46—Arrangements of nozzles
    • F04F5/465—Arrangements of nozzles with supersonic flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
    • F04F5/46—Arrangements of nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/02—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being liquid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/02—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being liquid
    • F04F5/10—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being liquid displacing liquids, e.g. containing solids, or liquids and elastic fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/14—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/44—Component parts, details, or accessories not provided for in, or of interest apart from, groups F04F5/02 - F04F5/42
    • F04F5/46—Arrangements of nozzles
    • F04F5/464—Arrangements of nozzles with inversion of the direction of flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
    • F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
    • F04F5/54—Installations characterised by use of jet pumps, e.g. combinations of two or more jet pumps of different type

Definitions

  • the invention relates to a jet pump comprising a driving nozzle for accelerating a driving medium, the driving nozzle having a converging inlet part and an outlet part connected to the converging inlet part, the outlet part, according to the preamble of claim 1, having an interior space enclosed by an inner wall and diverging at an opening angle includes.
  • Jet pumps use a jet of fluid from a propellant medium to suck in and accelerate a suction medium.
  • the suction effect is caused by the propellant medium flowing past the suction medium, the suction medium being carried along by the propellant medium when the flow speed of the propellant medium is sufficiently high.
  • To accelerate a propellant medium it is passed under pressure through a nozzle that accelerates the propellant medium. If the suction pressure and the driving pressure have a subcritical pressure ratio have, a convergent nozzle is used to accelerate the propellant in the jet pump.
  • a convergent-divergent nozzle a so-called Laval nozzle
  • Laval nozzle results in a deceleration of flow velocity for propellant media flowing at subsonic speeds because the divergent section of the Laval nozzle acts as a diffuser for the propellant.
  • the object of the invention is to provide an improved jet pump that allows operation at subcritical and supercritical pressure conditions.
  • the invention relates to a jet pump comprising a driving nozzle for accelerating a
  • Propellant medium wherein the propellant nozzle has a converging inlet part and an outlet part connected to the converging inlet part, the outlet part comprising an interior enclosed by an inner wall that diverges at an opening angle, the inner wall defining the opening angle directly according to a narrowest cross section at an inlet opening of the interior
  • the opening angle is designed such that a propellant medium flowing through the outlet part at subsonic speed is separated from the inner wall, the outlet part (26) not acting as a diffuser for the propellant medium flowing at subsonic speed, and a propellant medium flowing through the outlet part at supersonic speed flowing propellant medium is guided by the inner wall, with the opening angle being more than 7° and a maximum of 45°.
  • the invention provides a jet pump with a driving nozzle, the convergent inlet part of which accelerates a propellant medium flowing through the convergent inlet part, the propellant medium flowing at subsonic speed before flowing through the inlet part. If the propellant medium continues to have subsonic speed after flowing through the inlet part and accelerating therein, it also flows through the outlet part at subsonic speed.
  • the outlet part of the driving nozzle has a divergent inner wall, that is, the cross section of the outlet part increases starting from the convergent inlet part.
  • the driving nozzle can be a specially designed Laval nozzle be. The opening angle of the divergent inner wall is so large that a propellant medium flowing through the outlet part at subsonic speed separates from the inner wall of the outlet part.
  • the outlet part of the propulsion nozzle works at subsonic speeds flowing propellant medium does not act as a diffuser, so that no delay in the speed of the propellant medium is caused when it flows through the outlet part. Rather, only the convergent inlet part of the propellant nozzle acts on the propellant medium flowing at subsonic speeds.
  • the propulsion nozzle acts as a convergent nozzle on the propellant medium, which flows at subsonic speeds. If the propellant medium is accelerated to the speed of sound by the convergent inlet part, it is further accelerated by the diverging interior of the outlet part. The propellant medium is guided through the divergent inner wall of the outlet part, since in this case it is not separated from the inner wall.
  • the outlet part acts as a nozzle for the propellant flowing at supersonic speed and further accelerates the propellant. This means that the propellant nozzle acts as a Laval nozzle for propellant medium flowing at supersonic speeds.
  • the invention thus provides a jet pump that can be used both at subcritical pressure conditions, i.e. H. when the propellant medium causes the suction effect at subsonic speeds, as well as at supercritical pressure conditions, i.e. H. if the propellant medium causes the suction effect at supersonic speed, it is operated with a single propellant nozzle.
  • the effect of the outlet part on the flowing propellant medium is automatically adjusted by the opening angle of the inner wall.
  • the invention thus provides an automatic, cost-effective and simple switchover of the jet pump to different pressure conditions.
  • the inner wall of the outlet part can be designed such that the propellant flowing through the outlet part detaches from the inner wall during a transition from supersonic speed to subsonic speed.
  • the inner wall of the outlet part can be designed such that the propellant flowing through the outlet part detaches from the inner wall during a transition from a supercritical pressure ratio to a subcritical pressure ratio.
  • the inner wall of the outlet part can be designed in such a way that the propellant medium flowing through the outlet part contacts the inner wall during a transition from subsonic speed to supersonic speed and is guided by the inner wall.
  • the inner wall of the outlet part can be designed such that the propellant medium flowing through the outlet part contacts the inner wall during a transition from the subcritical pressure ratio to the supercritical pressure ratio and is guided by the inner wall.
  • a pressure ratio of a driving pressure of the driving medium to a suction pressure at the outlet part can be between 1.05 and 5, preferably between 1.1 and 2.5.
  • jet pump can be operated in a wide pressure range, whereby the pressure conditions can be subcritical or supercritical in relation to a desired suction pressure.
  • This provides sufficient suction pressure for the operation of the jet pump both at a low pressure ratio, at which the propellant flows at subsonic speed, and at a high pressure ratio, at which the propellant flows at supersonic speed.
  • the jet pump therefore has a subcritical and a supercritical operating range in which it can be operated. This means that the jet pump can be operated in a wide range of applications.
  • the opening angle is more than 7°.
  • FIG. 1 A jet pump is shown in a schematic sectional view, the jet pump being designated in its entirety with the reference number 10.
  • the jet pump 10 has a propellant medium tank 12, a propellant nozzle 14, a suction medium tank 18, a mixing chamber 20 and a diffuser 22.
  • the propellant medium is provided in the propellant medium tank 12.
  • the driving medium can be a compressible driving medium.
  • the propellant can be pressurized in the propellant tank 12 or stored under pressure in the propellant tank 12.
  • the pressure ratio can e.g. B. between 1.05 and 5, preferably between 1.1 and 2.5. Under this driving pressure, the driving medium flows from the driving medium tank 12 to the driving nozzle 14 during operation of the jet pump 10. This is represented by the arrow 30.
  • the driving nozzle 14 has a convergent inlet part 28 and an outlet part 26 with a divergent interior 40.
  • the exit part 26 and the convergent entry part 28 are connected to one another.
  • the connection point of the convergent entry part 28 with the exit part 26 has the smallest cross section of the propulsion nozzle 14.
  • the convergent entry part 28 has a tapering cross section.
  • the propellant medium initially flows into an area of the convergent inlet part 28 with a large cross section.
  • the propellant medium flowing through the convergent inlet part 28 is accelerated.
  • the driving medium is accelerated to a subsonic speed or a speed of sound by means of the convergent entry part 28 when the driving medium flows through the convergent entry part 28.
  • the exit part 26 adjoins the tapered end of the convergent entry part 28.
  • the exit part 26 includes an inner wall 38 which laterally encloses the interior 40.
  • the inner wall 38 can enclose the interior 40 in the form of a conical lateral surface, as in Figure 3a shown.
  • the inner wall 38 can enclose the interior 40 in the form of a lateral surface of a bell shape, as in Fig. 3b shown.
  • the interior 40 has an inlet opening which is connected to the outlet opening of the convergent inlet part 28. Furthermore, the interior 40 has an outlet opening that is larger than the inlet opening of the interior 40.
  • the inner wall 38 extends between the inlet opening and the outlet opening of the interior 40. The interior 40 is therefore designed to be divergent and diverges at an opening angle 16.
  • the inner wall 38 defines the opening angle 16 directly after the narrowest cross section at the inlet opening of the interior 40. The opening angle 16 of the inner wall 38 can change as the distance from the inlet opening increases.
  • the opening angle 16 is chosen so that a propellant medium flowing through the outlet part 26 at subsonic speed is released from the inner wall 38 and a propellant medium flowing through the outlet part 26 at supersonic speed is guided by the inner wall 38. i.e. the inner wall 38 does not influence a propellant medium flowing through the outlet part 26 at subsonic speed. Rather, the propellant medium flowing at subsonic speed is detached from the inner wall 38 and flows as a jet from the outlet opening of the convergent inlet part 28 through the outlet part 26 and out of the propellant nozzle 14.
  • the opening angle 16 is further selected such that a propellant medium flowing through the outlet part 26 at supersonic speed is guided by the inner wall 38.
  • An expansion of the propellant medium flowing through the outlet part 26 that occurs perpendicular to the flow direction is limited by the inner wall 38.
  • An outer area of the flow of the propellant therefore flows along the inner wall 38.
  • the opening angle 16 is at least 7°.
  • An upper limit of the opening angle 16 is between 8° and 45°.
  • the propellant medium Due to the expansion occurring perpendicular to the direction of flow and limited by the inner wall 38, the propellant medium is further accelerated and flows out of the outlet part 26 at an increased supersonic speed.
  • the propellant After exiting the outlet part 26, the propellant flows past an opening of the suction medium tank 18 and thereby causes a suction pressure.
  • the suction medium is entrained and accelerated with the propellant medium flowing past the suction medium tank 18.
  • the driving medium and the suction medium enter the mixing chamber 20. While the driving medium and the suction medium flow through the mixing chamber 20, the driving medium and the suction medium mix.
  • a diffuser 22 adjoins the mixing chamber 20, in which the propellant medium and the suction medium mixed with it are delayed.
  • the diffuser 22 includes an outlet opening 24. The propellant medium and the sauté medium can flow out of the jet pump 10 through the outlet opening 24.
  • FIGS. 2a and 2b show schematically a cross section through the driving nozzle 14, the flow of the driving medium through the driving nozzle 14 being indicated by means of streamlines 32, 34.
  • the propellant medium is in Figure 2a accelerated to the speed of sound by means of the convergent entry part 28. In the convergent entry part 28, this is indicated by the converging streamlines 32.
  • the propellant medium accelerated to the speed of sound flows from the convergent inlet part 28 into the outlet part 26.
  • the streamlines 32 diverge in the outlet part 26.
  • the outer streamlines 32 run along the inner wall 38, which indicates that the propellant medium is guided along the inner wall 38 through the interior 40.
  • the propellant medium is expanded and the speed is further increased to supersonic speed.
  • the propellant medium therefore flows out of the convergent inlet part 28 at subsonic speed.
  • the streamlines 34 condense in the convergent entry part 28.
  • the opening angle 16 of the diverging inner wall 38 is selected such that a propellant medium flowing at subsonic speed is separated from the diverging inner wall 38, the propellant is not expanded in the outlet part 26, but flows as a free jet through the outlet part 26. This is due to the Streamlines 34 are shown in the exit part 26, which run essentially parallel to one another. The free jet has an almost constant width 36 in the exit part 26.
  • the width 36 of the subsonic flow of the propellant in the outlet part 26 is therefore smaller than a clear width of the interior space 40 laterally delimited by the inner wall 38, the clear width increasing due to the diverging inner wall 38.
  • the pressure of the propellant medium in the convergent entry portion 28 may be increased or decreased during operation.
  • the inner wall 38 of the outlet part 26 is designed such that the propellant medium flowing through the outlet part 26 detaches from the inner wall 38 during a transition from the supercritical pressure ratio to the subcritical pressure ratio. Conversely, the propellant flowing through the outlet part 26 will contact the inner wall 38 during a transition from a subcritical pressure ratio to a supercritical pressure ratio and be guided by the inner wall 38.
  • the jet pump 10 can therefore be operated with both a supercritical pressure ratio and a subcritical pressure ratio.
  • a subcritical pressure ratio can be set, in which the propellant flows through the outlet part 26 at subsonic speed, the flowing propellant being detached from the inner wall 38.
  • a supercritical pressure ratio can be set in which the propellant flows through the outlet part 26 at supersonic speed, with the flowing propellant being guided through the inner wall 38.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)

Description

Die Erfindung betrifft eine Strahlpumpe umfassend eine Treibdüse zum Beschleunigen eines Treibmediums, wobei die Treibdüse ein konvergierendes Eintrittsteil und ein mit dem konvergierenden Eintrittsteil verbundenes Austrittsteil aufweist, wobei das Austrittsteil, gemäß dem Oberbegriff von Anspruch 1, einen von einer Innenwand umschlossenen unter einem Öffnungswinkel divergierenden Innenraum umfasst.The invention relates to a jet pump comprising a driving nozzle for accelerating a driving medium, the driving nozzle having a converging inlet part and an outlet part connected to the converging inlet part, the outlet part, according to the preamble of claim 1, having an interior space enclosed by an inner wall and diverging at an opening angle includes.

Strahlpumpen verwenden einen Fluidstrahl aus einem Treibmedium, um ein Saugmedium anzusaugen und zu beschleunigen. Die Saugwirkung wird durch ein Vorbeiströmen des Treibmediums an dem Saugmedium bewirkt, wobei das Saugmedium von dem Treibmedium mitgerissen wird, wenn die Strömungsgeschwindigkeit des Treibmediums ausreichend hoch ist. Um ein Treibmedium zu beschleunigen, wird es unter Druck durch eine Düse geführt, die das Treibmedium beschleunigt. Wenn der Saugdruck und der Treibdruck ein unterkritisches Druckverhältnis aufweisen, wird eine konvergente Düse zur Beschleunigung des Treibmediums in der Strahlpumpe verwendet. Bei überkritischen Druckverhältnissen wird eine konvergent-divergente Düse, eine sog. Laval-Düse, genutzt, um das im konvergenten Teil der Laval-Düse auf Schallgeschwindigkeit beschleunigte Treibmedium weiter zu beschleunigen. Eine Laval-Düse führt bei Treibmedien, die mit Unterschallgeschwindigkeit fließen, zu einer Verzögerung der Strömungsgeschwindigkeit, da der divergente Abschnitt der Laval-Düse für das Treibmedium als Diffusor wirkt.Jet pumps use a jet of fluid from a propellant medium to suck in and accelerate a suction medium. The suction effect is caused by the propellant medium flowing past the suction medium, the suction medium being carried along by the propellant medium when the flow speed of the propellant medium is sufficiently high. To accelerate a propellant medium, it is passed under pressure through a nozzle that accelerates the propellant medium. If the suction pressure and the driving pressure have a subcritical pressure ratio have, a convergent nozzle is used to accelerate the propellant in the jet pump. At supercritical pressure conditions, a convergent-divergent nozzle, a so-called Laval nozzle, is used to further accelerate the propellant medium, which is accelerated to the speed of sound in the convergent part of the Laval nozzle. A Laval nozzle results in a deceleration of flow velocity for propellant media flowing at subsonic speeds because the divergent section of the Laval nozzle acts as a diffuser for the propellant.

Das Dokument US 6 877 970 offenbart eine Strahlpumpe mit einer Treibdüse,The document US 6,877,970 discloses a jet pump with a propulsion nozzle,

Aufgabe der Erfindung ist es, eine verbesserte Strahlpumpe bereitzustellen, die einen Betrieb bei unterkritischen und überkritischen Druckverhältnissen erlaubt.The object of the invention is to provide an improved jet pump that allows operation at subcritical and supercritical pressure conditions.

Hauptmerkmale der Erfindung sind im kennzeichnenden Teil von Anspruch 1 angegeben. Ausgestaltungen sind Gegenstand der Ansprüche 2 bis 8.Main features of the invention are set out in the characterizing part of claim 1. Refinements are the subject of claims 2 to 8.

Die Erfindung betrifft eine Strahlpumpe umfassend eine Treibdüse zum Beschleunigen einesThe invention relates to a jet pump comprising a driving nozzle for accelerating a

Treibmediums, wobei die Treibdüse ein konvergierendes Eintrittsteil und ein mit dem konvergierenden Eintrittsteil verbundenes Austrittsteil aufweist, wobei das Austrittsteil einen von einer Innenwand umschlossenen unter einem Öffnungswinkel divergierenden Innenraum umfasst, wobei die Innenwand den Öffnungswinkel direkt nach einem engsten Querschnitt an einer Eintrittsöffnung des Innenraums definiert wobei erfindungsgemäß vorgesehen ist, dass der Öffnungswinkel derart ausgebildet ist, dass ein mit Unterschallgeschwindigkeit durch das Austrittsteil strömendes Treibmedium von der Innenwand gelöst ist, wobei das Austrittsteil (26) für das mit Unterschallgeschwindigkeit strömende Treibmedium nicht als Diffusor wirkt, und ein mit Überschallgeschwindigkeit durch das Austrittsteil strömendes Treibmedium von der Innenwand geführt wird, wobei der Öffnungswinkel mehr als 7° und höchstens 45° beträgt.Propellant medium, wherein the propellant nozzle has a converging inlet part and an outlet part connected to the converging inlet part, the outlet part comprising an interior enclosed by an inner wall that diverges at an opening angle, the inner wall defining the opening angle directly according to a narrowest cross section at an inlet opening of the interior According to the invention, it is provided that the opening angle is designed such that a propellant medium flowing through the outlet part at subsonic speed is separated from the inner wall, the outlet part (26) not acting as a diffuser for the propellant medium flowing at subsonic speed, and a propellant medium flowing through the outlet part at supersonic speed flowing propellant medium is guided by the inner wall, with the opening angle being more than 7° and a maximum of 45°.

Mit der Erfindung wird eine Strahlpumpe mit einer Treibdüse bereitgestellt, dessen konvergentes Eintrittsteil ein durch das konvergente Eintrittsteil strömendes Treibmedium beschleunigt, wobei das Treibmedium vor dem Durchströmen des Eintrittsteils mit Unterschallgeschwindigkeit strömt. Wenn das Treibmedium nach dem Durchströmen des Eintrittsteils und der Beschleunigung darin weiterhin Unterschallgeschwindigkeit aufweist, durchströmt es das Austrittsteil ebenfalls mit Unterschallgeschwindigkeit. Das Austrittsteil der Treibdüse weist dabei eine divergente Innenwand auf, d. h., dass sich der Querschnitt des Austrittsteils von dem konvergenten Eintrittsteil ausgehend vergrößert. Die Treibdüse kann dabei eine speziell ausgebildete Laval-Düse sein. Der Öffnungswinkel der divergenten Innenwand ist dabei so groß, dass sich ein mit Unterschallgeschwindigkeit durch das Austrittsteil strömendes Treibmedium von der Innenwand des Austrittsteils löst. Das Austrittsteil der Treibdüse wirkt für das mit Unterschallgeschwindigkeit strömende Treibmedium damit nicht als Diffusor, so dass keine Verzögerung der Geschwindigkeit des Treibmediums beim Durchströmen des Austrittsteils bewirkt wird. Vielmehr wirkt lediglich das konvergente Eintrittsteil der Treibdüse auf das mit Unterschallgeschwindigkeit strömende Treibmedium. Die Treibdüse wirkt auf das Treibmedium, das mit Unterschallgeschwindigkeit strömt, als konvergente Düse. Wird das Treibmedium durch das konvergente Eintrittsteil auf Schallgeschwindigkeit beschleunigt, wird es durch den divergierenden Innenraum des Austrittsteils weiter beschleunigt. Das Treibmedium wird dabei durch die divergente Innenwand des Austrittsteils geführt, da es in diesem Fall nicht von der Innenwand gelöst ist. Dabei wirkt das Austrittsteil als Düse für das mit Überschallgeschwindigkeit strömende Treibmedium und beschleunigt das Treibmedium weiter. Damit wirkt die Treibdüse für mit Überschallgeschwindigkeit strömendes Treibmedium als Laval-Düse.The invention provides a jet pump with a driving nozzle, the convergent inlet part of which accelerates a propellant medium flowing through the convergent inlet part, the propellant medium flowing at subsonic speed before flowing through the inlet part. If the propellant medium continues to have subsonic speed after flowing through the inlet part and accelerating therein, it also flows through the outlet part at subsonic speed. The outlet part of the driving nozzle has a divergent inner wall, that is, the cross section of the outlet part increases starting from the convergent inlet part. The driving nozzle can be a specially designed Laval nozzle be. The opening angle of the divergent inner wall is so large that a propellant medium flowing through the outlet part at subsonic speed separates from the inner wall of the outlet part. The outlet part of the propulsion nozzle works at subsonic speeds flowing propellant medium does not act as a diffuser, so that no delay in the speed of the propellant medium is caused when it flows through the outlet part. Rather, only the convergent inlet part of the propellant nozzle acts on the propellant medium flowing at subsonic speeds. The propulsion nozzle acts as a convergent nozzle on the propellant medium, which flows at subsonic speeds. If the propellant medium is accelerated to the speed of sound by the convergent inlet part, it is further accelerated by the diverging interior of the outlet part. The propellant medium is guided through the divergent inner wall of the outlet part, since in this case it is not separated from the inner wall. The outlet part acts as a nozzle for the propellant flowing at supersonic speed and further accelerates the propellant. This means that the propellant nozzle acts as a Laval nozzle for propellant medium flowing at supersonic speeds.

Mit der Erfindung wird damit eine Strahlpumpe bereitgestellt, die sowohl bei unterkritischen Druckverhältnissen, d. h. wenn das Treibmedium mit Unterschallgeschwindigkeit die Saugwirkung bewirkt, als auch bei überkritischen Druckverhältnissen, d. h. wenn das Treibmedium mit Überschallgeschwindigkeit die Saugwirkung bewirkt, mit einer einzigen Treibdüse betrieben wird. Die Wirkung des Austrittsteils auf das strömende Treibmedium wird dabei automatisch durch den Öffnungswinkel der Innenwand eingestellt. Durch die Erfindung wird damit eine automatische, kostengünstige und einfache Umschaltung der Strahlpumpe auf verschiedene Druckverhältnisse bereitgestellt.The invention thus provides a jet pump that can be used both at subcritical pressure conditions, i.e. H. when the propellant medium causes the suction effect at subsonic speeds, as well as at supercritical pressure conditions, i.e. H. if the propellant medium causes the suction effect at supersonic speed, it is operated with a single propellant nozzle. The effect of the outlet part on the flowing propellant medium is automatically adjusted by the opening angle of the inner wall. The invention thus provides an automatic, cost-effective and simple switchover of the jet pump to different pressure conditions.

Die Innenwand des Austrittsteils kann so ausgebildet sein, dass sich das durch das Austrittsteil strömende Treibmedium bei einem Übergang von Überschallgeschwindigkeit zu Unterschallgeschwindigkeit von der Innenwand löst. Anders ausgedrückt kann die Innenwand des Austrittsteils so ausgebildet sein, dass sich das durch das Austrittsteil strömende Treibmedium bei einem Übergang von einem überkritischen Druckverhältnis zu einem unterkritischen Druckverhältnis von der Innenwand löst.The inner wall of the outlet part can be designed such that the propellant flowing through the outlet part detaches from the inner wall during a transition from supersonic speed to subsonic speed. In other words, the inner wall of the outlet part can be designed such that the propellant flowing through the outlet part detaches from the inner wall during a transition from a supercritical pressure ratio to a subcritical pressure ratio.

Damit kann der Druck während des Betriebs der Strahlpumpe von dem überkritischen Druckverhältnis zu dem unterkritischen Druckverhältnis geändert werden, wobei Druckstöße bei dem Umschaltvorgang vermieden werden. Dies bewirkt eine zusätzliche Erweiterung des Einsatzbereiches der Strahlpumpe.This allows the pressure to be changed from the supercritical pressure ratio to the subcritical pressure ratio during operation of the jet pump, avoiding pressure surges during the switching process. This causes an additional expansion of the area of application of the jet pump.

Weiter kann die Innenwand des Austrittsteils so ausgebildet sein, dass sich das durch das Austrittsteil strömende Treibmedium bei einem Übergang von Unterschallgeschwindigkeit zu Überschallgeschwindigkeit an die Innenwand anlegt und von der Innenwand geführt wird. In anderen Worten kann die Innenwand des Austrittsteils so ausgebildet sein, dass sich das durch das Austrittsteil strömende Treibmedium bei einem Übergang von dem unterkritischen Druckverhältnis zu dem überkritischen Druckverhältnis an die Innenwand anlegt und von der Innenwand geführt wird.Furthermore, the inner wall of the outlet part can be designed in such a way that the propellant medium flowing through the outlet part contacts the inner wall during a transition from subsonic speed to supersonic speed and is guided by the inner wall. In other words, the inner wall of the outlet part can be designed such that the propellant medium flowing through the outlet part contacts the inner wall during a transition from the subcritical pressure ratio to the supercritical pressure ratio and is guided by the inner wall.

Damit kann ein reibungsloser Übergang von dem unterkritischen Druckverhältnis zu dem überkritischen Druckverhältnis erfolgen. Dies erweitert den Einsatzbereich der Strahlpumpe weiter.This allows a smooth transition from the subcritical pressure ratio to the supercritical pressure ratio. This further expands the area of application of the jet pump.

Weiter kann ein Druckverhältnis von einem Treibdruck des Treibmediums zu einem Saugdruck an dem Austrittsteil zwischen 1,05 und 5, vorzugsweise zwischen 1,1 und 2,5, betragen.Furthermore, a pressure ratio of a driving pressure of the driving medium to a suction pressure at the outlet part can be between 1.05 and 5, preferably between 1.1 and 2.5.

Damit kann die Strahlpumpe in einem weiten Druckbereich betrieben werden, wobei die Druckverhältnisse im Verhältnis zu einem gewünschten Saugdruck unterkritisch oder überkritisch sein können.This means that the jet pump can be operated in a wide pressure range, whereby the pressure conditions can be subcritical or supercritical in relation to a desired suction pressure.

Damit wird sowohl bei einem niedrigen Druckverhältnis, bei dem das Treibmedium mit Unterschallgeschwindigkeit strömt, als auch bei einem hohen Druckverhältnis, bei dem das Treibmedium mit Überschallgeschwindigkeit strömt, ein ausreichender Saugdruck für den Betrieb der Strahlpumpe bereitgestellt.This provides sufficient suction pressure for the operation of the jet pump both at a low pressure ratio, at which the propellant flows at subsonic speed, and at a high pressure ratio, at which the propellant flows at supersonic speed.

Die Strahlpumpe weist damit einen unterkritischen und einen überkritischen Betriebsbereich auf, in dem sie betrieben werden kann. Damit kann die Strahlpumpe in einem weiten Einsatzbereich betrieben werden.The jet pump therefore has a subcritical and a supercritical operating range in which it can be operated. This means that the jet pump can be operated in a wide range of applications.

Erfindungsgemäß beträgt der Öffnungswinkel mehr als 7°.According to the invention, the opening angle is more than 7°.

Mit Öffnungswinkeln von mehr als 7° wird das Ablösen des durch das Austrittsteil mit Unterschallgeschwindigkeit strömende Treibmedium von der Innenwand weiter begünstigt. Damit wird ein Anhaften des durch das Austrittsteil strömenden Treibmediums an die Innenwand des Austrittsteils bei Unterschallgeschwindigkeiten vermieden.With opening angles of more than 7°, the separation of the propellant medium flowing through the outlet part at subsonic speed from the inner wall is further promoted. This prevents the propellant flowing through the outlet part from sticking to the inner wall of the outlet part at subsonic speeds.

Weitere Merkmale, Einzelheiten und Vorteile der Erfindung ergeben sich aus dem Wortlaut der Ansprüche sowie aus der folgenden Beschreibung von Ausführungsbeispielen anhand der Zeichnungen. Es zeigen:

Fig. 1
eine schematische Darstellung der Strahlpumpe,
Fig. 2a, b
schematische Darstellungen der Treibdüse, und
Fig. 3a, b
schematische Darstellungen von Beispielen des Austrittsteils.
Further features, details and advantages of the invention emerge from the wording of the claims and from the following description of exemplary embodiments based on the drawings. Show it:
Fig. 1
a schematic representation of the jet pump,
Fig. 2a, b
schematic representations of the propulsion nozzle, and
Fig. 3a, b
schematic representations of examples of the exit part.

In Figur 1 ist eine Strahlpumpe in schematischer Schnittdarstellung gezeigt, wobei die Strahlpumpe in ihrer Gesamtheit mit dem Referenzzeichen 10 bezeichnet wird.In Figure 1 A jet pump is shown in a schematic sectional view, the jet pump being designated in its entirety with the reference number 10.

Die Strahlpumpe 10 weist einen Treibmedium-Tank 12, eine Treibdüse 14, einen Saugmedium-Tank 18, eine Mischkammer 20 und einen Diffusor 22 auf.The jet pump 10 has a propellant medium tank 12, a propellant nozzle 14, a suction medium tank 18, a mixing chamber 20 and a diffuser 22.

In dem Treibmedium-Tank 12 wird das Treibmedium bereitgestellt. Das Treibmedium kann dabei ein kompressibles Treibmedium sein. Das Treibmedium kann in dem Treibmedium-Tank 12 mit einem Druck beaufschlagt werden oder unter Druck in dem Treibmedium-Tank 12 gelagert werden. Das Druckverhältnis kann z. B. zwischen 1,05 und 5, vorzugsweise zwischen 1,1 und 2,5, betragen. Unter diesem Treibdruck strömt das Treibmedium beim Betrieb der Strahlpumpe 10 von dem Treibmedium-Tank 12 zu der Treibdüse 14. Dies wird durch den Pfeil 30 dargestellt.The propellant medium is provided in the propellant medium tank 12. The driving medium can be a compressible driving medium. The propellant can be pressurized in the propellant tank 12 or stored under pressure in the propellant tank 12. The pressure ratio can e.g. B. between 1.05 and 5, preferably between 1.1 and 2.5. Under this driving pressure, the driving medium flows from the driving medium tank 12 to the driving nozzle 14 during operation of the jet pump 10. This is represented by the arrow 30.

Die Treibdüse 14 weist dabei ein konvergentes Eintrittsteil 28 und ein Austrittsteil 26 mit einem divergenten Innenraum 40 auf. Das Austrittsteil 26 und das konvergente Eintrittsteil 28 sind miteinander verbunden. Die Verbindungsstelle des konvergenten Eintrittsteils 28 mit dem Austrittsteil 26 weist den kleinsten Querschnitt der Treibdüse 14 auf.The driving nozzle 14 has a convergent inlet part 28 and an outlet part 26 with a divergent interior 40. The exit part 26 and the convergent entry part 28 are connected to one another. The connection point of the convergent entry part 28 with the exit part 26 has the smallest cross section of the propulsion nozzle 14.

Das konvergente Eintrittsteil 28 weist einen sich verjüngenden Querschnitt auf. Das Treibmedium strömt zunächst in einen Bereich des konvergenten Eintrittsteils 28 mit einem großen Querschnitt. Durch die Verjüngung des Querschnitts des konvergenten Eintrittsteils 28 wird das durch das konvergente Eintrittsteil 28 strömende Treibmedium beschleunigt.The convergent entry part 28 has a tapering cross section. The propellant medium initially flows into an area of the convergent inlet part 28 with a large cross section. By narrowing the cross section of the convergent inlet part 28, the propellant medium flowing through the convergent inlet part 28 is accelerated.

In Abhängigkeit des Treibdrucks wird das Treibmedium mittels des konvergenten Eintrittsteils 28 auf eine Unterschallgeschwindigkeit oder eine Schallgeschwindigkeit beschleunigt, wenn das Treibmedium durch das konvergente Eintrittsteil 28 strömt.Depending on the driving pressure, the driving medium is accelerated to a subsonic speed or a speed of sound by means of the convergent entry part 28 when the driving medium flows through the convergent entry part 28.

Das Austrittsteil 26 schließt sich an dem verjüngten Ende des konvergenten Eintrittsteils 28 an. Dabei umfasst das Austrittsteil 26 eine Innenwand 38, die den Innenraum 40 seitlich umschließt. Die Innenwand 38 kann in einem Ausführungsbeispiel den Innenraum 40 dabei in Form einer konischen Mantelfläche umschließen, wie in Figur 3a dargestellt. In einem anderen Ausführungsbeispiel kann die Innenwand 38 den Innenraum 40 in Form einer eine Mantelfläche einer Glockenform umschließen, wie in Fig. 3b dargestellt.The exit part 26 adjoins the tapered end of the convergent entry part 28. The exit part 26 includes an inner wall 38 which laterally encloses the interior 40. In one exemplary embodiment, the inner wall 38 can enclose the interior 40 in the form of a conical lateral surface, as in Figure 3a shown. In another exemplary embodiment, the inner wall 38 can enclose the interior 40 in the form of a lateral surface of a bell shape, as in Fig. 3b shown.

Der Innenraum 40 weist dabei eine Eintrittsöffnung auf, die mit der Austrittsöffnung des konvergenten Eintrittsteils 28 verbunden ist. Weiter weist der Innenraum 40 eine Austrittsöffnung auf, die größer als die Eintrittsöffnung des Innenraums 40 ist. Zwischen der Eintrittsöffnung und der Austrittsöffnung des Innenraums 40 erstreckt sich die Innenwand 38. Der Innenraum 40 ist damit divergent ausgebildet und divergiert unter einem Öffnungswinkel 16. Die Innenwand 38 definiert den Öffnungswinkel 16 direkt nach dem engsten Querschnitt an der Eintrittsöffnung des Innenraums 40. Der Öffnungswinkel 16 der Innenwand 38 kann sich dabei mit zunehmendem Abstand von der Eintrittsöffnung ändern.The interior 40 has an inlet opening which is connected to the outlet opening of the convergent inlet part 28. Furthermore, the interior 40 has an outlet opening that is larger than the inlet opening of the interior 40. The inner wall 38 extends between the inlet opening and the outlet opening of the interior 40. The interior 40 is therefore designed to be divergent and diverges at an opening angle 16. The inner wall 38 defines the opening angle 16 directly after the narrowest cross section at the inlet opening of the interior 40. The opening angle 16 of the inner wall 38 can change as the distance from the inlet opening increases.

Der Öffnungswinkel 16 ist dabei so gewählt, dass ein mit Unterschallgeschwindigkeit durch das Austrittsteil 26 strömendes Treibmedium von der Innenwand 38 gelöst ist und ein mit Überschallgeschwindigkeit durch das Austrittsteil 26 strömendes Treibmedium von der Innenwand 38 geführt wird. D. h. die Innenwand 38 beeinflusst ein mit Unterschallgeschwindigkeit durch das Austrittsteil 26 strömendes Treibmedium nicht. Vielmehr ist das mit Unterschallgeschwindigkeit strömende Treibmedium von der Innenwand 38 gelöst und strömt als Strahl aus der Austrittsöffnung des konvergenten Eintrittsteils 28 durch das Austrittsteil 26 und aus der Treibdüse 14.The opening angle 16 is chosen so that a propellant medium flowing through the outlet part 26 at subsonic speed is released from the inner wall 38 and a propellant medium flowing through the outlet part 26 at supersonic speed is guided by the inner wall 38. i.e. the inner wall 38 does not influence a propellant medium flowing through the outlet part 26 at subsonic speed. Rather, the propellant medium flowing at subsonic speed is detached from the inner wall 38 and flows as a jet from the outlet opening of the convergent inlet part 28 through the outlet part 26 and out of the propellant nozzle 14.

Der Öffnungswinkel 16 ist weiter so gewählt, dass ein mit Überschallgeschwindigkeit durch das Austrittsteil 26 strömendes Treibmedium von der Innenwand 38 geführt wird. Eine senkrecht zur Strömungsrichtung erfolgende Expansion des durch das Austrittsteil 26 strömenden Treibmediums wird dabei durch die Innenwand 38 begrenzt. Ein Außenbereich der Strömung des Treibmediums strömt daher an der Innenwand 38 entlang.The opening angle 16 is further selected such that a propellant medium flowing through the outlet part 26 at supersonic speed is guided by the inner wall 38. An expansion of the propellant medium flowing through the outlet part 26 that occurs perpendicular to the flow direction is limited by the inner wall 38. An outer area of the flow of the propellant therefore flows along the inner wall 38.

Dabei beträgt der Öffnungswinkel 16 mindestens 7°. Eine obere Grenze des Öffnungswinkels 16 liegt zwischen 8° und 45°.The opening angle 16 is at least 7°. An upper limit of the opening angle 16 is between 8° and 45°.

Durch die senkrecht zur Strömungsrichtung erfolgende und die Innenwand 38 begrenzte Expansion wird das Treibmedium weiter beschleunigt und strömt mit erhöhter Überschallgeschwindigkeit aus dem Austrittsteil 26 aus.Due to the expansion occurring perpendicular to the direction of flow and limited by the inner wall 38, the propellant medium is further accelerated and flows out of the outlet part 26 at an increased supersonic speed.

Nach dem Austritt aus dem Austrittsteil 26 strömt das Treibmedium an einer Öffnung des Saugmedium-Tanks 18 vorbei und bewirkt dabei einen Saugdruck.After exiting the outlet part 26, the propellant flows past an opening of the suction medium tank 18 and thereby causes a suction pressure.

Das Saugmedium wird mit dem an dem Saugmedium-Tank 18 vorbeiströmenden Treibmedium mitgerissen und beschleunigt. Dadurch gelangen das Treibmedium und das Saugmedium in die Mischkammer 20. Während das Treibmedium und das Saugmedium die Mischkammer 20 durchströmen, vermischen sich das Treibmedium und das Saugmedium.The suction medium is entrained and accelerated with the propellant medium flowing past the suction medium tank 18. As a result, the driving medium and the suction medium enter the mixing chamber 20. While the driving medium and the suction medium flow through the mixing chamber 20, the driving medium and the suction medium mix.

An die Mischkammer 20 schließt sich ein Diffusor 22 an, in dem das Treibmedium und das mit ihm vermischte Saugmedium verzögert werden. Der Diffusor 22 umfasst eine Auslassöffnung 24. Das Treibmedium und das Saumedium können durch die Auslassöffnung 24 aus der Strahlpumpe 10 ausströmen.A diffuser 22 adjoins the mixing chamber 20, in which the propellant medium and the suction medium mixed with it are delayed. The diffuser 22 includes an outlet opening 24. The propellant medium and the sauté medium can flow out of the jet pump 10 through the outlet opening 24.

Die Figur 2a und 2b zeigen in schematischer Weise einen Querschnitt durch die Treibdüse 14, wobei die Strömung des Treibmediums durch die Treibdüse 14 mittels Stromlinien 32, 34 angezeigt wird.The Figures 2a and 2b show schematically a cross section through the driving nozzle 14, the flow of the driving medium through the driving nozzle 14 being indicated by means of streamlines 32, 34.

Dabei wird das Treibmedium in Figur 2a mittels des konvergenten Eintrittsteils 28 auf Schallgeschwindigkeit beschleunigt. In dem konvergenten Eintrittsteil 28 wird dies durch die zusammenlaufenden Stromlinien 32 angezeigt. Von dem konvergenten Eintrittsteil 28 strömt das auf Schallgeschwindigkeit beschleunigte Treibmedium in das Austrittsteil 26. In dem Austrittsteil 26 laufen die Stromlinien 32 auseinander. Die äußeren Stromlinien 32 verlaufen dabei entlang der Innenwand 38, wodurch anzeigt wird, dass das Treibmedium entlang der Innenwand 38 durch den Innenraum 40 geführt wird. Das Treibmedium wird dabei expandiert und die Geschwindigkeit damit weiter auf Überschallgeschwindigkeit erhöht.The propellant medium is in Figure 2a accelerated to the speed of sound by means of the convergent entry part 28. In the convergent entry part 28, this is indicated by the converging streamlines 32. The propellant medium accelerated to the speed of sound flows from the convergent inlet part 28 into the outlet part 26. The streamlines 32 diverge in the outlet part 26. The outer streamlines 32 run along the inner wall 38, which indicates that the propellant medium is guided along the inner wall 38 through the interior 40. The propellant medium is expanded and the speed is further increased to supersonic speed.

In Figur 2b wird das Treibmedium mittels konvergenten Eintrittsteils 28 ebenfalls beschleunigt, jedoch verbleibt die Geschwindigkeit des Treibmediums unterhalb der Schallgeschwindigkeit.In Figure 2b the propellant medium is also accelerated by means of the convergent inlet part 28, but the speed of the propellant medium remains below the speed of sound.

Das Treibmedium strömt daher mit Unterschallgeschwindigkeit aus dem konvergenten Eintrittsteil 28 aus. Die Stromlinien 34 verdichten sich in dem konvergenten Eintrittsteil 28.The propellant medium therefore flows out of the convergent inlet part 28 at subsonic speed. The streamlines 34 condense in the convergent entry part 28.

Da der Öffnungswinkel 16 der divergierenden Innenwand 38 so gewählt ist, dass ein mit Unterschallgeschwindigkeit strömendes Treibmedium von der divergierenden Innenwand 38 gelöst ist, wird das Treibmedium in dem Austrittsteil 26 nicht expandiert, sondern strömt als freier Strahl durch das Austrittsteil 26. Dies wird durch die Stromlinien 34 in dem Austrittsteil 26 dargestellt, die im Wesentlichen parallel zu einander verlaufen. Der freie Strahl hat in dem Austrittsteil 26 eine nahezu konstante Breite 36.Since the opening angle 16 of the diverging inner wall 38 is selected such that a propellant medium flowing at subsonic speed is separated from the diverging inner wall 38, the propellant is not expanded in the outlet part 26, but flows as a free jet through the outlet part 26. This is due to the Streamlines 34 are shown in the exit part 26, which run essentially parallel to one another. The free jet has an almost constant width 36 in the exit part 26.

Die Breite 36 der Unterschallströmung des Treibmediums in dem Austrittsteil 26 ist daher kleiner als eine lichte Weite des seitlich durch die Innenwand 38 begrenzten Innenraums 40, wobei sich die lichte Weite aufgrund der divergierenden Innenwand 38 vergrößert.The width 36 of the subsonic flow of the propellant in the outlet part 26 is therefore smaller than a clear width of the interior space 40 laterally delimited by the inner wall 38, the clear width increasing due to the diverging inner wall 38.

Damit wird vermieden, dass die Innenwand 38 als Diffusor für das mit Unterschallgeschwindigkeit fließende Treibmedium wirkt und das Treibmedium durch das Austrittsteil 26 abgebremst wird.This prevents the inner wall 38 from acting as a diffuser for the propellant medium flowing at subsonic speed and the propellant medium being braked by the outlet part 26.

Der Druck des Treibmediums in dem konvergenten Eintrittsteil 28 kann während des Betriebs vergrößert oder verringert werden. Die Innenwand 38 des Austrittsteils 26 ist dabei so ausgebildet, dass sich das durch das Austrittsteil 26 strömende Treibmedium bei einem Übergang von dem überkritischen Druckverhältnis zu dem unterkritischen Druckverhältnis von der Innenwand 38 löst. Umgekehrt wird sich das durch das Austrittsteil 26 strömende Treibmedium bei einem Übergang von einem unterkritischen Druckverhältnis zu einem überkritischen Druckverhältnis an die Innenwand 38 anlegen und von der Innenwand 38 geführt werden.The pressure of the propellant medium in the convergent entry portion 28 may be increased or decreased during operation. The inner wall 38 of the outlet part 26 is designed such that the propellant medium flowing through the outlet part 26 detaches from the inner wall 38 during a transition from the supercritical pressure ratio to the subcritical pressure ratio. Conversely, the propellant flowing through the outlet part 26 will contact the inner wall 38 during a transition from a subcritical pressure ratio to a supercritical pressure ratio and be guided by the inner wall 38.

Das bedeutet, dass die Geschwindigkeit des Treibmediums im Austrittsteil 26 zwischen Überschallgeschwindigkeit und Unterschallgeschwindigkeit wechseln kann, ohne dass eine Störung des Betriebs der Strahlpumpe 10 erfolgt. Die Strahlpumpe 10 ist damit sowohl mit einem überkritischen Druckverhältnis als auch mit einem unterkritischen Druckverhältnis betreibbar.This means that the speed of the propellant in the outlet part 26 can change between supersonic speed and subsonic speed without disrupting the operation of the jet pump 10. The jet pump 10 can therefore be operated with both a supercritical pressure ratio and a subcritical pressure ratio.

Dabei kann bei einem Saugdruck von 0,98 bar und einem Treibdruck von 1,1 bar ein unterkritisches Druckverhältnis eingestellt sein, bei dem das Treibmedium mit Unterschallgeschwindigkeit durch das Austrittsteil 26 strömt, wobei das strömende Treibmedium von der Innenwand 38 gelöst ist.With a suction pressure of 0.98 bar and a driving pressure of 1.1 bar, a subcritical pressure ratio can be set, in which the propellant flows through the outlet part 26 at subsonic speed, the flowing propellant being detached from the inner wall 38.

Bei einem Saugdruck von 0,98 bar und einem Treibdruck von 2,5 bar kann damit ein überkritisches Druckverhältnis eingestellt werden, bei dem das Treibmedium mit Überschallgeschwindigkeit durch das Austrittsteil 26 strömt, wobei das strömende Treibmedium durch die Innenwand 38 geführt wird.With a suction pressure of 0.98 bar and a driving pressure of 2.5 bar, a supercritical pressure ratio can be set in which the propellant flows through the outlet part 26 at supersonic speed, with the flowing propellant being guided through the inner wall 38.

Die Erfindung ist nicht auf eine der vorbeschriebenen Ausführungsformen beschränkt, sondern in vielfältiger Weise abwandelbar.The invention is not limited to one of the previously described embodiments, but can be modified in many ways.

Sämtliche aus den Ansprüchen, der Beschreibung und der Zeichnung hervorgehenden Merkmale und Vorteile, einschließlich konstruktiver Einzelheiten, räumlicher Anordnungen und Verfahrensschritten, können sowohl für sich als auch in den verschiedensten Kombinationen erfindungswesentlich sein.All features and advantages arising from the claims, the description and the drawing, including constructive details, spatial arrangements and process steps, can be essential to the invention both individually and in a wide variety of combinations.

BezugszeichenlisteReference symbol list

1010
Strahlpumpejet pump
1212
Treibmedium-TankPropellant tank
1414
TreibdüsePropulsion nozzle
1616
Öffnungswinkelopening angle
1818
Saugmedium-TankSuction medium tank
2020
MischkammerMixing chamber
2222
Diffusordiffuser
2424
AuslassöffnungExhaust opening
2626
Austrittsteilexit part
2828
konvergierendes Eintrittsteilconverging entry part
3030
StrömungsrichtungDirection of flow
3232
Überschall-StromlinienSupersonic streamlines
3434
Unterschall-StromlinienSubsonic streamlines
3636
Breite freier StrahlWidth of free beam
3838
InnenwandInterior wall
4040
Innenrauminner space

Claims (4)

  1. Jet pump comprising a jet nozzle (14) for accelerating a propellant, wherein the jet nozzle (14) has a convergent inlet portion (28) and an outlet portion (26) which is connected to the convergent inlet portion (28), wherein the outlet portion (26) comprises an inner space (40) which is surrounded by an inner wall (38) and which diverges at an opening angle (16), wherein the inner wall (38) defines the opening angle (16) directly after a narrowest cross section at an entry opening of the inner space (40), characterized in that the opening angle (16) is constructed in such a manner that a propellant which flows through the outlet portion (26) at subsonic speed is released from the inner wall (38), wherein the outlet portion (26) does not act as a diffusor for the propellant which flows at subsonic speed, and a propellant which flows through the outlet portion (26) at supersonic speed is guided by the inner wall (38), wherein the opening angle (16) is more than 7° and at most 45°.
  2. Jet pump according to Claim 1, characterized in that the inner wall (38) of the outlet portion (26) is constructed in such a manner that the propellant flowing through the outlet portion (26) is released from the inner wall (38) during a transition from supersonic speed to subsonic speed.
  3. Jet pump according to Claim 1 or 2, characterized in that the inner wall (38) of the outlet portion (26) is constructed in such a manner that the propellant flowing through the outlet portion (26) during a transition from subsonic speed to supersonic speed is positioned against the inner wall (38) and is guided by the inner wall (38).
  4. Jet pump according to one of Claims 1 to 3, characterized in that a pressure relationship between a propellant pressure of the propellant and a suction pressure after the outlet portion (26) is between 1.05 and 5, preferably between 1.1 and 2.5.
EP20719576.9A 2019-04-08 2020-03-30 Jet pump Active EP3953588B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019109195.0A DE102019109195A1 (en) 2019-04-08 2019-04-08 Jet pump
PCT/EP2020/058994 WO2020207847A1 (en) 2019-04-08 2020-03-30 Jet pump

Publications (2)

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EP3953588A1 EP3953588A1 (en) 2022-02-16
EP3953588B1 true EP3953588B1 (en) 2023-12-06

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US (1) US11905978B2 (en)
EP (1) EP3953588B1 (en)
JP (1) JP7472165B2 (en)
KR (1) KR102649754B1 (en)
CN (1) CN113614386B (en)
DE (1) DE102019109195A1 (en)
MX (1) MX2021011742A (en)
WO (1) WO2020207847A1 (en)

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DE102021005770A1 (en) 2021-11-22 2023-05-25 Serge Olivier Menkuimb Novel and regenerative energy generation cooling system
KR20230171701A (en) * 2022-06-14 2023-12-21 주식회사 엘지에너지솔루션 Gas venting device, battery module and battery pack comprising the same

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Publication number Publication date
CN113614386B (en) 2024-01-23
KR102649754B1 (en) 2024-03-20
CN113614386A (en) 2021-11-05
JP2022526627A (en) 2022-05-25
KR20210139453A (en) 2021-11-22
EP3953588A1 (en) 2022-02-16
JP7472165B2 (en) 2024-04-22
US11905978B2 (en) 2024-02-20
WO2020207847A1 (en) 2020-10-15
MX2021011742A (en) 2021-10-22
DE102019109195A1 (en) 2020-10-08
US20220213904A1 (en) 2022-07-07

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