EP3390832B1 - Backfeed stage of a radial turbo fluid energy machine - Google Patents
Backfeed stage of a radial turbo fluid energy machine Download PDFInfo
- Publication number
- EP3390832B1 EP3390832B1 EP17707876.3A EP17707876A EP3390832B1 EP 3390832 B1 EP3390832 B1 EP 3390832B1 EP 17707876 A EP17707876 A EP 17707876A EP 3390832 B1 EP3390832 B1 EP 3390832B1
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- European Patent Office
- Prior art keywords
- section
- guide vanes
- circumferential direction
- backfeed
- guide
- Prior art date
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/053—Shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
Definitions
- the invention relates to a recirculation stage of a radial turbofluid energy machine, in particular a radial turbocompressor, for deflecting a flow direction of a process fluid emerging from a rotor rotating about an axis from radially outside to radially inside, comprising a return channel, which has three adjacent sections in the flow direction, wherein a first section is designed to conduct the process fluid radially outward, wherein a second portion for deflecting the process fluid is formed from radially outside to radially inside, wherein a third portion for guiding the process fluid is formed radially inward, wherein the second portion and the third portion or only the third section has first guide vanes, which define flow channels of the return channel in the circumferential direction to one another.
- the fluid to be compressed leaves an impeller rotating about an axis in the radial direction with a significant velocity component in the circumferential direction (twist).
- the static aerodynamically active components following in the flow direction have the task of converting the kinetic energy supplied in the impeller into pressure.
- the fluid In a multi-stage single-shaft compressor, such as from the JP000244516 known, the fluid must also be passed to the next impeller. Furthermore, the flow of the swirl is to escape, so that the following impeller is flowed largely swirl-free.
- a so-called recirculation stage comprising a first portion which leads the process fluid radially outward, a second portion substantially corresponding to a 180 ° arc, and a third portion for directing the process fluid radially inward for entry into the downstream one Wheel.
- the third section also includes a diversion of the Process fluid from the radially inwardly directed flow in the axial direction to the impeller inlet of the downstream impeller back.
- the scaffoldschaufelung can consist of lined up in the circumferential direction of individual blades, as it is known from JP 11173299-A is known.
- the invention has the object to develop a feedback stage of the type defined in such a way that a less expansive feedback stage generates a less lossy flow.
- a return stage of the type defined is proposed with the additional features of the characterizing part of patent claim 1. Furthermore, the invention proposes a radial turbofluid energy machine with such a return stage.
- the first section can be freely designed within the scope of the invention, so that the first section with or without blades, in Meriodinal bain in the flow direction For example, it may be expanding, constant or tapering.
- geometric expressions such as axial, tangential, radial or circumferential direction are always related to a rotational axis of an impeller of a radial turbofan energy machine, unless otherwise specified in the immediate context.
- the return stage according to the invention has a clear relationship to such an impeller, since the return stage extends circumferentially around the impeller downstream of the impeller outlet in a radial turbocompressor.
- the feedback stage is rotationally symmetrical to the axis.
- the return stage according to the invention is less bulky than a return stage which does not have the two vane stages one behind the other. Alignment of the flow to entry into the downstream impeller is aerodynamically more efficient by means of the stepped vane design.
- the inventively circumferentially offset second vane stage or the arrangement of the second vanes in the circumferential direction asymmetrically to the outlet edges of the first vanes leads to a reduction of the aerodynamic losses of the process fluid in the flow through the return stage.
- the reorientation and deflection of the process fluid downstream of the exit from an impeller to the entrance of the downstream impeller following the invention is particularly low loss and little space.
- the arc length which circumferentially characterizes the distance between the two exit edges of adjacent first vanes, is divided by the radial jet through the leading edge of the second vanes circumferentially disposed between the first two vanes in a pressure-side portion and a suction-side portion.
- a particularly advantageous embodiment of the invention provides that the second guide vanes are designed and arranged such that the second guide blade arranged downstream between the two first guide vanes is arranged in the circumferential direction closer to the suction side of the adjacent first guide vane than on the pressure side of the other adjacent first vane Vane.
- FIG. 1 shows a schematic representation of a longitudinal section of a radial turbofluid energy machine RTFEM in the section of a flow channel for a process fluid PF.
- the section shows five impellers IMP, which rotate as part of a rotor R in operation about an axis X. On this axis X all the information in this description, such as axial, radial, tangential or circumferential direction are related.
- the impellers IMP suck in each case the process fluid PF substantially axially and convey this accelerated radially outward. After exiting the impeller IMP, the process fluid PF enters a return stage BFS comprising a return channel BFC.
- the FIG. 2 shows the feedback stage BFS and the return channel BFC in detail.
- the process fluid PF passes from the impeller IMP into a first section S1 of the return channel, which is designed to conduct the process fluid PF radially outward.
- the process fluid PF is deflected from a flow direction radially outward in a flow direction radially inward.
- the process fluid PF is guided radially inward and then axially fed to the following impeller IMP.
- the deflection of the process fluid PF in the second section S2 is essentially in the form of a 180 ° arc.
- the deflection from a radially inward-pointing flow direction in the third section S3 in the axial flow direction takes place substantially in a 90 ° arc.
- first vanes L1 and second vanes L2 are arranged.
- the first vanes have an entrance edge L1LE and a exit edge L1TE.
- the second vanes L2 have an entrance edge L2LE and an exit edge L2TE.
- the leading edge L2LE of the second vane L2 is located downstream in a radial section RAD and at a smaller radius than the exit edges L1TE of the first vanes L1 - this arrangement is preferred according to the invention.
- the scope of the invention also includes embodiments in which this radial section RAD is zero or the entry edges L2LE are located in the radial region of the first guide vanes L1.
- a flow channel FC in the circumferential direction between two first vanes L1 is respectively defined by a pressure side PSL1 of a first vane L1 and a suction side SSL1 of another first vane L1.
- a connecting line CLTE can always be indicated by two outlet edges L1TE of adjacent first guide vanes L1. This connecting line CLTE extends with a radius of curvature which corresponds to the distance radius to the axis X.
- connection line CLTE An arc length BLD of this connection line CLTE between the two exit edges L1TE of the adjacent first guide vanes L1 is not divided centrally by a radial jet RS through the leading edge L2LE of the second guide vane arranged circumferentially between the two first vanes L1.
- a first subsection of this connection line CLTE is located between the leading edge L2LE of the second vane L2 and the trailing edge L1TE of the first vane L1, which delimits the relevant flow channel FC with its suction side SSB1.
- This suction-side portion SSD is smaller than the corresponding adjacent pressure-side portion PSD.
- the ratio of the suction-side portion SSD to the total arc length BLD of the connection line CLTE between the two exit edges L1TE of the first guide vanes L1 is between 0.2-0.4.
- This type of unequal distribution of the flow channel FC between the two first guide vanes L1 by means of the following guide vane L2 leads to a particularly advantageous low-loss flow through the third section S3.
Description
Die Erfindung betrifft eine Rückführstufe einer Radialturbofluidenergiemaschine, insbesondere eines Radialturboverdichters, zur Umlenkung einer Strömungsrichtung eines aus einem sich um eine Achse rotierenden Rotor austretenden Prozessfluids von radial außen nach radial innen, umfassend einen Rückführkanal, der drei in Strömungsrichtung benachbarte Abschnitte aufweist, wobei ein erster Abschnitt zur Leitung des Prozessfluids nach radial außen ausgebildet ist, wobei ein zweiter Abschnitt zur Umlenkung des Prozessfluids von radial außen nach radial innen ausgebildet ist, wobei ein dritter Abschnitt zur Leitung des Prozessfluids nach radial innen ausgebildet ist, wobei der zweite Abschnitt und der dritte Abschnitt oder nur der dritte Abschnitt erste Leitschaufeln aufweist, die Strömungskanäle des Rückführkanals in Umfangsrichtung zueinander definieren.The invention relates to a recirculation stage of a radial turbofluid energy machine, in particular a radial turbocompressor, for deflecting a flow direction of a process fluid emerging from a rotor rotating about an axis from radially outside to radially inside, comprising a return channel, which has three adjacent sections in the flow direction, wherein a first section is designed to conduct the process fluid radially outward, wherein a second portion for deflecting the process fluid is formed from radially outside to radially inside, wherein a third portion for guiding the process fluid is formed radially inward, wherein the second portion and the third portion or only the third section has first guide vanes, which define flow channels of the return channel in the circumferential direction to one another.
In einem Radialverdichter (siehe
Aus der
Die aus dem Stand der Technik bekannte Anordnung ist wenig kompakt - also verhältnismäßig raumgreifend - und die Durchströmung ist verhältnismäßig verlustbehaftet.The known from the prior art arrangement is not very compact - so relatively large space - and the flow is relatively lossy.
Ausgehend von dem Problem und Nachteilen des Standes der Technik hat es sich die Erfindung zur Aufgabe gemacht, eine Rückführstufe der eingangs definierten Art derart weiterzubilden, dass eine weniger raumgreifende Rückführstufe eine weniger verlustbehaftete Strömung erzeugt.Based on the problem and disadvantages of the prior art, the invention has the object to develop a feedback stage of the type defined in such a way that a less expansive feedback stage generates a less lossy flow.
Zur Lösung der erfindungsgemäßen Aufgabe wird eine Rückführstufe der eingangs definierten Art mit den zusätzlichen Merkmalen des kennzeichnenden Teils des Patentanspruchs 1 vorgeschlagen. Weiterhin schlägt die Erfindung eine radiale Turbofluidenergiemaschine mit einer derartigen Rückführstufe vor.To achieve the object of the invention, a return stage of the type defined is proposed with the additional features of the characterizing part of patent claim 1. Furthermore, the invention proposes a radial turbofluid energy machine with such a return stage.
Im technischen Sprachgebrauch ist es auch üblich, nur die Kombination aus dem zweiten Abschnitt mit dem dritten Abschnitt als Rückführstufe zu bezeichnen und den ersten Abschnitt als einen in Strömungsrichtung davor befindlichen Diffusor zu definieren. Die Terminologie dieses Dokumentes bezeichnet die drei hintereinander angeordneten Abschnitte (S1, S2, S3; siehe Figuren) als Rückführstufe. Hierbei ist zu beachten, dass der erste Abschnitt im Rahmen der Erfindung frei gestaltet werden kann, so dass der erste Abschnitt mit oder ohne Schaufeln, im Meriodinalschnitt in Strömungsrichtung zum Beispiel sich aufweitend, konstant oder sich verjüngend ausgebildet sein kann.In technical usage, it is also common to refer to only the combination of the second section with the third section as the return stage and to define the first section as a forward flow diffuser. The terminology of this document designates the three successive sections (S1, S2, S3, see figures) as the feedback stage. It should be noted that the first section can be freely designed within the scope of the invention, so that the first section with or without blades, in Meriodinalschnitt in the flow direction For example, it may be expanding, constant or tapering.
Im Zusammenhang mit der Erfindung sind geometrische Ausdrücke, wie axial, tangential, radial oder Umfangsrichtung stets auf eine Rotationsachse eines Laufrades einer Radialturbofluidenergiemaschine bezogen, falls im unmittelbaren Zusammenhang nichts anderes angegeben ist.
Die erfindungsgemäße Rückführstufe hat einen eindeutigen Zusammenhang zu einem derartigen Laufrad, da die Rückführstufe sich stromabwärts des Laufradaustritts bei einem Radialturboverdichter in Umfangsrichtung um das Laufrad herum erstreckt. In der Regel ist die Rückführstufe zumindest hinsichtlich der aerodynamisch relevanten Aspekte der Erfindung rotationssymmetrisch zu der Achse ausgebildet.In the context of the invention, geometric expressions, such as axial, tangential, radial or circumferential direction are always related to a rotational axis of an impeller of a radial turbofan energy machine, unless otherwise specified in the immediate context.
The return stage according to the invention has a clear relationship to such an impeller, since the return stage extends circumferentially around the impeller downstream of the impeller outlet in a radial turbocompressor. As a rule, at least with regard to the aerodynamically relevant aspects of the invention, the feedback stage is rotationally symmetrical to the axis.
Die Rückführstufe nach der Erfindung ist in Folge der in Strömungsrichtung hintereinander angeordneten ersten Leitschaufel und zweiten Leitschaufel weniger raumgreifend als eine Rückführstufe, die nicht die beiden Leitschaufelstufen hintereinander aufweist. Eine Ausrichtung der Strömung auf den Eintritt in das stromabwärts nachfolgende Laufrad ist mittels der gestuften Leitschaufelausführung aerodynamisch effizienter.As a result of the first guide vane and the second guide vane arranged one behind the other in the direction of flow, the return stage according to the invention is less bulky than a return stage which does not have the two vane stages one behind the other. Alignment of the flow to entry into the downstream impeller is aerodynamically more efficient by means of the stepped vane design.
Die erfindungsgemäß in Umfangsrichtung versetzte zweite Leitschaufelstufe bzw. die Anordnung der zweiten Leitschaufeln in Umfangsrichtung asymmetrisch zu den Austrittskanten der ersten Leitschaufeln führt zu einer Verringerung der aerodynamischen Verluste des Prozessfluids bei der Durchströmung der Rückführstufe.The inventively circumferentially offset second vane stage or the arrangement of the second vanes in the circumferential direction asymmetrically to the outlet edges of the first vanes leads to a reduction of the aerodynamic losses of the process fluid in the flow through the return stage.
Die Neuausrichtung und Umlenkung des Prozessfluids stromabwärts des Austritts aus einem Laufrad hin zu dem Eintritt des stromabwärts nachfolgenden Laufrades ist nach der Erfindung besonders verlustarm und wenig raumgreifend. Die Bogenlänge, die in Umfangsrichtung den Abstand zwischen den zwei Austrittskanten benachbarter erster Leitschaufeln charakterisiert, wird von dem radialen Strahl durch die Eintrittskante der in Umfangsrichtung zwischen den beiden ersten Schaufeln angeordneten zweiten Leitschaufeln in einem druckseitigen Abschnitt und einem saugseitigen Abschnitt geteilt.The reorientation and deflection of the process fluid downstream of the exit from an impeller to the entrance of the downstream impeller following the invention is particularly low loss and little space. The arc length, which circumferentially characterizes the distance between the two exit edges of adjacent first vanes, is divided by the radial jet through the leading edge of the second vanes circumferentially disposed between the first two vanes in a pressure-side portion and a suction-side portion.
Eine besonders vorteilhafte Weiterbildung der Erfindung sieht vor, dass die zweiten Leitschaufeln derart ausgebildet und angeordnet sind, dass die stromabwärts zwischen den beiden ersten Leitschaufeln angeordnete zweite Leitschaufel in Umfangsrichtung näher an der Saugseite der benachbarten ersten Leitschaufel angeordnet ist als an der Druckseite der anderen benachbarten ersten Leitschaufel.A particularly advantageous embodiment of the invention provides that the second guide vanes are designed and arranged such that the second guide blade arranged downstream between the two first guide vanes is arranged in the circumferential direction closer to the suction side of the adjacent first guide vane than on the pressure side of the other adjacent first vane Vane.
Es hat sich gezeigt, dass die Aufteilung der Bogenlänge, die in Umfangsrichtung den Abstand zwischen den zwei Austrittskanten benachbarter erster Leitschaufeln charakterisiert, besonders vorteilhaft ist, wenn das Verhältnis des saugseitigen Abschnitts zu der gesamten Bogenlänge zwischen 0,2 - 0,4 liegt. Dieser charakteristische Versatz hin zu der Saugseite einer ersten Leitschaufel, die in Umfangsrichtung den Strömungskanal definiert, führt zu einer turbolenzfreien und weniger ablösungsbehafteten Durchströmung, die besonders verlustarm ist.It has been found that the division of the arc length, which in the circumferential direction characterizes the distance between the two exit edges of adjacent first guide vanes, is particularly advantageous when the ratio of the suction-side portion to the total arc length is between 0.2-0.4. This characteristic offset towards the suction side of a first vane, which defines the flow channel in the circumferential direction, leads to a turbulence-free and less dissolution-dependent flow, which is particularly low loss.
Im Folgenden ist die Erfindung anhand eines speziellen Ausführungsbeispiels unter Bezugnahme auf Zeichnungen näher beschrieben. Es zeigen:
- Figur 1
- einen Längsschnitt in schematischer Darstellung durch den Strömungskanal einer Radialturbofluidenergiemaschine am Beispiel eines Einwellenverdichters,
- Figur 2
- ein Detail der
Figur 1 , das inFigur 1 mit II -II ausgewiesen ist, - Figur 3
- einen Schnitt durch einen dritten Abschnitt der Rückführstufe gemäß dem in
Figur 2 mit III-III ausgewiesenen Schnitt in einer Radialebene an der axialen Position des dritten Abschnitts.
- FIG. 1
- a longitudinal section in a schematic representation through the flow channel of a radial turbofluid energy machine using the example of a single-shaft compressor,
- FIG. 2
- a detail of
FIG. 1 , this inFIG. 1 with II -II, - FIG. 3
- a section through a third portion of the return stage according to the in
FIG. 2 with III-III designated section in a radial plane at the axial position of the third section.
Die
In dem Abschnitt S2 und dem dritten Abschnitt S3 oder nur in dem dritten Abschnitt S3 sind erste Leitschaufeln L1 und zweite Leitschaufeln L2 angeordnet. Die ersten Leitschaufeln haben eine Eintrittskante L1LE und eine Austrittskante L1TE. Die zweiten Leitschaufeln L2 haben eine Eintrittskante L2LE und eine Austrittskante L2TE. In diesem bevorzugten Ausführungsbeispiel befindet sich die Eintrittskante L2LE der zweiten Leitschaufel L2 in einem Radialabschnitt RAD stromabwärts und auf einem kleineren Radius als die Austrittskanten L1TE der ersten Leitschaufeln L1 - diese Anordnung ist nach der Erfindung bevorzugt. Dem Umfang der Erfindung sind ebenfalls Ausführungsformen zuzurechnen, bei denen dieser Radialabschnitt RAD null ist oder die Eintrittskanten L2LE sich in dem Radialbereich der ersten Leitschaufeln L1 befinden. Die Leitschaufeln L1, L2, ein Strömungskanal FC in Umfangsrichtung zwischen zwei ersten Leitschaufeln L1 ist jeweils durch eine druckseitig PSL1 einer ersten Leitschaufel L1 und eine Saugseite SSL1 einer anderen ersten Leitschaufel L1 definiert. In einer radial sich erstreckenden Ebene (Zeichnungsebene der
Claims (5)
- Backfeed stage (BFS) of a radial turbo fluid energy machine (RTFEM), especially of a radial turbocompressor, for deflecting a flow direction of a process fluid (PF) issuing from a rotor (R), rotating around an axis (X), from radially outward to radially inward,
comprising a backfeed duct (BFC),
which has three adjacent sections (S1, S2, S3) in the flow direction,
wherein a first section (S1) is designed for conducting the process fluid (PF) radially outward,
wherein a second section (S2) is designed for deflecting the process fluid (PF) from radially outward to radially inward,
wherein a third section (S3) is designed for conducting the process fluid (PF) radially inward,
wherein the second section (S2) and the third section (S3), or only the third section (S3), have/has first guide vanes (L1) which define flow passages (FC) of the backfeed duct (BFC) in relation to each other in the circumferential direction,
wherein
the second section (S2) and the third section (S3), or only the third section (S3), have/has second guide vanes (L2) which are offset downstream by leading edges (L2LE) in relation to leading edges (L1LE) of the first guide vanes (L1), which second guide vanes define flow passages (FC) of the backfeed duct (BFC) in relation to each other in the circumferential direction,
wherein the second guide vanes (L2) are designed and arranged in such a way that
in a radially extending plane in the region of the axial extent of the third section (S3) a connecting line (CLTE) through two trailing edges (L1TE) of adjacent first guide vanes (L1) is not divided in the middle by a radial line (RS) through the leading edge (L1LE) of a second guide vane (L2) which is arranged between the two first guide vanes (L1) in the circumferential direction, wherein
the first guide vanes (L1) each have a concave pressure side (PSL1) and a convex suction side (SSL1) and each flow passage (FC) in the region of the first guide vanes (L1) is defined by a pressure side (PSL1) of a first guide vane (L1) and a suction side (SSL1) of another adjacent first guide vane (L1), characterized in that
the second guide vane (L2) which is arranged downstream between the two first guide vanes (L1) is arranged closer to the suction side (SSL1) of the other adjacent first guide vane (L1) in the circumferential direction (CD). - Backfeed stage (BFS) according to Claim 1, wherein a second guide vane (L2) is specifically arranged downstream between the two first guide vanes (L1) in the circumferential direction (CD).
- Backfeed stage (BFS) according to at least one of the preceding Claims 1 and 2, wherein a bend length in the circumferential direction of the distance (BLD) between the two trailing edges (L1TE) of adjacent first guide vanes (L1) is divided by the radial line (RS) through the leading edge (L1LE) of the second guide vane (L2) which is arranged between the two first guide vanes (L1) in the circumferential direction into a pressure-side section (PSD) and a suction-side section (SSD), wherein
- Backfeed stage (BFS) according to at least one of the preceding Claims 1 to 3, wherein the first guide vanes (L1) and the second guide vanes (L2) are fixedly and immovably connected to a stator.
- Radial turbo fluid energy machine (RTFEM) having a backfeed stage (BFS) according to at least one of the preceding Claims 1 and 2.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102016203305.0A DE102016203305A1 (en) | 2016-03-01 | 2016-03-01 | Return stage, radial turbofan energy machine |
PCT/EP2017/054686 WO2017148971A1 (en) | 2016-03-01 | 2017-03-01 | Backfeed stage of a radial turbo fluid energy machine |
Publications (2)
Publication Number | Publication Date |
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EP3390832A1 EP3390832A1 (en) | 2018-10-24 |
EP3390832B1 true EP3390832B1 (en) | 2019-07-31 |
Family
ID=58191467
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP17707876.3A Active EP3390832B1 (en) | 2016-03-01 | 2017-03-01 | Backfeed stage of a radial turbo fluid energy machine |
Country Status (4)
Country | Link |
---|---|
US (1) | US10422346B2 (en) |
EP (1) | EP3390832B1 (en) |
DE (1) | DE102016203305A1 (en) |
WO (1) | WO2017148971A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3376041A1 (en) * | 2017-03-15 | 2018-09-19 | Siemens Aktiengesellschaft | Return stage and radial turbo fluid energy machine |
JP7019446B2 (en) * | 2018-02-20 | 2022-02-15 | 三菱重工サーマルシステムズ株式会社 | Centrifugal compressor |
JP2022099003A (en) * | 2020-12-22 | 2022-07-04 | 株式会社日立インダストリアルプロダクツ | Centrifugal compressor and manufacturing method thereof |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE157924C (en) * | ||||
DE723824C (en) * | 1935-05-27 | 1942-08-11 | Escher Wyss Maschf Ag | Multi-stage centrifugal compressor or multi-stage centrifugal pump |
US4824325A (en) * | 1988-02-08 | 1989-04-25 | Dresser-Rand Company | Diffuser having split tandem low solidity vanes |
JPH0244516A (en) | 1988-08-05 | 1990-02-14 | Mitsubishi Electric Corp | Magnetic head |
JPH11173299A (en) | 1997-12-05 | 1999-06-29 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor |
JP2009244516A (en) | 2008-03-31 | 2009-10-22 | Fuji Seal International Inc | Neck label and container with neck label |
JP6339794B2 (en) | 2013-11-12 | 2018-06-06 | 株式会社日立製作所 | Centrifugal turbomachine |
-
2016
- 2016-03-01 DE DE102016203305.0A patent/DE102016203305A1/en not_active Withdrawn
-
2017
- 2017-03-01 EP EP17707876.3A patent/EP3390832B1/en active Active
- 2017-03-01 US US16/079,625 patent/US10422346B2/en not_active Expired - Fee Related
- 2017-03-01 WO PCT/EP2017/054686 patent/WO2017148971A1/en active Application Filing
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP3390832A1 (en) | 2018-10-24 |
US20190055960A1 (en) | 2019-02-21 |
DE102016203305A1 (en) | 2017-09-07 |
WO2017148971A1 (en) | 2017-09-08 |
US10422346B2 (en) | 2019-09-24 |
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