EP3577347B1 - Turbo-compresseur avec canaux de retour de fluide - Google Patents

Turbo-compresseur avec canaux de retour de fluide Download PDF

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Publication number
EP3577347B1
EP3577347B1 EP18729651.2A EP18729651A EP3577347B1 EP 3577347 B1 EP3577347 B1 EP 3577347B1 EP 18729651 A EP18729651 A EP 18729651A EP 3577347 B1 EP3577347 B1 EP 3577347B1
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EP
European Patent Office
Prior art keywords
flow
flow channels
turbocompressor
compressor stage
compressor
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
EP18729651.2A
Other languages
German (de)
English (en)
Other versions
EP3577347A1 (fr
Inventor
Markus ENGERT
Angelika Klostermann
Daniel Conrad
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.)
Ebm Papst Mulfingen GmbH and Co KG
Original Assignee
Ebm Papst Mulfingen 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.)
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Publication of EP3577347A1 publication Critical patent/EP3577347A1/fr
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Publication of EP3577347B1 publication Critical patent/EP3577347B1/fr
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Classifications

    • 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
    • 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
    • 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
    • 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
    • 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
    • F04D29/30—Vanes

Definitions

  • the invention relates to a turbo compressor with a recirculation geometry for an optimized flow connection of a first and second compressor stage of the turbo compressor.
  • the invention is therefore based on the object of providing a recirculation geometry for a turbo compressor which reduces the risk of flow separation and minimizes the pressure loss.
  • a recirculation geometry of a turbo compressor which is designed for flow connection of a first and second compressor stage of the turbo compressor.
  • the recirculation geometry has a plurality of partial spirals which are arranged uniformly distributed in the circumferential direction and run at least partially in the circumferential direction.
  • the word component “geometry” is included in “return geometry”, but determines the resulting flow line due to the formation of the flow channels.
  • the plurality of flow channels reduces the flow cross section of each individual flow channel and offers a more even inflow into the second compressor stage.
  • the maximum extent, in particular in the radial direction, of each individual channel can be increased compared to a single rotationally symmetrical return channel without large-area flow separations or backflows being observed at operating points with low mass flow.
  • the flow channels form a plurality of elbows arranged one after the other, which repeatedly deflect the flow between the first and second compressor stages. In this way it is possible to realize an optimal axial flow against the compressor impeller of the second compressor stage from the radial outflow direction of the compressor impeller of the turbocompressor in the first compressor stage.
  • the elbows of the flow channels direct the flow from a radial outflow direction first into a first axial direction in the direction of the second compressor stage and then back into a radial inflow direction, which runs counter to the outflow direction.
  • the last elbow of the flow channels viewed in the flow direction, then directs the flow to the inflow direction in a second axial direction, which runs counter to the first axial direction.
  • the second axial direction corresponds to the intake direction of the compressor impeller of the second compressor stage, so that a predefined inflow exactly to the intake area via the flow channels of the compressor impeller of the second compressor stage can take place.
  • the bends each produce an essentially 90° deflection.
  • the compressor impeller of the second compressor stage can be arranged in the same direction as the compressor impeller of the previous compressor stage, i.e. the direction of entry is the same for both compressor impellers.
  • both compressor impellers can also be arranged in opposite directions, i.e. in a so-called back-to-back arrangement, which is mainly useful for two-stage turbo compressors, with the outflow geometry of the second compressor stage, which is designed as a spiral, for example, and the subsequent outlet pipe passing through the area between the individual Partial spirals of the return geometry can be performed.
  • the invention is not limited to two-stage turbo compressors, but can also be applied to multi-stage designs.
  • the flow channels of the partial spirals extend from an inlet area of the first compressor stage, in particular from the outlet area of the impeller of the first compressor stage, to an outlet area of the first compressor stage, in particular to the inlet area of the impeller of the second compressor stage, and in the Combine the outlet area to form a circumferentially symmetrical overall channel.
  • the overall channel then forms the inflow for or into the second compressor stage.
  • an exemplary embodiment of the return geometry is characterized in that the individual flow channels each have curved walls and/or curved twist struts in a transition to the overall channel exhibit.
  • the swirl struts are designed to impart a predefined swirl to the flow as it enters the overall channel, which effectively promotes intake through the compressor wheel of the second compressor stage.
  • the return geometry is designed according to the invention in such a way that the elbow formed in the flow channels, which deflects the flow from the radial outflow direction into the first axial direction in the direction of the second compressor stage, has a guide strut, which extends along the respective flow channel in Extends radially outward and in the first axial direction.
  • the guide struts divide the respective flow channel in the middle, so that both remaining parts of the respective flow channel are flown through with the same large mass flow. It is also provided in a development that the guide struts extend radially outside of a tongue radius of the return geometry, i.e. at a distance radially outwards from an inlet of the respective flow channel formed by the tongue radius.
  • the return geometry is also provided according to the invention, in which the flow channels have an axial section in which the flow is directed in the first axial direction in the direction of the second compressor stage, and the axial section of the flow channels is designed as a diffuser.
  • the respective axial section as a diffuser, the flow is decelerated, friction losses are reduced and static pressure is built up.
  • the axial section of the recirculation geometry advantageously runs parallel to an axis of rotation of the turbo compressor.
  • an embodiment of the recirculation geometry is favorable in which the flow channels can be assigned to one of the first compressor stage Inflow radial section and an outflow radial section that can be assigned to the second compressor stage, which direct the flow in each case in the inflow direction or in the outflow direction, before the flow fluid preferably flows out axially from the return geometry.
  • the embodiment is advantageous in which the flow channels in the outflow radial section widen in terms of their cross section in the direction of flow, so that an acceleration of the flow in the outflow radial section is reduced or even avoided.
  • the flow channels of the partial spirals of the recirculation geometry are formed in a compact design by an intermediate disk housing of the turbo compressor, which separates the first compressor stage from the second compressor stage.
  • the flow channels may extend in the outer peripheral surface of the washer housing.
  • the flow channels of the partial spirals are formed by the intermediate disk housing and the turbo compressor housing, the flow channels being formed by a channel free space between an outer surface of the intermediate disk housing and an inner wall surface of the turbo compressor housing.
  • the flow channels run in the outer peripheral surface of the washer housing and are covered by the turbo compressor housing.
  • the turbo compressor housing and the intermediate disk housing can also be designed in multiple parts.
  • the intermediate disk housing has an axial opening for receiving the compressor impeller of the first compressor stage with an axial opening radius R1 and the flow channels of the partial spirals extend from the tongue radius R2 of the intermediate disk housing.
  • the tongue radius is set to be 1.4 - 1.8 times larger than the axial opening radius R1.
  • the outflow direction of the compressor impeller of the first compressor stage and the inflow direction into the flow channels can thus be matched to one another with regard to the outflow angle and inflow angle.
  • an advantageous embodiment provides that the ratio of the extension (a1) of the flow channels of the partial spirals in the circumferential direction to adjacent circumferential sections (a2) without flow channels is formed, so that 0.2 ⁇ a1/(a1 +a2) ⁇ 0.5.
  • a turbo compressor 1 is shown schematically with a turbo compressor housing 3 and an intermediate disc housing 2 accommodated therein.
  • a compressor impeller 6 of the first compressor stage is arranged on the intermediate disc housing 2 at the flow inlet 4, partially inserted into an axial opening, which sucks in a flow fluid axially and blows it out radially in the direction of the second compressor stage.
  • the compressor impeller 7 of the second compressor stage is arranged axially separated from the compressor impeller 6, which also sucks in the flow fluid axially and blows it out radially in the direction of the outlet 11 of the intermediate disc housing 2 and finally the outlet 12 on the turbo compressor housing 3.
  • the turbo compressor housing 3 and the intermediate disk housing 2 provide a recirculation geometry for the flow connection of the first and second compressor stages with several partial spirals arranged evenly distributed in the circumferential direction, the flow channels running separately from one another 5 for establishing the flow connection from the inlet area of the first compressor stage to the outlet area of the second compressor stage, as shown in the exploded view according to FIG figure 2 and 3 can be seen.
  • the flow channels 5 are each created by a channel free space between the outer surface of the intermediate disk housing 2 and the inner wall surface of the turbo compressor housing 3.
  • the geometry of the respective flow channels 5 can be determined by both components or, for example, only by the intermediate disk housing 2, as in the case shown.
  • the recirculation geometry for the flow connection of the first and second compressor stage is generated by seven partial spirals, each with identical flow channels 5, which extend radially outwards from the flow inlet 4 and at the same time in the circumferential direction.
  • the flow is deflected multiple times by the manifolds 15, 16 provided in the flow channels 5, namely through the first manifold 15 from a substantially radial outflow direction into a first axial direction in the direction of the second compressor stage and then through the second manifold 16 back into the radial direction Inflow direction, which runs counter to the outflow direction.
  • the third elbow of the flow channels 5 is located within the intermediate disc housing 2 and is therefore not visible, but then directs the flow to the inflow direction in a second axial direction, which runs counter to the first axial direction.
  • a guide strut 8 is provided in each of the flow channels 5, which extends in the radial and axial direction over the first bend 15 and divides the flow fluid in the respective flow channel 5 centrally during the first deflection.
  • the geometric shape of the intermediate disk housing 2 is designed in such a way that the flow channels 5 extend from the inlet area with the flow inlet 4 of the first compressor stage to the outlet area of the first compressor stage and in the outlet area to form a circumferentially symmetrical overall channel 9 with a radius R9 and a central section through which there is no flow extend the axis of rotation with a radius R10.
  • the ratio a1/(a1+2) is set in a range of 0.2-0.5.
  • all flow channels 5 have the same size and the same flow cross section, but they can also be designed differently from one another, so that, for example, the length a1 of each flow channel or some flow channels 5 varies, so that a1 1 +a2 1 ⁇ a1 2 + would apply a2 2 .
  • the individual flow channels 5 each have curved twist struts in the transition to the overall channel 9, which impart a twist to the flow as it enters the overall channel 9, so that the flow at the outlet into the second compressor stage has a predefined twist.
  • the twist struts are as a negative in the in 7 indicated flow with the reference numeral 22 'and have an opening angle a5.
  • the flow channels 5 are designed as diffusers in their axial section z, in which the flow is directed in the first axial direction in the direction of the second compressor stage, and have a diffuser angle a4, the condition [R5(z) 2 -R4(z) 2 ] (a1 ⁇ n)/360 ⁇ 2 ⁇ R2 b2 is satisfied.
  • R5 is the outer radius as a function of the axial coordinate z
  • R4 is the radius of the inner wall of the flow channel 5 as a function of the axial coordinate z
  • R2 is the tongue radius or outlet radius of the return geometry
  • b2 is the flow channel width in the outflow radial section.
  • the diffusion ratio R2/R1 is set in a range of 1.4-1.8.
  • the diffuser angle is formed in section z2 of the axial section z, which defines part of the straight axial extension z1.
  • the flow channel width b2 in the radial outflow direction section is smaller than the flow channel widths b6 and b7 in the opposite radial inflow direction section.
  • the radial deflection and merging of the flow 5' is designed in such a way that the flow velocities are changed as little as possible or not at all.
  • b6 is the flow channel width adjacent to the second bend 16 at radius R6 and b7 is the flow channel width immediately before the third bend at radius R7, according to FIG figure 6 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Turbocompresseur (1) de conception radiale avec une géométrie de recirculation pour le raccordement d'écoulement d'un premier et d'un second étage de compresseur du turbocompresseur (1), dans lequel la géométrie de recirculation présente une pluralité de spirales partielles qui sont réparties uniformément ou inégalement dans la direction circonférentielle et s'étendent au moins partiellement dans la direction circonférentielle, qui forment des canaux d'écoulement (5) s'étendant au moins par sections séparément les uns des autres pour le raccordement d'écoulement du premier et du second étage de compresseur, dans lequel les canaux d'écoulement (5) forment une pluralité de coudes (15, 16) disposés les uns après les autres, qui dévient plusieurs fois l'écoulement entre le premier et le second étage de compresseur,
    dans lequel les coudes des canaux d'écoulement (5) guident l'écoulement depuis une direction d'évacuation radiale dans une première direction axiale en direction du second étage de compresseur, puis de nouveau dans une direction d'admission radiale, qui s'oppose à la direction d'évacuation,
    dans lequel les canaux d'écoulement (5) présentent une section axiale, dans laquelle l'écoulement est dirigé dans la première direction axiale en direction du second étage de compresseur, dans lequel la section axiale des canaux d'écoulement (5) est conçue sous la forme d'un diffuseur,
    caractérisé en ce que
    le coude (15) formé respectivement dans les canaux d'écoulement (5), qui dévie l'écoulement de la direction d'évacuation radiale dans la première direction axiale en direction du second étage de compresseur, présente respectivement une entretoise de guidage (8), qui s'étend le long du canal d'écoulement respectif dans la direction radiale vers l'extérieur et dans la première direction axiale.
  2. Turbocompresseur selon la revendication 1, caractérisé en ce que l'un des coudes des canaux d'écoulement (5) dirige alors l'écoulement vers la direction d'admission dans une seconde direction axiale qui s'oppose à la première direction axiale.
  3. Turbocompresseur selon l'une des revendications précédentes, caractérisé en ce que les canaux d'écoulement (5) s'étendent d'une zone d'entrée pouvant être associée au premier étage de compresseur à une zone de sortie pouvant être associée au premier étage de compresseur et se rejoignent dans la zone de sortie pour former un canal global à symétrie circonférentielle (9).
  4. Turbocompresseur selon les revendications précédentes 2 et 3, caractérisé en ce que les canaux d'écoulement (5) se rejoignent dans le sens de l'écoulement pour former le canal global (9) en aval du coude, qui dirige l'écoulement dans la seconde direction axiale.
  5. Turbocompresseur selon la revendication précédente, caractérisé en ce que les différents canaux d'écoulement (5) présentent chacun, dans une transition vers le canal global (9), des parois incurvées ou des entretoises de torsion incurvées, qui sont conçues pour conférer une torsion à l'écoulement lorsqu'il pénètre dans le canal global (9), de sorte que l'écoulement présente une torsion prédéfinie à la sortie dans le second étage de compresseur.
  6. Turbocompresseur selon l'une des revendications précédentes 1 à 5, caractérisé en ce que les canaux d'écoulement (5) présentent une section radiale d'admission pouvant être associée au premier étage de compresseur et une section radiale d'évacuation pouvant être associée au second étage de compresseur, qui dirigent l'écoulement dans la direction d'admission et dans la direction d'évacuation, dans lequel les canaux d'écoulement (5) s'élargissent dans la section radiale d'évacuation par rapport à leur section transversale dans le sens de l'écoulement.
  7. Turbocompresseur selon l'une des revendications précédentes, caractérisé en ce qu'il est formé par un carter de disque intermédiaire (2) d'un turbocompresseur (1) qui sépare le premier étage de compresseur du second étage de compresseur.
  8. Turbocompresseur selon la revendication précédente, caractérisé en ce que les canaux d'écoulement (5) des spirales partielles sont formés par le carter de disque intermédiaire (2) et un carter de turbocompresseur (3), dans lequel les canaux d'écoulement (5) sont formés par un espace libre de canal entre une surface extérieure du carter de disque intermédiaire (2) et une surface de paroi intérieure du carter de turbocompresseur (3).
  9. Turbocompresseur selon l'une des deux revendications précédentes, caractérisé en ce que le carter de disque intermédiaire (2) présente une ouverture axiale pour recevoir la roue de compresseur du premier étage de compresseur avec un rayon d'ouverture axiale R1 et les canaux d'écoulement (5) des spirales partielles s'étendent à partir d'un rayon de languette R2 du carter de disque intermédiaire (2), dans lequel le rayon de languette est 1,4 à 1,8 fois plus grand que le rayon d'ouverture axiale R1.
  10. Turbocompresseur selon la revendication précédente, caractérisé en ce que les spirales partielles s'étendent radialement vers l'extérieur à une entrée des canaux d'écoulement (5) déterminée par le rayon de languette R2 selon un angle a3 = 60° - 80° par rapport à un plan radial dans la direction circonférentielle.
  11. Turbocompresseur selon l'une des deux revendications précédentes, caractérisé en ce qu'il est formé un rapport entre l'extension (a1) des canaux d'écoulement (5) des spirales partielles dans la direction circonférentielle et les sections circonférentielles adjacentes (a2) sans canaux d'écoulement, de sorte que 0,2 ≤ a1/(a1+ a2) ≤ 0,5.
  12. Turbocompresseur selon l'une des revendications précédentes, caractérisé en ce qu'au moins deux des canaux d'écoulement (5) pour le raccordement d'écoulement du premier et du second étage de compresseur présentent une section transversale d'écoulement globale différente l'un de l'autre.
EP18729651.2A 2017-06-27 2018-06-05 Turbo-compresseur avec canaux de retour de fluide Active EP3577347B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017114232.0A DE102017114232A1 (de) 2017-06-27 2017-06-27 Rückführgeometrie eines Turboverdichters
PCT/EP2018/064772 WO2019001910A1 (fr) 2017-06-27 2018-06-05 Canaux d'écoulement de retour pour turbocompresseur à plusieurs étages

Publications (2)

Publication Number Publication Date
EP3577347A1 EP3577347A1 (fr) 2019-12-11
EP3577347B1 true EP3577347B1 (fr) 2022-04-27

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Application Number Title Priority Date Filing Date
EP18729651.2A Active EP3577347B1 (fr) 2017-06-27 2018-06-05 Turbo-compresseur avec canaux de retour de fluide

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US (1) US11519424B2 (fr)
EP (1) EP3577347B1 (fr)
CN (1) CN207406386U (fr)
DE (1) DE102017114232A1 (fr)
WO (1) WO2019001910A1 (fr)

Citations (1)

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Publication number Priority date Publication date Assignee Title
US984189A (en) * 1908-06-27 1911-02-14 William C Brown Centrifugal and turbine pump and the like.

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US2900126A (en) * 1953-08-29 1959-08-18 Austin Motor Co Ltd Centrifugal compressors
CH331941A (de) * 1955-01-27 1958-08-15 Buechi Alfred J Dipl Ing Verfahren zur Herstellung eines Satzes von Zentrifugalfördermaschinen und nach diesem Verfahren hergestellter Maschinensatz
GB854127A (en) * 1957-06-28 1960-11-16 Power Jets Res & Dev Ltd Improvements in or relating to radial-flow compressors and turbines
US3171353A (en) * 1962-02-27 1965-03-02 Kenton D Mcmahan Centrifugal fluid pump
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JP5611307B2 (ja) 2012-11-06 2014-10-22 三菱重工業株式会社 遠心回転機械のインペラ、遠心回転機械
JP6133748B2 (ja) 2013-10-09 2017-05-24 三菱重工業株式会社 インペラ及びこれを備える回転機械
AT516978B1 (de) * 2015-03-26 2018-04-15 Avl List Gmbh Mehrstufiger abgasturbolader

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
US984189A (en) * 1908-06-27 1911-02-14 William C Brown Centrifugal and turbine pump and the like.

Also Published As

Publication number Publication date
WO2019001910A1 (fr) 2019-01-03
CN207406386U (zh) 2018-05-25
DE102017114232A1 (de) 2018-12-27
US20200080569A1 (en) 2020-03-12
EP3577347A1 (fr) 2019-12-11
US11519424B2 (en) 2022-12-06

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