EP3390832B1 - Étage de retour d'une turbomachine à énergie fluidique radiale - Google Patents

Étage de retour d'une turbomachine à énergie fluidique radiale Download PDF

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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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Prior art keywords
section
guide vanes
circumferential direction
backfeed
guide
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EP17707876.3A
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German (de)
English (en)
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EP3390832A1 (fr
Inventor
Viktor Hermes
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Siemens AG
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Siemens AG
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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
    • 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
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • 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
    • 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
    • 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.

Claims (5)

  1. Etage (BFS) de retour d'une turbomachine (RTFEM) radiale à énergie fluidique, notamment d'un turbocompresseur radial pour dévier un sens d'écoulement d'un fluide (PF) de processus sortant d'un rotor (R) tournant autour d'un axe (Y), de l'extérieur radialement vers l'intérieur radialement, comprenant un canal (BFC) de retour, qui a trois parties (S1, S2, S3) voisines dans la direction d'écoulement,
    dans lequel une première partie (S1) est constituée pour conduire le fluide (PF) de processus vers l'extérieur radialement,
    dans lequel une deuxième partie (S2) est constituée pour dévier le fluide (PF) de processus de l'extérieur radialement vers l'intérieur radialement,
    dans lequel une troisième partie (S3) est constituée pour conduire le fluide (PF) de processus vers l'intérieur radialement,
    dans lequel la deuxième partie (S2) et la troisième partie (S3) ou seulement la troisième partie (S3) a de premières aubes (L1) directrices, qui définissent, les unes par rapport aux autres, des canaux (FC) d'écoulement du canal (BFC) de retour dans la direction périphérique,
    dans lequel
    la deuxième partie (S2) et la troisième partie (S3) ou seulement la troisième partie (S3) a des deuxièmes aubes (L2) directrices, décalées vers l'aval par des bords (L2LE) d'entrée par rapport aux bords (L1LE) d'entrée des premières aubes (L1) directrices, deuxième aubes (L2), qui définissent entre elles des canaux (FC) d'écoulement du canal (BFC) de retour dans la direction périphérique,
    dans lequel les deuxième aubes (L2) directrices sont constituées et disposées de manière à ce que, dans un plan s'étendant radialement, dans la région de l'étendue axiale de la troisième partie (S3), une ligne (CLTE) de liaison, passant par deux bords (L1TE) de sortie de premières aubes (L1) directrices voisines, ne soit pas séparée au milieu d'un rayon (RS) radial par le bord (L2LE) d'entrée d'une deuxième aube (L2) directrice, disposée dans la direction périphérique entre les deux premières aubes (L1) directrices,
    dans lequel les premières aubes (L1) directrices ont chacune un intrados (PSL1) concave et un extrados (SSL1) convexe et chaque canal (FC) d'écoulement est défini dans la région des premières aubes (L1) directrices par un intrados (PSL1) d'une première aube (L1) directrice et un extrados (SSL1) d'une autre première aube (L1) directrice voisine, caractérisé en ce que
    la deuxième aube (L2) directrice, disposée en aval, entre les deux premières aubes (L1) directrices, est, dans la direction (CD) périphérique, près de l'extrados (SSL1) de l'autre première aube (L1) directrice voisine.
  2. Etage (BFS) de retour suivant la revendication 1, dans lequel exactement une deuxième aube (L2) directrice est disposée en aval dans la direction (CD) périphérique entre les deux premières aubes (L1) directrices.
  3. Etage (BFS) de retour suivant au moins l'une des revendications 1 à 2 précédentes, dans lequel une longueur d'arc, dans la direction périphérique de la distance (BLD) entre les deux bords (L1TE) de sortie de premières aubes (L1) directrices voisines, est séparée du rayon (RS) radial par le bord (L1LE) d'entrée de la deuxième aube (L2) directrice, disposée dans la direction périphérique entre les deux premières aubes (L1) directrices, en une partie (PSD) du côté d'intrados et en une partie (SSD) du côté d'extrados en ayant : 0,2 < SSD / BLD < 0,4 .
    Figure imgb0003
  4. Etage (BFS) de retour suivant au moins l'une des revendications 1 à 3 précédentes, dans lequel les premières aubes (L1) directrices et les deuxièmes aubes (L2) directrices sont reliées, fixement et sans possibilité de se déplacer, à un stator.
  5. Turbomachine (RTFEM) radiale à énergie fluidique, ayant un stade (BFS) de retour suivant au moins l'une des revendications 1 à 2 précédentes.
EP17707876.3A 2016-03-01 2017-03-01 Étage de retour d'une turbomachine à énergie fluidique radiale Active EP3390832B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016203305.0A DE102016203305A1 (de) 2016-03-01 2016-03-01 Rückführstufe, Radialturbofluidenergiemaschine
PCT/EP2017/054686 WO2017148971A1 (fr) 2016-03-01 2017-03-01 Étage de retour d'une turbomachine à énergie fluidique radiale

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EP3390832A1 EP3390832A1 (fr) 2018-10-24
EP3390832B1 true EP3390832B1 (fr) 2019-07-31

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EP (1) EP3390832B1 (fr)
DE (1) DE102016203305A1 (fr)
WO (1) WO2017148971A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3376041A1 (fr) * 2017-03-15 2018-09-19 Siemens Aktiengesellschaft Étage de recirculation et turbomachine à énergie fluidique radiale
JP7019446B2 (ja) 2018-02-20 2022-02-15 三菱重工サーマルシステムズ株式会社 遠心圧縮機
JP2022099003A (ja) * 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 遠心圧縮機およびその製造方法

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Publication number Priority date Publication date Assignee Title
DE157924C (fr) *
DE723824C (de) * 1935-05-27 1942-08-11 Escher Wyss Maschf Ag Mehrstufiger Fliehkraftverdichter bzw. mehrstufige Fliehkraftpumpe
US4824325A (en) * 1988-02-08 1989-04-25 Dresser-Rand Company Diffuser having split tandem low solidity vanes
JPH0244516A (ja) 1988-08-05 1990-02-14 Mitsubishi Electric Corp 磁気ヘッド
JPH11173299A (ja) 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd 遠心圧縮機
JP2009244516A (ja) 2008-03-31 2009-10-22 Fuji Seal International Inc 首掛けラベル、及び首掛けラベル付き容器
JP6339794B2 (ja) * 2013-11-12 2018-06-06 株式会社日立製作所 遠心形ターボ機械

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WO2017148971A1 (fr) 2017-09-08
US10422346B2 (en) 2019-09-24
DE102016203305A1 (de) 2017-09-07
EP3390832A1 (fr) 2018-10-24
US20190055960A1 (en) 2019-02-21

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