EP3390832A1 - Étage de retour d'une turbomachine à énergie fluidique radiale - Google Patents

Étage de retour d'une turbomachine à énergie fluidique radiale

Info

Publication number
EP3390832A1
EP3390832A1 EP17707876.3A EP17707876A EP3390832A1 EP 3390832 A1 EP3390832 A1 EP 3390832A1 EP 17707876 A EP17707876 A EP 17707876A EP 3390832 A1 EP3390832 A1 EP 3390832A1
Authority
EP
European Patent Office
Prior art keywords
section
guide vanes
circumferential direction
process fluid
vanes
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.)
Granted
Application number
EP17707876.3A
Other languages
German (de)
English (en)
Other versions
EP3390832B1 (fr
Inventor
Viktor Hermes
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.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3390832A1 publication Critical patent/EP3390832A1/fr
Application granted granted Critical
Publication of EP3390832B1 publication Critical patent/EP3390832B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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 feedback stage of a Radialturbo- fluid energy machine, in particular a Radialturboverdich ⁇ ters, for deflecting a flow direction of a flowing out of a is rotating about an axis rotor process fluid from radially outside to radially inside, comprising a return duct, which three adjacent in the flow direction Ab ⁇ sections, wherein a first portion for guiding the process fluid is formed radially outward, wherein a second portion for deflecting the process fluid from radially outside to radially inside is formed, wherein a third section for guiding the process fluid radially is formed inside, wherein the second portion and the third portion or only the third portion first guide vanes, which define flow channels of the return channel in the circumferential direction to each other.
  • the fluid to be compressed leaves an impeller rotating in the radial direction about an axis with a significant speed component in the circumferential direction (swirl).
  • the following in the flow direction static aerodynamic components have the task of implementing the power supplied in the impeller kineti ⁇ specific energy into pressure.
  • the fluid In the case of a multistage single-shaft compressor, as known from JP000244516, for example, the fluid must also be conducted to the following impeller. Furthermore, the flow of the swirl is to escape, so that the following impeller is flowed largely swirl-free.
  • a so ⁇ said feedback stage comprising a first section, which leads radially outwards, the process fluid to a second portion of the substantially corresponding to a 180 ° bend and a third portion for guiding the process fluid radially inward to the inlet in the downstream impeller.
  • 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 return blading can consist of individual blades arranged in the circumferential direction, as is known from JP 11173299-A.
  • the invention has made it to the task einzu ⁇ form a feedback stage of the type defined that a less expansive feedback stage generates a less lossy flow.
  • the first section can be freely designed within the scope of the invention so that the first section with or without blades, for example in the Meriodinal section in the flow direction, can be widening, constant or tapering.
  • the feedback stage according to the invention has a clear relationship to such an impeller, since the recirculation stage extends downstream of the impeller outlet in a radial turbo ⁇ compressor in the circumferential direction around the impeller around.
  • the feedback stage is designed to be rotationally symmetrical with respect to the axis.
  • the recirculation 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 succeeding impeller is aerodynamically more efficient by means of the stepped vane design.
  • the inventively circumferentially offset second Leit ⁇ blade stage or the arrangement of the second vanes in the circumferential direction asymmetrically to the exit 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 redirection and diversion of the process fluid downstream ⁇ Winderson of the outlet of an impeller toward the inlet of the subsequent downstream impeller is particularly low-loss according to the invention and little ground covering.
  • the arc length circumferentially characterizing the distance between the two exit edges of adjacent first vanes is shared 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 development of the invention provides that the second guide vanes are designed and arranged in such a way that the second guide vane arranged downstream between the two first vanes is arranged closer to the suction side of the adjacent first vane in the circumferential direction than on the pressure side of the other adjacent first vane.
  • FIG. 1 shows a longitudinal section in a schematic illustration through the flow channel of a radial turbofluid energy machine using the example of FIG
  • FIG. 1 shows a schematic representation of a longitudinal section of a radial ⁇ Turbo fluid energy machine RTFEM in the section of a flow channel for a process fluid PF.
  • the section shows five impellers IMP, which are part of a rotor R in operation rotate about an axis X. All information in this description, such as axi ⁇ al, radial, tangential or circumferential direction are related to this axis X.
  • the impellers IMP suck the process fluid PF essentially axially in each case and convey it accelerated radially outward. After exiting the impeller, the IMP Pro ⁇ zessfluid PF enters a feedback stage comprising a BFS
  • FIG. 2 shows the feedback stage BFS or the
  • the process fluid PF passes from the impeller IMP in a first section Sl of
  • first vanes LI and second vanes L2 are arranged in the section S2 and the third section S3 or only in the third section S3.
  • the first vanes have a leading edge L1LE and a trailing edge LITE.
  • the second vanes L2 have an entrance edge L2LE and an exit edge L2TE.
  • the leading edge of the two L2LE ⁇ th vane L2 is in a radial section RAD downstream and on a smaller radius than the outlet edges of the first vanes LITE LI - this arrangement is preferred according to the invention.
  • the scope of the invention are also attributed embodiments in which this Radialab- b
  • RAD is zero or the entry edges L2LE are in the radial area of the first vanes LI.
  • the vanes LI, L2, a flow channel FC in the circumferential direction between two first vanes LI is in each case by a pressure side PSL1 a first vane and a suction side LI SSL1 another first vane LI defi ned ⁇ .
  • a connecting line CLTE by two trailing edges of adjacent first LITE vanes LI can always be indicated.
  • This connecting line CLTE extends with a radius of curvature which corresponds to the distance radia ⁇ us to the axis X.
  • Arc length BLD of the connecting line CLTE between the two exit edges LITE of the first guide vanes LI is between 0.2-0.4. This type of unequal distribution of the flow channel FC between the two first Leitschau- fine LI means of the following vane L2 leads to a particularly advantageous low-loss flow through the third section S3.

Abstract

L'invention concerne un étage de retour (BFS) d'une turbomachine à énergie fluidique radiale (RTFEM), en particulier un turbocompresseur radial (RTC), destiné à dévier la direction d'écoulement (FD) d'un fluide de processus (PF) sortant d'un rotor (R) tournant sur un axe (X) radialement de l'extérieur vers l'intérieur, comportant un conduit de retour (BFC) qui comporte trois parties (S1, S2, S3) adjacentes dans la direction d'écoulement, une première partie (S1) étant conçue pour faire guider le fluide de processus (PF) radialement vers l'extérieur, une deuxième partie (S2) étant conçue pour dévier le fluide de processus (PF) radialement de l'extérieur vers l'intérieur, et une troisième partie (S3) étant conçue pour guider le fluide de processus (PF) radialement vers l'intérieur. La deuxième partie (S2) et la troisième partie (S3) ou seulement la troisième partie (S3) comportent des premières aubes directrices (L1) qui définissent des canaux d'écoulement (FC) du conduit de retour (BFC) les uns par rapport aux autres dans la direction périphérique. Selon l'invention, pour améliorer le rendement, la deuxième partie (S2) et la troisième partie (S3) ou seulement la troisième partie (S3) comportent des deuxièmes aubes directrices (L2) dont les bords d'attaque (L2LE) sont décalés par rapport aux bords d'attaque (L1LE) des premières aubes directrices (L1) et qui définissent des canaux d'écoulement (FC) du conduit de retour (BFC) les uns par rapport aux autres dans la direction périphérique. Les deuxièmes aubes directrices (L2) sont conçues et disposées de telle sorte que, dans un plan radial situé au niveau de l'extension axiale de la troisième partie (S3), une ligne de liaison (CLTE) passant par deux bords de fuite (L1TE) de premières aubes directrices adjacentes (L1) n'est pas divisée au milieu par un faisceau radial (RS) passant par le bord d'attaque (L1LE) d'une deuxième aube directrice (L2) disposée dans la direction périphérique entre les deux premières aubes directrices (L1).
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

Publications (2)

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

Family

ID=58191467

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17707876.3A Active EP3390832B1 (fr) 2016-03-01 2017-03-01 Étage de retour d'une turbomachine à énergie fluidique radiale

Country Status (4)

Country Link
US (1) US10422346B2 (fr)
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

Family Cites Families (7)

* Cited by examiner, † Cited by third party
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

Also Published As

Publication number Publication date
US10422346B2 (en) 2019-09-24
US20190055960A1 (en) 2019-02-21
EP3390832B1 (fr) 2019-07-31
DE102016203305A1 (de) 2017-09-07
WO2017148971A1 (fr) 2017-09-08

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