EP3568597A1 - Étage de retour et turbomachine à énergie fluidique radiale - Google Patents

Étage de retour et turbomachine à énergie fluidique radiale

Info

Publication number
EP3568597A1
EP3568597A1 EP18707245.9A EP18707245A EP3568597A1 EP 3568597 A1 EP3568597 A1 EP 3568597A1 EP 18707245 A EP18707245 A EP 18707245A EP 3568597 A1 EP3568597 A1 EP 3568597A1
Authority
EP
European Patent Office
Prior art keywords
vanes
section
guide vanes
bfs
process fluid
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
EP18707245.9A
Other languages
German (de)
English (en)
Other versions
EP3568597B1 (fr
Inventor
Nico Petry
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 Energy Global GmbH and Co KG
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 EP3568597A1 publication Critical patent/EP3568597A1/fr
Application granted granted Critical
Publication of EP3568597B1 publication Critical patent/EP3568597B1/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
    • 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
    • F04D29/26—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
    • F04D29/40—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
    • F04D29/40—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

Definitions

  • the invention relates to a return stage of a radial turbo fluid energy machine, in particular a Radialturboverdich ⁇ ters, for deflecting a flow direction of an emerging from an axis rotating impeller process fluid from radially outside to radially inside, comprising a nen ring around the axis extending return channel having four adjacent portions in the flow direction, wherein a first portion for guiding the process fluid is formed radially outward, wherein a ter ⁇ ter ⁇ ter section for deflecting the process fluid from radially outside to radially inwardly formed wherein a third Ab ⁇ section for guiding the process fluid is formed radially inward from ⁇ , wherein a fourth section is formed for redirecting the process fluid in the axial direction, wherein the third section first guide vanes, the flow channels of the return channel Define in the circumferential direction to each other defi ⁇ ren, wherein the return stage downstream of the first Leit ⁇ blades second guide vanes defining
  • 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 compo- nents have the task of implementing the power supplied in the impeller kineti ⁇ specific energy into pressure.
  • the fluid In a multi-stage single-shaft, such as from the JP000244516 ⁇ be known, the fluid must also be to the subsequent impeller Gelei ⁇ tet. 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 section, which leads the process fluid radially outward, a second section which substantially corresponds to a 180 ° arc and a third section for directing the process fluid radially inward for entry into the downstream succeeding impeller.
  • a fourth section defines a redirection of the process fluid from the radially inward flow in the axial direction to the impeller inlet of the downstream impeller.
  • the invention has made it to the task crizzu ⁇ form a feedback stage of the type defined that a less expansive feedback stage generates a less lossy flow, which is particularly particularly low swirl and low vortex.
  • 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 invention proposes a radial turbofluid energy machine with such a return stage.
  • it is also customary to designate only the combination of the second section with the third section as a return stage and the first Ab ⁇ section as a flow direction in front of it Define diffuser.
  • the fourth section is not always attributed to the feedback stage.
  • the termino ⁇ logy of this document refers to the four successively arranged in the flow Rich ⁇ processing sections (Sl, S2, S3; S4; see figures) as a feedback stage.
  • the first portion in the invention can be ⁇ tet free decor with dark, so that the first section with or without blades, for example, is formed divergently, constant or excluded tapering in the flow direction may be Meriodinalimpose.
  • the invention enables a task sharing between the two rows of vanes, the first vanes and the second vanes, which is particularly efficient.
  • the first vanes essentially deflect the flow and the second vanes substantially break lent the vortices forming in the first vanes. This leads to a more homogeneous inflow to the next impeller and to a middle swirl-free inflow to the next impeller.
  • the arrangement of the first vanes and second vanes solely in the third portion of the return stage combines an aerodynamically advantageous Vorbe ⁇ reitung of the process fluid on the downstream Running wheel according to the 90 ° deflection. It turns out that the split into two flow guide vane stages particularly efficient working in the third section in the twist-free orientation of the Pro ⁇ zessfluids.
  • the arrangement of Leitbe ⁇ paddle especially in the third section is particularly easy to manufacture and easy to install.
  • the arrangement in the third section advantageously allows for a solid attachment of the false bottom to the blade bottom and is also particularly well suited due to the relatively simple geometry of the radial feedback in the region of the third section for mounting and manufacturing the two rows of vane.
  • the finding of the invention consists in particular in that an arrangement of guide vanes in adjacent regions reinforces the tendency for undesirable secondary flows due to the complexity of the further deflection of the process fluid.
  • the multiple division of tasks according to the invention Zvi ⁇ rule multiple radial deflection (180 °, 90 ° bends),
  • Swirl elimination (first vanes) and breakage of vortices forming in the first vanes (by means of the second vanes) is particularly aerodynamically efficient. Due to the fact that the second guide vanes are arranged exclusively in the third section of the return stage, any vortices are broken efficiently and hardly or no new vortices are generated. In this way, a largely swirl-free and eddy-free flow reaches the fourth section of the return stage and can be deflected at this point by other ae ⁇ rodynamischen measures uninfluenced in the axial direction for entry into the downstream impeller ⁇ umge ⁇ .
  • An advantageous development of the invention provides that an outlet edge diameter of the first guide vanes in relation to an inlet edge diameter of the first guide vanes between
  • L1EA Metal exit angle of the first Leitschau ⁇ blades (LI) to the radial direction.
  • the second guide vanes can be arranged in such a way that an inlet edge diameter of the second guide vanes in relation to an outlet edge diameter of the first guide vanes between
  • a blade overlap of guide vanes is in each case defined as a quotient of an average chord line length and an average arc length spacing in the circumferential direction of the mutually adjacent blades, wherein an overlap for the second guide vanes 0.8 ⁇ RAS / CDT ⁇ 1.2, with
  • CD sheet length distance
  • the return stage has the same number of first vanes and second vanes.
  • the second guide vanes are particularly efficient in accordance with an advantageous development of the invention as a vortex breaker, it is convenient when the second Leitschau ⁇ feln have a difference between a secondary metal and secondary metal entry angle exit angle, in which:
  • DL2A difference between mean metal entry angle and mean metal exit angle. Particularly preferred is the difference between the mean metal entry angle and mean metal exit angle zero. In addition, it is also advantageous if the first Leit ⁇ blades and / or second vanes are cylindrical.
  • Another advantageous development of the invention provides that exactly one second guide vane is arranged downstream in the circumferential direction between the two closest first guide vanes.
  • a 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 redirection and diversion of the process fluid downstream ⁇ Winderson of the outlet of an impeller toward the inlet 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 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 representation through the flow channel of a radial turbofluid energy machine using the example of a
  • FIG. 2 shows a detail of FIG. 1, which is indicated by II in FIG. 1,
  • FIG. 1 shows a schematic representation of a longitudinal section of a radial turbofan energy machine RTFEM in FIG.
  • Section of a flow channel for a process fluid PF The detail shows five IMP wheels that rotate as a component of egg ⁇ nes 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 the process fluid in each PF We ⁇ sentlichen axially and convey this accelerated radially outwardly. After exiting the impeller IMP, the process fluid PF enters a return stage BFS comprising a return channel BFC.
  • FIG. 2 shows the feedback stage BFS or the
  • the process fluid PF passes from the impeller IMP in a first section Sl of
  • the deflection from a radially inward flow direction FD in the third section S3 in the axial flow direction FD takes place essentially in a 90 ° arc, which represents a fourth section S4.
  • Only in the third section S3 are first vanes LI and second vanes L2 arranged.
  • the first Leitschau ⁇ blades have an entrance 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 second vane L2LE L2 is in a radial section RAD downstream ⁇ Wind lake 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 is also attributable to 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 LI.
  • a flow channel FC in the circumferential direction between two first vanes LI is respectively defined by a pressure side PSL1 of a first vane LI and a suction side SSL1 of another first vane LI.
  • a connecting line CLTE can always be indicated by two exit edges LITE of adjacent first guide vanes LI. This compound CLTE line extends with a radius of curvature which corresponds to the Abstandsra ⁇ dius to the axis X.
  • An arc length BLD of this connecting line CLTE between the two exit edges LITE of the adjacent first guide vanes LI is not divided centrally by a radial jet RS through the leading edge L2LE of the second guide vane arranged in the circumferential direction between the two first guide vanes LI.
  • a first part portion of this connecting line is CLTE Zvi ⁇ rule of the leading edge of the second vane L2LE L2 and the trailing edge of the first vane LITE LI, which adjoins the respective flow channel FC with its suction side SSB1 be ⁇ .
  • 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 entire Arc length BLD of the connecting line CLTE between the two exit edges LITE of the first vanes LI is between 0.4 - 0.6 (0, 4 ⁇ SSD / BLD ⁇ 0, 6).
  • This type of unequal distribution of the flow channel FC between the two first vanes LI by means of the following vane L2 leads to a particularly advantageous low-loss flow through the third section S3.
  • Figures 2 and 3 have different diameters for different positions of the return stage BFS.
  • the first section Sl extends up to a diameter DO.
  • the second section S2 extends in the flow direction up to a diameter D1. These two diameters are almost identical in the exemplary embodiment.
  • the leading edge L1LE of the first vanes LI is located on a diameter D2.
  • the exit edge LITE of the first vane LI is located on a diameter D3.
  • From the third ⁇ cut S3 extends from the diameter D to the diameter D6.
  • the entry edges L2LE of the second guide vanes L2 are each located on a diameter D4.
  • the exit edges L2TE of the second vanes L2 are each located on a diameter D5.
  • the according to the third section S3 subsequent fourth section S4 begins to be ⁇ a diameter D6.

Landscapes

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

Abstract

L'invention concerne un étage de retour (BFS) d'une turbomachine à énergie fluidique radiale (RTFEM), en particulier d'un turbocompresseur radial (RTC), destiné à dévier un sens d'écoulement (FD) d'un fluide de traitement (PF) sortant d'une roue à aubes (IMP) tournant autour d'un axe (X) ,radialement de l'extérieur vers l'intérieur dans le sens radial, ledit étage de retour comprenant un canal de retour (BFC) s'étendant de manière annulaire autour de l'axe (X), ledit canal de retour présentant quatre parties (S1, S2, S3, S4) adjacentes qui peuvent être parcourues par le fluide de traitement dans le sens d'écoulement, une première partie (S1) étant conçue pour guider le fluide de traitement (PF) radialement vers l'extérieur, une deuxième partie (S2) étant conçue pour dévier le fluide de traitement (PF) radialement de l'extérieur vers l'intérieur dans le sens radial, une troisième partie (S3) étant conçue pour guider le fluide de traitement (PF) radialement vers l'intérieur, une quatrième partie (S4) étant conçue pour dévier le fluide de traitement (PF) dans la direction axiale, la troisième partie (S3) présentant de premières aubes directrices (L1) qui définissent mutuellement des canaux d'écoulement (FC) du canal de retour (BFC) dans le sens d'écoulement, l'étage de retour (BFS) présentant de secondes aubes directrices (L2), en aval des premières aubes directrices (L1), qui définissent mutuellement des canaux d'écoulement (FC) du canal de retour (BFC) dans le sens d'écoulement. Selon l'invention, les premières aubes directrices (L1) sont disposées exclusivement dans la troisième partie (S3), les secondes aubes directrices (L2) étant disposées exclusivement dans la quatrième partie (S4).
EP18707245.9A 2017-03-15 2018-02-06 Étage de recirculation et turbomachine à énergie fluidique radiale Active EP3568597B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP17161002.5A EP3376041A1 (fr) 2017-03-15 2017-03-15 Étage de recirculation et turbomachine à énergie fluidique radiale
PCT/EP2018/052852 WO2018166716A1 (fr) 2017-03-15 2018-02-06 Étage de retour et turbomachine à énergie fluidique radiale

Publications (2)

Publication Number Publication Date
EP3568597A1 true EP3568597A1 (fr) 2019-11-20
EP3568597B1 EP3568597B1 (fr) 2020-09-16

Family

ID=58347182

Family Applications (2)

Application Number Title Priority Date Filing Date
EP17161002.5A Withdrawn EP3376041A1 (fr) 2017-03-15 2017-03-15 Étage de recirculation et turbomachine à énergie fluidique radiale
EP18707245.9A Active EP3568597B1 (fr) 2017-03-15 2018-02-06 Étage de recirculation et turbomachine à énergie fluidique radiale

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP17161002.5A Withdrawn EP3376041A1 (fr) 2017-03-15 2017-03-15 Étage de recirculation et turbomachine à énergie fluidique radiale

Country Status (4)

Country Link
US (1) US10989202B2 (fr)
EP (2) EP3376041A1 (fr)
CN (1) CN110418896B (fr)
WO (1) WO2018166716A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2018173020A (ja) * 2017-03-31 2018-11-08 三菱重工業株式会社 遠心圧縮機
EP3798453A1 (fr) 2019-09-26 2021-03-31 Siemens Aktiengesellschaft Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication
US20230375005A1 (en) * 2020-09-23 2023-11-23 Hitachi Industrial Products, Ltd. Centrifugal compressor

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE723824C (de) 1935-05-27 1942-08-11 Escher Wyss Maschf Ag Mehrstufiger Fliehkraftverdichter bzw. mehrstufige Fliehkraftpumpe
US2300766A (en) * 1940-05-10 1942-11-03 Bbc Brown Boveri & Cie Multistage centrifugal compressor
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
JP2001200797A (ja) * 2000-01-17 2001-07-27 Hitachi Ltd 多段遠心圧縮機
CA2324533A1 (fr) * 2000-10-27 2002-04-27 Carl Hunter Enrichissement en oxygene dans des moteurs diesels
JP4951583B2 (ja) * 2008-04-28 2012-06-13 日立アプライアンス株式会社 ターボ冷凍機
JP2010185361A (ja) * 2009-02-12 2010-08-26 Mitsubishi Heavy Ind Ltd 遠心圧縮機
RU2013111982A (ru) * 2010-09-02 2014-10-10 Боргварнер Инк. Компрессорная рециркуляция в кольцевой объем
CN102678590B (zh) 2011-03-07 2015-08-12 中国科学院工程热物理研究所 超紧凑高压比斜流-离心组合压气机结构
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
DE102014226195A1 (de) * 2014-12-17 2016-06-23 Siemens Aktiengesellschaft Radialturbofluidenergiemaschine
DE102016203305A1 (de) * 2016-03-01 2017-09-07 Siemens Aktiengesellschaft Rückführstufe, Radialturbofluidenergiemaschine

Also Published As

Publication number Publication date
CN110418896B (zh) 2020-10-30
CN110418896A (zh) 2019-11-05
EP3376041A1 (fr) 2018-09-19
US20200025205A1 (en) 2020-01-23
EP3568597B1 (fr) 2020-09-16
WO2018166716A1 (fr) 2018-09-20
US10989202B2 (en) 2021-04-27

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