WO2016079222A1 - Étage de retour - Google Patents

Étage de retour Download PDF

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Publication number
WO2016079222A1
WO2016079222A1 PCT/EP2015/077052 EP2015077052W WO2016079222A1 WO 2016079222 A1 WO2016079222 A1 WO 2016079222A1 EP 2015077052 W EP2015077052 W EP 2015077052W WO 2016079222 A1 WO2016079222 A1 WO 2016079222A1
Authority
WO
WIPO (PCT)
Prior art keywords
deflection
radial
radial deflection
feedback stage
flow direction
Prior art date
Application number
PCT/EP2015/077052
Other languages
German (de)
English (en)
Inventor
Nico Petry
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP15797326.4A priority Critical patent/EP3194792B1/fr
Publication of WO2016079222A1 publication Critical patent/WO2016079222A1/fr

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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • said portions are each formed annularly around a rotational property ⁇ se of the radial extending turbocompressor, wherein the radial deflection is formed by an outer contour and an inner contour.
  • the fluid leaves the impeller ⁇ ra dial outwards and passes from there into the diffuser, which is also flows radially outwardly.
  • the process fluid is in the portion of the radial deflection, the so-called 180 degree arc from the radially outwardly flowing deflected into a flow radially Inside.
  • the flow path downstream of the 180 ° arc is bladed to prevent the swirl of the
  • vanes provided in the return duct are also referred to as return vanes. Downstream of
  • the process fluid is usually deflected from ei ⁇ ner radially inwardly directed flow in an axial direction, so that an axis-parallel inflow into the downstream compression stage can be done.
  • the actual baffles affecting the process fluid in the 180 ° arc and in the downstream 90 ° deflection can deviate from the names giving values 180 ° and 90 °.
  • the 180 ° deflection is therefore usually referred to in the terminology of the invention as a radial deflection.
  • the downstream ⁇ Wind concept of the return duct provided for the 90 ° deflection in achspa- rallele direction for supplying the subsequent stage has according to the invention, no special configuration and is accordingly not described in detail.
  • a similar multi-stage centrifugal turbomachine namely, a radial turbine is already known from EP 2518280 Al ⁇ be known. Even if the flow direction in a radial turbine runs counter to that in a radial compressor, it has hitherto been customary to form the respective return stage geometrically at least approximately the same.
  • the prior art provides that the radial deflection per ⁇ wells having inlet side and outlet side, a substantially identical axial width. Furthermore, it is provided that the radial deflection has a substantially constant radius both on an inner contour and on an outer contour.
  • This design of the radial deflection corresponds to the simplest geometric design and tends as a result of separation phenomena at the Umlenkungsradien in operation with a high pressure drop. Based on the disadvantages of the prior art, it has the object of the invention to further develop the radial deflection of the return stage of a radial turbocompressor of the type defined in such a way that avoidable
  • the invention Under a direction of flow, the invention relates to a movement of a process fluid relative to the entire return stage through the flow channel defined by means of the return stage of the radial turbo ⁇ compressor in general.
  • this flow direction can tung arrows mark by the middle channel course under appropriate delineation RICH.
  • the sections annulus, radial deflection, Rü + ck Crystalkanal and axial deflection of the return stage are each formed annularly extending around a rotational axis of the radial turbocompressor.
  • Return stage is a center line between the outer contour and the inner contour defined as the location of the centers of the circles contiguous by the two contours. Since the return step in the circumferential direction extending about the rotation axis of the centrifugal turbocompressor and thus an annular space de ⁇ finiert which is rotationally symmetrical to the axis of rotation substantially a center area between the three-dimensional inner contour and the three-dimensional outer contour as a surface of revolution of the center line around the rotation axis can at ⁇ be seen.
  • the description of the geometry is always related to a meridional section through the radial turbo compressor, wherein the meridional section extending along the axis of rotation and represents the de ⁇ -defined by the feedback stage flow channel in a section along an axially and radially extending plane.
  • Such sections along the axis of rotation are also be ⁇ as longitudinal sections.
  • the inventive combination of a decreasing curve ⁇ radius with simultaneous widening of the cross-sectional area perpendicular to the flow direction along the flow direction leads to an equalization of the load of the flow over the course of the radial deflection as a result of deceleration and deflection, so that the tendency to separation of the flow from the Inner contour or outer contour harmonized in an inventive design of the radial deflection and is reduced in the top.
  • the flow in the course of the radial deflection as far as it is possible under the specification of the deflection braked without undue increase the tendency to detachment before the flow is deflected with a correspondingly delayed speed, in this section of the radial deflection only one less delay by QueritessaufWei ⁇ tion takes place.
  • this From ⁇ cut no delay is provided.
  • the average Strö ⁇ flow direction means a perpendicular to the center line between the inner contour and the outer contour of the radial deflection along the cross-sectional width - volumetric flow weighted average flow rate of the process fluid.
  • the cross-sectional area of the radial deflection has accordingly spre ⁇ accordingly a direct impact on the Strömungsgeschwindig ⁇ ness, so as a result of the widening in the direction of flow cross-sectional area results in a delay of Strö ⁇ tion.
  • decreasing radius of curvature continuously ⁇ border flow along the flow direction in the radial deflection is equivalent to an increasing curvature of the deflection.
  • Preferably in the range of the radial deflection of the ceremoninzu ⁇ acquisition of the cross-sectional area in the flow direction is continuously formed from ⁇ .
  • Particularly preferred is a degressive area increase of the cross-sectional area in the flow direction.
  • a further advantageous development provides that the radius of curvature is formed progressively decreasing in the flow direction and steadily decreases to a minimum at the end of the radial deflection, so that there is given a maximum curvature of a center line between the inner contour and the outer contour.
  • a particularly low-release design of the radial deflection can be achieved by a steadily progressive curvature ⁇ increase the inner contour of the radial deflection in the flow direction and / or a steadily progressive curvature zunähme the outer contour in the flow direction.
  • One end of the section of the radial deflection is defined in the sense of the invention by an end of the outer contour and inner contour guided deflection of the flow radially inward, wherein a further deflection in the same direction, in which the total fluid is deflected more than 180 °, for example, to reduce the axial distance between 2 stages, also the radial deflection is attributable ,
  • the radial deflection is accordingly designed to be limited in the flow direction when the center line no longer has a curvature in the deflection direction of the radial deflection. At this point, the return channel begins, which conducts the process fluid essentially straight radially inward.
  • radially inward in the sense of the invention is not necessarily meant perpendicular to the axis of rotation, but simply the inversion of the flow from radially outward to radially inward, the resulting Strömungsrichtrung may differ after the deflection of the strictly radial direction.
  • FCSS> 1.5 Cross sectional area by the factor FCSS> 1.5 (FCSS> 1.5).
  • FCSS factor is at least 2.0 (FCSS> 2.0).
  • FCSS is between 2.3 - 3.3 (2, 3 ⁇ FCSS ⁇ 3, 3).
  • FCSS is greater than 1.4 (FCSS> 1.4), preferably greater than 1.5 (FCSS> 1.5), and more preferably between 1.5 - 2,5 (1, 5 ⁇ FCSS ⁇ 2, 5).
  • An advantageous development of the invention provides that in the meridional section, the axial extent of the deflection directed from radially outward to the axial direction of the Flow of the process fluid at a first axial plane he follows ⁇ , with the 1 ° e ⁇ preferably between g takes the center line in the radial deflection.
  • An advantageous development of the invention provides that in the meridional section, the axial extent of the deflection of the center line from radially outward to the axial ⁇ direction of the center line at a first axial plane, which preferably between the middle
  • a further advantageous development provides that at least 65% of the total area widening of the cross-sectional area of the radial deflection is achieved at the axial position of the first axial plane.
  • FIG. 1 shows a meridional section through a stage of a Ra ⁇ dialturbover Actuallyrs with a return stage according to the invention in a schematic representation
  • Figure 2 shows a detail of Figure 1, which is designated there by II.
  • the feedback stage RS of a radial turbo ⁇ compressor RTC shown in Figure 1 is shown schematically in the meridional section or longitudinal section.
  • the meridional section extends along an axis of rotation X of a shaft SH of a rotor R of the radial turbocharger ⁇ RTC. Furthermore, the meridional section is defined through the radial direction so that the axis of rotation X and the radial direction span the plane of the cut. Dement ⁇ speaking, an extension in the circumferential direction of the axis of rotation X is not reproduced, as well as in Figure 2, which represents a reproduced with II in Figure 1 detail.
  • Stators ST which is essentially composed of the components bucket bottom BD and intermediate bottom ID.
  • the bucket bottom BD is hereby means
  • a center line ML can draw, which coincide substantially with the flow rate FD and the mean flow direction proji ⁇ ed pmfd.
  • Perpendicular to the center line of the channel width as a function of B is extending along the center ⁇ lline ML in the flow direction FD coordinate plotted s.
  • a cross-CSS is congruent in the projek ⁇ tion of Meridional bains with Kanalbrei- te B (s) and on the one hand function of the channel width B (s) and on the other hand depends on the diameter of the position of the respective channel width.
  • the increase in area is here a ⁇ gangs stronger than exit of - so designed decreasing.
  • the cross-sectional area may also be decreasing-in particular due to the decrease in diameter when traveling radially inward-so that slight accelerations may occur.
  • the radius of curvature of the center line ML is in the flow direction FD, as well as the radius of curvature RBIC (s) of the inner contour IC, as well as the radius of curvature RBOC (S) of the outer contour OC, decreasing decor with dark ⁇ tet.
  • the new design increases the maximum possible deceleration and thus redu ⁇ ed due to a lower speed levels, the losses in the deflection and subsequent components.
  • the radial deflection RT first brakes the flow and then redirects it. In this case, however, deflection and deceleration already take place upon entry into the radial deflection RT.
  • the focus of this shift the flow directing measures ⁇ is taking place from the catchy main delay towards more towards the exit koruptsumblelichen deflection.
  • the area increase of the cross-sectional area CSS is over the

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

Abstract

L'invention concerne un étage de retour (RF) d'un turbocompresseur radial (RTC) dans la direction d'écoulement (FD) d'un fluide de traitement (PF) comprenant en détail les sections (SE) suivantes : a) un espace annulaire (RR), b) une déviation radiale (RT), c) un canal de retour (RC), les sections (SE) s'étendant respectivement de manière annulaire autour d'un axe de rotation (X) du turbocompresseur radial (RTC), la déviation radiale (RT) étant formée par un contour extérieur (OC) et par un contour intérieur (IC). Pour chaque coupe méridionale, une ligne médiane (ML) est définie entre le contour extérieur (OC) et le contour intérieur (IC) comme l'emplacement des centres des cercles touchés par les deux contours. L'invention vise à réduire au minimum les pertes d'écoulement. À cet effet, dans la coupe méridionale, l'étage de retour (RS) présente dans la déviation radiale (RT) sur au moins les premiers 150° de la déviation une augmentation de la largeur méridionale traversée, s'étendant perpendiculairement à la ligne médiane (ML), de la surface de section (CSS) dans le sens d'écoulement (FD), la ligne médiane (ML) présentant un rayon de courbure (BRML) diminuant dans le sens d'écoulement (FD).
PCT/EP2015/077052 2014-11-21 2015-11-19 Étage de retour WO2016079222A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15797326.4A EP3194792B1 (fr) 2014-11-21 2015-11-19 Étage de retour

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014223833.1 2014-11-21
DE102014223833.1A DE102014223833A1 (de) 2014-11-21 2014-11-21 Rückführstufe

Publications (1)

Publication Number Publication Date
WO2016079222A1 true WO2016079222A1 (fr) 2016-05-26

Family

ID=54601787

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2015/077052 WO2016079222A1 (fr) 2014-11-21 2015-11-19 Étage de retour

Country Status (3)

Country Link
EP (1) EP3194792B1 (fr)
DE (1) DE102014223833A1 (fr)
WO (1) WO2016079222A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110325743A (zh) * 2017-02-21 2019-10-11 西门子股份公司 返回级
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

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010216456A (ja) * 2009-03-19 2010-09-30 Hitachi Plant Technologies Ltd 多段遠心圧縮機及び多段遠心圧縮機の改造方法
WO2014115417A1 (fr) * 2013-01-28 2014-07-31 三菱重工業株式会社 Machine à rotation centrifuge

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3488718B2 (ja) * 1996-03-06 2004-01-19 株式会社日立インダストリイズ 遠心圧縮機および遠心圧縮機用ディフューザ
JP3569087B2 (ja) * 1996-11-05 2004-09-22 株式会社日立製作所 多段遠心圧縮機
JPH11173299A (ja) * 1997-12-05 1999-06-29 Mitsubishi Heavy Ind Ltd 遠心圧縮機
JP2003083281A (ja) * 2001-09-06 2003-03-19 Mitsubishi Heavy Ind Ltd 多段遠心圧縮機の改造方法
JP2011132877A (ja) 2009-12-24 2011-07-07 Mitsubishi Heavy Ind Ltd 多段ラジアルタービン

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010216456A (ja) * 2009-03-19 2010-09-30 Hitachi Plant Technologies Ltd 多段遠心圧縮機及び多段遠心圧縮機の改造方法
WO2014115417A1 (fr) * 2013-01-28 2014-07-31 三菱重工業株式会社 Machine à rotation centrifuge

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110325743A (zh) * 2017-02-21 2019-10-11 西门子股份公司 返回级
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

Also Published As

Publication number Publication date
EP3194792B1 (fr) 2018-09-26
EP3194792A1 (fr) 2017-07-26
DE102014223833A1 (de) 2016-05-25

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