EP3194792B1 - Étage de retour - Google Patents

Étage de retour Download PDF

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Publication number
EP3194792B1
EP3194792B1 EP15797326.4A EP15797326A EP3194792B1 EP 3194792 B1 EP3194792 B1 EP 3194792B1 EP 15797326 A EP15797326 A EP 15797326A EP 3194792 B1 EP3194792 B1 EP 3194792B1
Authority
EP
European Patent Office
Prior art keywords
radial
recirculation stage
flow direction
turn
fcss
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.)
Not-in-force
Application number
EP15797326.4A
Other languages
German (de)
English (en)
Other versions
EP3194792A1 (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 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 EP3194792A1 publication Critical patent/EP3194792A1/fr
Application granted granted Critical
Publication of EP3194792B1 publication Critical patent/EP3194792B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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

  • the invention relates to a recycling stage according to claim 1.
  • the fluid leaves the impeller radially outward and from there into the diffuser, which is also flowed through radially outward.
  • the process fluid in the portion of the radial deflection, the so-called 180 ° arc is deflected from radially outward to radially inward flow.
  • the flow path downstream of the 180 ° arc is bladed to convert the swirl of the fluid, which is part of the kinetic energy stored by the fluid, into static pressure - comparable to converting kinetic energy into potential energy.
  • the vanes provided in the return duct are also referred to as return vanes. Downstream of the return vanes, the process fluid is usually deflected from a radially inwardly directed flow in an axial direction, so that an axially parallel inflow into the downstream compression stage can take place.
  • 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 90 ° deflection provided downstream of the return channel in the direction parallel to the axis for feeding the subsequent stage has no special design according to the invention and will accordingly not be described in detail.
  • a comparable multi-stage radial turbomachine namely a radial turbine is already out of the EP 2 518 280 A1 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 state of the art in this document provides that the radial deflection on the inlet side and outlet side each have 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 to a high pressure loss.
  • 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 turbocompressor in general.
  • this direction of flow can be characterized by the middle channel course with the marking of corresponding directional arrows.
  • the sections annular space, radial deflection, return channel and axial deflection of the return stage are each formed annularly extending around a rotational axis of the radial turbocompressor.
  • a center line between the outer contour and the inner contour is defined as the location of the centers of the circles tangent to the two contours. Since the return stage extends in the circumferential direction about the axis of rotation of the radial turbocompressor and thus defines an annular space which is substantially rotationally symmetrical to the axis of rotation, a central area between the three-dimensional inner contour and the three-dimensional outer contour can be regarded as a rotation surface of the center line about the axis of rotation.
  • the description of the geometry is always based on a meridional section through the radial turbocompressor, wherein the meridional section extends along the axis of rotation and represents the flow channel defined by the return stage in a section along an axially and radially extending plane.
  • Such cuts along the axis of rotation are also referred to as longitudinal cuts.
  • the terminology of the invention always refers to radial and axial components of the flow velocity.
  • the inventive combination of a decreasing radius of curvature with simultaneous expansion of the cross-sectional area perpendicular to the flow direction along the flow direction leads to a homogenization of the load on the flow over the course of the radial deflection as a result of deceleration and deflection, so that the tendency to a separation of the flow from the inner contour or Outer contour harmonized in a design according to the invention of the radial deflection and 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 due to cross-sectional expansion takes place. It is also possible that there is no delay in this section.
  • the average flow direction means an average flow-weighted average flow velocity of the process fluid, perpendicular to the center line between the inner contour and the outer contour of the radial deflection along the cross-sectional width. Since the invention always considers the meridional section, the circumferential component is omitted in the context of a projection of the spatially oriented velocity, so that the average flow velocity can be described exclusively in the projection as the addition of an axial velocity and a radial velocity.
  • the projected mean flow direction - short flow direction - is to be understood as a magnitude normalized vector of the projected average flow velocity.
  • the cross-sectional area of the radial deflection has a direct influence on the flow velocity, so that as a result of the cross-sectional area widening in the direction of flow, the flow is retarded.
  • the invention according to the decreasing radius of curvature with progressing flow along the flow direction in the radial deflection is synonymous with an increasing curvature of the deflection.
  • the area increase of the cross-sectional area in the flow direction is preferably formed continuously. Furthermore, a steadily formed decrease of the radius of curvature in the flow direction is particularly preferred. Particularly preferred is a degressive area increase of the cross-sectional area in the flow direction. Excellent results are achieved with a degressive steady surface increase of the cross-sectional area in the flow direction, which has steadily decreased to 0 at the end of the radial deflection.
  • 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 increase in curvature of the inner contour of the radial deflection in the flow direction and / or a steadily progressive increase in curvature of 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 duct begins, which directs the process fluid substantially straight radially inward.
  • radially inward in the context 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 FCSS> 1, 5
  • FCSS> 2.0 FCSS> 2.0
  • FCSS is greater than 1.4 (FCSS> 1.4), preferably greater than 1.5 (FCSS> 1.5) and is 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 takes place at a first axial plane, wherein the first axial plane between 7/12 to 11/12, preferably occupies 2/3 ⁇ 1/6 of the total axial extent of the center line in the radial deflection. It is postulated that the flow direction follows without deviation of the center line.
  • An advantageous development of the invention provides that in the meridional section the axial extension of the deflection of the center line is directed from radially outward to the axial direction of the center line at a first axial plane, wherein the first axial plane between 7 / 12 to 11/12, preferably occupying between 2/3 ⁇ 1/6 of the total axial extent of the center line in the radial deflection.
  • 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.
  • a radial turbocompressor RTC is shown schematically in meridional section or longitudinal section.
  • the meridional section extends along a rotation axis X of a shaft SH of a rotor R of the radial turbocompressor 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. Accordingly, an extension in the circumferential direction of the rotation axis X is not reproduced, as well as in FIG. 2 that one with II in FIG. 1 represents reproduced detail.
  • a process fluid PF enters an impeller IMP or an impeller of the rotor R in a flow direction FD.
  • the process fluid PF is accelerated in the radial direction by means of the impeller IMP and introduced into the return stage RS.
  • the return stage RS is part of a stator ST, which is composed essentially of the components bucket bottom BD and intermediate bottom ID.
  • the blade bottom BD is here attached by means of return duct guide vanes GVRC to the intermediate bottom ID.
  • several combinations of shelves ID and blade bottoms BD of the stator ST line up axially.
  • the blade floors BD and the shelves ID are formed divided in the circumferential direction, so that an assembly of the rotor R with the stator ST by division of the stator ST in a generally horizontal parting line is possible.
  • the return stage RS comprises in the flow direction FD of the process fluid PF listed multiple sections SE, which form a flow channel from an impeller IMP to a downstream impeller IMP.
  • These sections SE are: a) an annular space RR, b) a radial deflection RT and c) a return channel RC.
  • To the sections may also be added to a less important for the invention section SE, namely a downstream axial deflection AT for axial entry into the downstream impeller.
  • the annular space RR can be formed bladed with annulus guide vanes GVRR or without blades, that is, unencumbered.
  • the radial deflection RT which is defined by an inner contour IC and an outer contour OC of the stator ST.
  • the radial deflection RT deflects the flow essentially from a radially outward-pointing direction into a radially inward-pointing direction, ie approximately 180 °. Because of the 180 ° deflection, the radial deflection is also often referred to as 180 ° deflection or 180 ° bend (equivalent: 180 ° turn, u-turn). From the eponymous 180 ° deflection, the actual deflection may differ for various, especially aerodynamic reasons.
  • FIG. 2 schematically shows a detail that in the FIG. 1 is indicated with "II" and the radial deflection RT reflects.
  • the radial deflection RT is also annular in the circumferential direction and extends around the rotation axis X.
  • the representations in the meridional section do not show the extent in the circumferential direction.
  • a process fluid PF flows into the radial deflection RT and is directed substantially radially outward, wherein the outflow from the radial deflection RT takes place radially inward.
  • the deflection takes place along a flow direction FD, wherein in the FIG. 2 only the projected mean flow direction PMFD is reproduced, which is identical in the schematic representation with the flow direction FD.
  • the actual flow has a significant share in the circumferential direction, so that the FIG. 2 shows only the projected mean flow direction PMFD omitting the reproduction of the circumferentially oriented component.
  • the inner contour IC and the outer contour OC define the flow channel of the radial deflection RT. Between the inner contour IC and the outer contour OC, a center line ML can be inscribed which is substantially congruent with the flow velocity FD or the mean projected flow direction PMFD. Perpendicular to the center line, the channel width B is plotted as a function of a coordinate s running along the center line ML in the flow direction FD.
  • a cross-sectional area CSS is congruent with the channel width in the projection of the meridional section B (s) and on the one hand function of the channel width B (s) and on the other hand depending on the diameter of the position of the respective channel width.
  • the center line ML runs along the radial deflection RT with a respective radius of curvature RBML (s) dependent on the coordinate s. Also dependent on the coordinate s is the radius of curvature of the inner contour RBIC (s) and the radius of curvature of the outer contour RBOC (s).
  • the meridional width of the cross-sectional area CSS widens with increasing flow direction FD from an inlet to an outlet of the radial deflection RT. In the beginning, the increase in area is stronger than the initial one - that is, decreasing. At the outset of the radial deflection, the cross-sectional area may also be decreasing-in particular due to the decrease in diameter when traveling radially inwards-so that slight accelerations may occur.
  • the radius of curvature of the center line ML is designed to be decreasing in the flow direction FD, as is 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.
  • the new design increases the maximum possible deceleration and thus reduces the losses in the deflection and the subsequent components due to a lower speed level.
  • the radial deflection RT according to the invention first brakes the flow and then redirects it.
  • the area increase of the cross-sectional area CSS is continuous over the course of the radial deflection RT.
  • the decrease in the radius of curvature in the flow direction FD of the center line ML, the outer contour OC and the inner contour IC are also constantly designed.
  • the area increase of the cross-sectional area CSS in the flow direction FD is preferably degressive continuous for the cross-sectional area CSS.
  • the decrease in the radius of curvature in the flow direction FD is progressively continuous for the radius of curvature of the center line RBML (s).
  • the increase in area is decreasing in the direction of the course coordinate s or the flow direction FD, the decrease in the radius of curvature in this direction is increasingly formed.
  • the axial extension of the deflection from radially outward of the center line ML to the axial direction to about 2/3 of the total axial extent of the radial deflection RT is carried out.
  • the remaining approximately 90 ° deflection from the axial direction into the radially inward flow direction FD take place on the last third of the entire axial extension of the radial deflection RT, wherein the axial extent as the distance of the center line ML between the entrance of the radial deflection RT and the outlet of the radial deflection RT is understood.
  • this first axial plane AXP1 in which the flow has been deflected from radially outward directed in the axial direction, positioned at an axial position between 7/12 to 11/12 the entire axial extent of the center line ML of the radial deflection RT.
  • the first axial plane AXP1 is between half of the total axial extent and 5/6 of the total axial extent. In the position the first axial plane AXP1 is already at least 65% of the total area expansion of the radial deflection RT in the flow direction FD reached.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Claims (14)

  1. Etage (RF) de retour d'un turbocompresseur (RTC) radial, comprenant les parties (SE) suivantes dans le sens (FD) d'écoulement d'un fluide (PF) de processus :
    a) un espace (RR) annulaire,
    b) un coude (RT) radial,
    c) un conduit (RC) de retour,
    dans lequel le coude (RT) radial est formé d'un contour (OC) extérieur et d'un contour (IC) intérieur,
    dans lequel, pour chaque coupe méridienne, une ligne (ML) médiane est définie entre le contour (OC) extérieur et le contour (IC) intérieur, comme le lieu des centres des cercles tangents aux deux contours,
    caractérisé en ce que
    le coude (RT) radial a, dans la coupe méridienne, sur au moins les premiers 150° du coude, un élargissement de la largeur méridienne, parcourue et s'étendant perpendiculairement à la ligne (ML) médiane, de la surface (CSS) de section transversale dans le sens (FD) d'écoulement, la ligne (ML) médiane ayant, dans le coude (RT) radial, un rayon (BRML) de courbure diminuant dans le sens (FD) d'écoulement.
  2. Etage (RS) de retour suivant la revendication 1,
    dans lequel une augmentation de la surface (CSS) transversale, en raison de l'augmentation de la largeur méridienne, est formée de manière continue dans le sens d'écoulement.
  3. Etage (RS) de retour suivant la revendication 1,
    dans lequel, dans la coupe méridienne, l'étage (RS) de retour a, dans le coude (RT) radial, sur au moins les premiers 180° du coude, un élargissement de la largeur méridienne, parcourue et s'étendant perpendiculairement à la ligne (ML) médiane, de la surface (CSS) de section transversale dans le sens (FD) d'écoulement.
  4. Etage (RS) de retour suivant la revendication 1, 2 ou 3, dans lequel un rayon de courbure de la ligne (ML) médiane du contour (OC) extérieur ou du contour (IC) intérieur est décroissant d'une manière continue dans le sens (FD) d'écoulement.
  5. Etage (RS) de retour suivant l'une des revendications précédentes 1 à 4,
    dans lequel l'accroissement de la surface (CSS) de section transversale, dans le sens (FD) d'écoulement, est dégressif d'une manière continue.
  6. Etage (RS) de retour suivant la revendication 4,
    dans lequel le rayon de courbure diminue progressivement.
  7. Etage (RS) de retour suivant l'une des revendications précédentes 1 à 6,
    dans lequel l'espace (RR) annulaire est sans aube et un rapport (FCSS) de la surface (CSS) de section transversale entre une entrée du coude (RT) radial et une sortie du coude (RT) radial est différent au moins d'un facteur (FCSS) de 1,5.
  8. Etage (RS) de retour suivant la revendication 7,
    dans lequel le facteur (FCSS) est d'au moins 2,0.
  9. Etage (RS) de retour suivant la revendication 8,
    dans lequel le facteur (FCSS) est compris entre 2,3 et 3,3.
  10. Etage (RS) de retour suivant l'une des revendications précédentes 1 à 6,
    dans lequel l'espace (RR) annulaire est constitué sans aube et le rapport de la surface (CSS) transversale entre une entrée du coude (RT) radial et une sortie du coude (RT) radial diffère d'un facteur (FCSS) d'au moins 1,4.
  11. Etage (RS) de retour suivant la revendication 10,
    dans lequel le facteur (FCSS) est d'au moins 1,5.
  12. Etage (RS) de retour suivant la revendication 11,
    dans lequel le facteur (FCSS) est plus petit que 2,5.
  13. Etage (RS) suivant au moins l'une des revendications précédentes,
    dans lequel, dans la coupe méridienne, l'étendue axiale du coude, de radialement vers l'extérieur de la ligne (ML) médiane jusque dans la direction axiale, s'étend jusqu'à un premier plan (AXP1) axial, qui s'étend de préférence entre 7/12 à 11/12, de préférence entre 2/3 - 1/6 à 2/3 + 1/6 de l'étendue axiale totale de la ligne (ML) médiane du coude (RT) radial.
  14. Etage (RS) suivant la revendication 13
    dans lequel, sur le premier plan (AXP1) axial, au moins 65% de tout l'élargissement de surface du coude (RT) radial sont atteints.
EP15797326.4A 2014-11-21 2015-11-19 Étage de retour Not-in-force EP3194792B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014223833.1A DE102014223833A1 (de) 2014-11-21 2014-11-21 Rückführstufe
PCT/EP2015/077052 WO2016079222A1 (fr) 2014-11-21 2015-11-19 Étage de retour

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EP3194792A1 EP3194792A1 (fr) 2017-07-26
EP3194792B1 true EP3194792B1 (fr) 2018-09-26

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Application Number Title Priority Date Filing Date
EP15797326.4A Not-in-force EP3194792B1 (fr) 2014-11-21 2015-11-19 Étage de retour

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

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3364039A1 (fr) * 2017-02-21 2018-08-22 Siemens Aktiengesellschaft Étage de retour
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

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Publication number Priority date Publication date Assignee Title
WO1997033092A1 (fr) * 1996-03-06 1997-09-12 Hitachi, Ltd. Compresseur centrifuge et diffuseur pour ce compresseur centrifuge
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
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
JP2011132877A (ja) 2009-12-24 2011-07-07 Mitsubishi Heavy Ind Ltd 多段ラジアルタービン
WO2014115417A1 (fr) * 2013-01-28 2014-07-31 三菱重工業株式会社 Machine à rotation centrifuge

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Publication number Publication date
DE102014223833A1 (de) 2016-05-25
EP3194792A1 (fr) 2017-07-26
WO2016079222A1 (fr) 2016-05-26

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