EP2993357B1 - Étage de compresseur radial - Google Patents

Étage de compresseur radial Download PDF

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Publication number
EP2993357B1
EP2993357B1 EP15179255.3A EP15179255A EP2993357B1 EP 2993357 B1 EP2993357 B1 EP 2993357B1 EP 15179255 A EP15179255 A EP 15179255A EP 2993357 B1 EP2993357 B1 EP 2993357B1
Authority
EP
European Patent Office
Prior art keywords
stator
flow
diffuser
impeller
side guide
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.)
Active
Application number
EP15179255.3A
Other languages
German (de)
English (en)
Other versions
EP2993357A3 (fr
EP2993357A2 (fr
Inventor
Thomas Mokulys
Philipp Jenny
Christof Seebass-Linggi
Yves Bidaut
Samuel Schneider
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.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2993357A2 publication Critical patent/EP2993357A2/fr
Publication of EP2993357A3 publication Critical patent/EP2993357A3/fr
Application granted granted Critical
Publication of EP2993357B1 publication Critical patent/EP2993357B1/fr
Active 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
    • 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
    • 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
    • F04D29/44—Fluid-guiding means, e.g. 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
    • 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
    • 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
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations

Definitions

  • the invention relates to a radial compressor stage for a radial compressor according to the Oberbergriff of claim 1.
  • each radial compressor stage of a radial compressor comprises an impeller rotating with respect to a stator, the impeller comprising a hub and a plurality of rotor-side impeller blades.
  • Each impeller vane of the impeller has a flow entrance edge and a flow exit edge, wherein a suction side, a pressure side, and an outer surface facing the stator extend between the flow entrance edge and the flow exit edge of each impeller vane, the outer surface of the respective impeller vane adjacent to the stator and sealing against the stator vane Stator is used.
  • Such an impeller of a centrifugal compressor in which the outer surfaces of the impeller blades indirectly adjacent to the stator, has no shroud and is also referred to as an open impeller.
  • the impeller blades are positioned in an impeller flow passage delimited by the hub of the impeller and the stator.
  • the centrifugal compressor stage includes a diffuser positioned downstream of the impeller having a plurality of stator vanes.
  • Each vane of the diffuser has a flow inlet edge and a flow outlet edge, extending between the flow inlet edge and the flow outlet edge of each vane a suction side and a pressure side extends.
  • the vanes are positioned in a diffuser flow channel defined by the stator. From the DE 195 02 802 C2 can be seen that between the impeller and the stator of the radial compressor stage shown there is formed a so-called Radreteraum, namely between a rear side of the impeller and the stator. This wheel side space is connected to an intermediate flow passage extending between the impeller flow passage and the diffuser flow passage.
  • Another radial compressor stage with such a Radierraum is from the DE 10 2007 019 264 A1 known.
  • From the EP 2 014 925 A1 is a radial compressor stage with a diffuser known, in which the angular distance of flow inlet edges of two adjacently arranged guide elements is different from the angular distance of flow inlet edges of two other adjacently arranged guide elements.
  • the JP 2004 100 553 A discloses an arrangement of stator vanes which are rotatable about an axis of rotation.
  • the DE 41 26 907 A1 discloses a diffuser having first stationary stator vanes and second variable stator vanes. Also, the document discloses a bladed diffuser having circumferentially different flow cross sections.
  • the WO 2009/012990 A1 discloses a vaneless diffuser having a radially varying flow area.
  • the centrifugal compressor stages are exposed to mechanical stimuli and vibrations which can cause damage to the radial compressor stage, in particular to the rotor blades of the impeller of the radial compressor stage.
  • mechanical excitations can be based on synchronous excitation mechanisms as well as on asynchronous excitation mechanisms.
  • the present invention has the object to provide a radial compressor stage for a centrifugal compressor, which the above Satisfies requirements and therefore a low vibration excitation is exposed in particular by such asynchronous excitations.
  • a radial compressor stage according to claim 1.
  • the flow inlet edges of the stator vanes of the diffuser lie on a first circular contour, namely such that the flow inlet edges of all the stator vanes have an identical distance to the flow inlet edges of the respective adjacent vanes.
  • the flow outlet edges of the stator-side guide vanes of the diffuser lie on a second circular contour, namely such that at at least one first circumferential position the flow exit edge of the respective stator side vane has a different distance from the flow exit edge of at least one adjacent vane than at second circumferential positions.
  • a diffuser flow channel section formed between adjacent stator-side guide vanes has a flow cross-section deviating from the diffuser flow channel sections formed at fourth circumferential positions.
  • the present invention relates to a centrifugal compressor with at least one radial compressor stage.
  • Fig. 1 shows a detail of a radial compressor stage according to the invention in the meridional section, wherein Fig. 2 an axial section through the radial compressor stage of Fig. 1 shows.
  • the radial compressor stage of Fig. 1 has an impeller 10 with a plurality of rotor-side impeller blades 11.
  • the impeller 10 rotates with respect to a stator 12.
  • the stator 12 may be a housing or a stator ring or the like.
  • the impeller blades 11 are positioned in an impeller flow channel 13 which is delimited by a rotor-side hub contour 14 and a stator contour 15.
  • Each impeller blade 11 has a flow inlet edge 16 and a flow outlet edge 17. Between the flow inlet edge 16 and the flow outlet edge 17 of each impeller blade 11 extends a pressure side, a suction side and radially outside of the impeller blade 11 a stator 12 facing outer surface 18 of the respective impeller blade 11.
  • the outer surface 18 of the impeller blade 11 adjacent to the stator 12 is used to seal against the stator 12.
  • Such an impeller 10, in which the outer surfaces 18 of the impeller blades 11 adjacent to the stator 12 indirectly, has no shroud and is also referred to as an open impeller.
  • a stator-side diffuser 19 is positioned downstream of the impeller 10.
  • the diffuser 19 includes a plurality of stator vanes 20.
  • the stator vanes 20 of the diffuser 19 are positioned in a diffuser flow channel 21 defined by the stator 12, wherein each of the stator vanes 20 of the diffuser 19 includes a flow entrance edge 22 and a flow exit edge 23.
  • an intermediate flow channel 26 extends, via which medium compressed in the radial compressor stage, starting from the impeller 10 in the direction of the diffuser 19 can flow.
  • a Radacheraum 28 said Radnerraum 28 according to Fig. 1 is coupled to the intermediate flow passage 26 via a gap 34.
  • the invention now relates to such details of a centrifugal compressor stage, with the help of which the risk of transient flow phenomena, which can lead to an asynchronous excitation of the open wheels, can be reduced.
  • all flow inlet edges 22 of all stator-side guide vanes 20 of the diffuser 19 lie on a first circular contour 29.
  • the flow inlet edges 22 of the stator vanes 20 of the diffuser 19 are located on the first circular contour 29 such that the flow inlet edges 22 of all the stator vanes 20 have an identical spacing from the flow inlet edges 22 of the adjacent vanes 20.
  • the flow inlet edges 22 of the guide vanes 20 of the diffuser 19 positioned next to one another in the circumferential direction of the diffuser flow channel 21 are thus distributed identically in the circumferential direction, so that accordingly all flow inlet edges 22 lying on the first circular contour 29 have identical circumferential spacings to adjacent flow inlet edges 22.
  • the flow outlet edges 23 of the stator-side guide vanes 20 of the diffuser 19 lie on a second circular contour 30.
  • the flow outlet edges 23 of the stator vanes 20 of the diffuser 19 are located on the second circular contour 30, that at least a first circumferential position of the diffuser flow channel 21, the flow outlet edge 23 of the respective stator side vane 20 positioned there to the flow outlet edge of at least one adjacent vane 20 at a different distance than at second circumferential positions of the diffuser flow channel 21.
  • no uniform distribution of the flow outlet edges 23 is provided in the circumferential direction of the diffuser flow channel 21, but rather is preferably at the first circumferential positions the uniform distribution of the flow outlet edges 23, which are all on the second circular contour 30, lifted, so as to reduce the risk of transient flow phenomena that can lead to an asynchronous excitation of the open wheels.
  • the corresponding flow outlet edge 23 has a different distance to the respective adjacent flow outlet edges 23, however, that at the other circumferential positions the flow outlet edges 23 are equally distributed in terms of their circumferential positions.
  • the flow outlet edges 23 in a second extreme case, it is possible for the flow outlet edges 23 to have respective different spacings at all peripheral positions of the diffuser flow channel 21 relative to the respectively adjacent flow outlet edges 23.
  • the respective stator-side vanes 20 of the diffuser 19 preferably all have identical second stagger angles.
  • the stator vanes 20 positioned at the or each first circumferential position preferably have a first staggering angle deviating from the second staggering angle, in particular ⁇ 10 °, preferably ⁇ 7 °, more preferably ⁇ 5 °, most preferably ⁇ 3 ° ,
  • the flow outlet edges 23 of all stator-side guide vanes 20 of the diffuser 19 may have different distances to the respectively adjacent flow outlet edges 23.
  • a flow outlet edge 23 "(see dashed line of in Fig. 2 Right vane) in the direction of the pressure side 25 of the respective adjacent vane 20 or a flow outlet edge 23 '(see dashed line of in Fig. 2 left guide blade) are displaced in the direction of the suction side 24 of the respective adjacent guide blade 20 in the circumferential direction, in such a way that as before all flow outlet edges 23 lie on the second circular contour 30.
  • Those selected vanes 20, which have a different staggering angle compared to the other stator vanes 20, are characterized in that their staggering angle deviates, in particular by ⁇ 10 °, particularly preferably ⁇ 5 °, from the staggering angles of the remaining vanes 20 of the diffuser 19 ,
  • At least one stator-side guide vane 20 of the diffuser 19 between the flow inlet edge 22 and the flow outlet edge 23 has a different curvature, namely a suction side 24 'and a pressure side 25' with respect to the other vanes 20 deviating curvature.
  • stator-side guide vanes 20 of the diffuser 19 it is possible for all the stator-side guide vanes 20 of the diffuser 19 to have different curvatures.
  • the diffuser flow channel 21 in order to reduce the risk of unsteady flow phenomena that may lead to asynchronous excitation of the open impellers, it is proposed to change at least a third circumferential position of the diffuser flow channel 21 a diffuser flow channel section 33 formed between adjacent stator vanes 20 of the diffuser 19 such that it is the same has a different flow cross-section with respect to the diffuser flow channel sections formed at fourth circumferential positions.
  • the respective diffuser flow channel section 33 has a reduced flow cross section, namely the stator side walls 31, 32 delimiting the respective diffuser flow channel section 33, reducing the flow cross section of the respective diffuser flow channel section 33 inwardly are arched into it.
  • the respective diffuser flow channel section 33 bounding side walls 31, 32 may be curved into the respective diffuser flow channel section 33 inside. It is also possible at selected circumferential positions the respective diffuser flow channel section with respect to its flow cross section expand, in which case at least one of these side walls 31, 32 is arched outwardly into the stator 12 in.
  • the diffuser flow channel sections 33 it is possible for the diffuser flow channel sections 33 to each have different flow cross sections at all circumferential positions of the diffuser flow channel 21.

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

Claims (4)

  1. Etage de compresseur radial,
    comportant un stator (12),
    comportant une roue mobile (10) tournant par rapport au stator (12) avec plusieurs aubes de roue mobile (11) du côté du stator, et
    comportant un diffuseur (19) positionné en aval de la roue mobile (10) dans la direction d'écoulement avec plusieurs aubes directrices (20) du côté du stator, dans lequel chaque aube directrice (20) du côté du stator présente une arête d'entrée d'écoulement (22) et une arête de sortie d'écoulement (23), et dans lequel entre l'arête d'entrée d'écoulement (22) et l'arête de sortie d'écoulement (23) de l'aube directrice respective (20), un côté d'aspiration (24) et un côté de pression (25) de cette dernière s'étendent,
    dans lequel entre la roue mobile (10) et le stator (12) un espace latéral de roue (28) est réalisé, caractérisé en ce que
    toutes les arêtes d'entrée d'écoulement (22) des aubes directrices du côté du stator (20) sont situées sur un premier contour de cercle (29), à savoir de telle sorte que les arêtes d'entrée d'écoulement (22) de toutes les aubes directrices du côté du stator (20) présentent un espacement identique par rapport aux arêtes d'entrée d'écoulement (22) des aubes directrices (20) voisines respectives ;
    toutes les arêtes de sortie d'écoulement (23) des aubes directrices du côté de stator (20) sont situées
    sur un deuxième contour de cercle (30), à savoir de telle sorte que sur au moins une première position circonférentielle, l'arête de sortie d'écoulement (23) de l'aube directrice du côté du stator respective (20) présente par rapport à l'arête de sortie d'écoulement (23) d'au moins une aube directrice voisine (20) un espacement autre que sur les deuxièmes positions circonférentielles ;
    sur au moins une troisième position circonférentielle, une portion de canal d'écoulement de diffuseur (33) réalisée entre les pales directrices (20) du côté du rotor voisines présente une section transversale d'écoulement différant des portions de canal d'écoulement de diffuseur réalisée sur les quatrièmes positions circonférentielles.
  2. Etage de compresseur radial selon la revendication 1, caractérisé en ce que
    sur les deuxièmes positions circonférentielles, les pales directrices du côté du stator (20) respectives présentent toutes des deuxièmes angles de décalage identiques ; et
    sur la ou chaque première position circonférentielle, les pales directrices du côté du stator (20) respectives présentent un premier angle de décalage, qui diffère du deuxième angle de décalage.
  3. Etage de compresseur radial selon la revendication 2, caractérisé en ce que le premier angle de décalage diffère du deuxième angle de décalage de ± 10°, de préférence de ± 7°, de manière particulièrement préférée de ± 5°.
  4. Etage de compresseur radial selon une des revendications 1 à 3, caractérisé en ce que par rapport aux quatrièmes positions circonférentielles, sur la ou chaque troisième position circonférentielle entre les aubes directrices (20), au moins une paroi latérale (31,32) délimitant la portion de canal d'écoulement de diffuseur (33) est bombée vers l'intérieur dans la portion de canal d'écoulement de diffuseur (33) en réduisant la section transversale d'écoulement et/ou est bombée vers l'extérieur dans le stator (12) en agrandissant la section transversale d'écoulement.
EP15179255.3A 2014-09-02 2015-07-31 Étage de compresseur radial Active EP2993357B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014012765.6A DE102014012765A1 (de) 2014-09-02 2014-09-02 Radialverdichterstufe

Publications (3)

Publication Number Publication Date
EP2993357A2 EP2993357A2 (fr) 2016-03-09
EP2993357A3 EP2993357A3 (fr) 2016-04-13
EP2993357B1 true EP2993357B1 (fr) 2018-02-21

Family

ID=53765155

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15179255.3A Active EP2993357B1 (fr) 2014-09-02 2015-07-31 Étage de compresseur radial

Country Status (7)

Country Link
US (1) US20160061219A1 (fr)
EP (1) EP2993357B1 (fr)
JP (1) JP6716220B2 (fr)
CN (1) CN105387002B (fr)
DE (1) DE102014012765A1 (fr)
NO (1) NO3191511T3 (fr)
RU (1) RU2691699C2 (fr)

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DE102015219556A1 (de) 2015-10-08 2017-04-13 Rolls-Royce Deutschland Ltd & Co Kg Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
KR102427392B1 (ko) * 2018-01-24 2022-07-29 한화에어로스페이스 주식회사 압축기용 디퓨저
EP3650709A1 (fr) * 2018-11-08 2020-05-13 ABB Turbo Systems AG Dispositif diffuseur à aubes pour un compresseur radial
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
EP3848590A1 (fr) 2020-01-07 2021-07-14 ABB Schweiz AG Zone d'écoulement d'un compresseur, compresseur doté d'une telle zone d'écoulement et turbocompresseur doté du compresseur
US11441516B2 (en) * 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine
RU2757150C1 (ru) * 2020-11-03 2021-10-11 Акционерное общество "Интер РАО - Электрогенерация" Осевой многоступенчатый компрессор с впрыском воды в его проточную часть
CN113882971B (zh) * 2021-09-15 2023-02-03 浙江理工大学 一种火箭发动机涡轮泵的定子导叶结构

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Also Published As

Publication number Publication date
DE102014012765A1 (de) 2016-03-03
JP6716220B2 (ja) 2020-07-01
CN105387002A (zh) 2016-03-09
RU2691699C2 (ru) 2019-06-17
RU2015137073A3 (fr) 2018-10-29
EP2993357A3 (fr) 2016-04-13
CN105387002B (zh) 2019-10-25
US20160061219A1 (en) 2016-03-03
JP2016053363A (ja) 2016-04-14
NO3191511T3 (fr) 2018-02-17
RU2015137073A (ru) 2017-03-07
EP2993357A2 (fr) 2016-03-09

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