EP3141761A1 - Boîtier à spirales, turbomachine radiale, procédé de montage - Google Patents

Boîtier à spirales, turbomachine radiale, procédé de montage Download PDF

Info

Publication number
EP3141761A1
EP3141761A1 EP15184160.8A EP15184160A EP3141761A1 EP 3141761 A1 EP3141761 A1 EP 3141761A1 EP 15184160 A EP15184160 A EP 15184160A EP 3141761 A1 EP3141761 A1 EP 3141761A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
radial
guide vanes
disk
diffuser disk
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.)
Withdrawn
Application number
EP15184160.8A
Other languages
German (de)
English (en)
Inventor
Jan Weule
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
Priority to EP15184160.8A priority Critical patent/EP3141761A1/fr
Publication of EP3141761A1 publication Critical patent/EP3141761A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates to a spiral casing of a radial turbomachine, comprising a collecting spiral extending spirally in the circumferential direction about an axis of rotation of the turbomachine, comprising a radial diffuser, which is radially conducting between an impeller and the collecting spiral, wherein the radial diffuser on an axial side of a first Diffuser disc and on the other axial side is limited at least over a partial radial section of a second diffuser disc, wherein the radial diffuser vanes, which segment the radial diffuser in a radial region in the circumferential direction in flow passages, wherein the second diffuser disc - an opening to the interior of the radial diffuser - is releasably secured to the volute.
  • the invention relates to a radial turbomachine with a corresponding volute casing and a method for mounting the volute casing by utilizing the structural features.
  • KR 2014106975 A shows a radial turbocompressor, probably as part of a Getriebeturbover confusers in one-stage design with flying storage, the impeller or the impeller outlet side empties into a radial diffuser, downstream of a collecting spiral is arranged.
  • the Leitbeschaufelung in the radial diffuser at the exit from the impeller or the impeller are provided, since with the connection to the radially outflow impeller, the crescent-shaped blades align the flow for the purpose of improving the efficiency and expansion of the efficient usable travel range of the compressor.
  • Conventional designs usually provide that the Leitbeschaufelung formed directly on a diffuser disc integrally or machined out, in particular milled.
  • this Leitbeschaufelung is inserted axially into the spiral housing as part of the radial diffuser.
  • the maximum radial outer dimension of the diffuser disk comprising the guide vanes is radially bounded by the opening of the spiral housing. This limit is also subject to the front side milled diffuser blades. From an aerodynamic point of view, it regularly happens that the diffuser blades would preferably result in a better efficiency and an even greater driving range of the machine with a longer extent extending radially outwards. Purely from the aerodynamic design, the vanes would protrude beyond the other outer radius of the diffuser disk or opening.
  • the diffuser blades are aerodynamically designed with this radial extent, which extends radially beyond the opening available for mounting. The projecting portion of these diffuser blades is then simply omitted or milled off, so that an assembly of the machine is possible. In this context one speaks also of cropped vanes. Accordingly, there is the aerodynamically not optimal implementation of the radial diffuser between the impeller or impeller outlet and the entry into the collecting spiral.
  • the spiral housing has, in this sense, at least one boundary wall extending along a circumferential direction, which behaves exactly geometrically with respect to the rotation axis.
  • This at least one boundary wall may be a radial or an axial or an obliquely bounding to these directions wall of the collecting spiral.
  • the collecting spiral is round in cross-section and changes the cross-sectional area along the circumferential direction.
  • indications such as radial, tangential, axial always relate to the axis of rotation of the radial turbocompressor, unless otherwise indicated.
  • the terms “inner”, “outer” with semantically related terms always refer to the interior of the radial turbomachine, in which the impeller is arranged and which is bounded by the volute casing or on the area outside the volute casing, which do not belong to the interior is.
  • the inventive modular splitting between the diffuser disk and the guide vanes results in greater flexibility with regard to the design of the radial diffuser and the assembly.
  • the vanes can be made of blanks of a much smaller dimension.
  • the invention is directed to volute with a radial diffuser having non-adjustable vanes.
  • the vanes are fixed in their angular position.
  • the guide vanes may also have a plurality of stages, which are arranged radially one behind the other, at least not all of which are radially located on the same diameter with their leading edge.
  • a preferred field of application of the invention are radial turbomachines in which the impeller is formed in diameter larger than one meter.
  • the invention can be used particularly advantageously for transmission turbo compressors in which the second diffuser disk is provided axially between the transmission or the transmission housing and the impeller.
  • the guide vanes are detachably fastened to the first diffuser disk by means of fastening elements.
  • the opening is formed such that the fasteners can be solved accessible or secured externally accessible through the opening, which is formed closable by means of the second diffuser disc. It makes sense here if the vanes abut the second diffuser disk with an axial end side in the closed state of the volute casing. This contact reduces unwanted bypass flow adjacent the flow passages formed by the vanes.
  • the second diffuser disk can also have recesses for this axial end face of the guide vanes, which can additionally reduce the bypass flow and optionally fix the guide vanes in their position in a form-fitting manner.
  • Another advantage of the adjacent contact between the second diffuser disc and the axial end face of the guide vanes comes into play when the fasteners are at least partially disposed in recesses, which in this axial end face are provided axially extending, such that when mounted second diffuser disc, the second diffuser disc covers the mouths of the recesses for the fastening elements in particular with respect to the flow. In this way, the flow at these recesses can not cause unwanted turbulence and possibly lead to erosion damage and further the fasteners are secured by the concern of the second diffuser disc on the front side and the covering of the recesses against complete release or detachment.
  • the first diffuser disk has recesses at the locations of the guide vanes, wherein the guide vanes may have a base, wherein the attachment of the vanes to the first diffuser disk provides that the base of the vanes each in Axially guided guided into the recess. In this way, a positive connection perpendicular to the axial direction due to the fitting of the base into the recesses.
  • the base of the guide vanes may either have exactly the profile of an airfoil of the guide vanes or deviate from this profile of the airfoil.
  • the airfoil profile is regularly a relatively complicated contour, which requires a high production cost, it makes sense if the socket has a simpler geometry, so that the recess into which the socket is inserted, also has only a simple cross-sectional geometry.
  • the base it is expedient for the base to have a different geometry relative to the airfoil and to be somewhat larger in relation to the airfoil with respect to a surface-normal direction of the airfoil.
  • the blade can be cylindrical, that is with a constant profile cross-section.
  • the advantages of the invention come in a development particularly useful for carrying, when a radial extent of the vanes in the final assembly position on the maximum Outside radius of the opening goes out, such that a purely axial movement of the guide vanes in the final assembly position through the opening is not possible, but at least one radial movement must be made in addition.
  • a movement in the circumferential direction can be superimposed.
  • the separation of the vanes is exploited by the diffuser disc while preventing the opening to be closed with the second diffuser disc is radially expanded.
  • a further advantageous embodiment of the invention provides that the axial height of the base of the guide vane in the region which extends beyond the radial extent of the opening is reduced compared to the other radial region, such that a pivoting movement of the guide vane into the recess during assembly is.
  • the guide vane can be introduced into the recess first approaching the mounting end position obliquely to the axial direction and obliquely to the radial direction with the socket first with the axially reduced height before the vane completely in the mounting position can be advanced radially and the base can be inserted into the recess with rotation of the vane about an axis of rotation, before the vanes is fastened with the fasteners.
  • the inventive method for mounting the spiral housing provides that, following the provision of the collecting spiral, the guide vanes are introduced individually into a final assembly position.
  • the already defined pivoting movement is carried out for each guide blade, before the guide blade is fastened in the end position to the first diffuser disk.
  • the opening of the volute casing is closed by means of the second diffuser disk. If necessary, find other assembly steps, which are not in essential connection with the invention, also take place between these steps described.
  • FIG. 1 schematically shows three-dimensionally an inventive volute VC of a radial turbomachine RTM.
  • guide vanes DV are provided, which - as well as in FIG. 2 - Align process fluid emerging from an impeller IMP with respect to a downstream inflow angle into a collection vial CV.
  • the impeller is arranged in rotation about an axis of rotation X, around which the collecting spiral CV and the radial diffuser RTF extend in the circumferential direction.
  • the guide vanes DV segment the radial diffuser RTF located radially between the impeller outlet and the inlet into the collecting spiral CV in the circumferential direction into flow passages for the process fluid.
  • the radial diffuser RTF is bounded on the left by a first diffuser disk DF1 and opposite on the right side by a second diffuser disk DF2.
  • the vanes DV are located between these two diffuser disks DF1, DF2.
  • the guide vanes on an airfoil AF and a base PF As well as in FIG. 3 can be seen, the guide vanes on an airfoil AF and a base PF.
  • the pedestal PF is made thicker than the profile of the cylindrical airfoil AF in the normal direction of the airfoil surface and has a simple geometry.
  • the base PF In the final assembly position in the first diffuser disk DF1 of the guide vanes DV, the base PF is in each case fitted in a form-fitting manner in a recess RS provided in the first diffuser disk DF1 for the guide blade.
  • the base PF is in this case designed such that the recess can be produced simply with a cylindrical milling cutter in a rectilinear movement in the first diffuser disk DF1.
  • the second diffuser disk DF2 is in FIG.
  • the individual guide vanes are inserted in their final assembly position in the first diffuser disk DF1 in the recesses RS.
  • This insertion corresponds to a pivoting movement or a pivoting.
  • a purely axial movement of the guide vanes DV in this final assembly position is not possible because the opening OP is not designed to large enough. Instead, the Einschwenkterrorism is that an axially and radially combined movement is provided for the introduction of the base PF in the recess RS.
  • the guide vanes DV are axially fitted with only a small clearance in the flow channel of the radial diffuser.
  • the base PF has in the region of radially over a reduced axial height or bevel FA.
  • the guide vanes can be approximated obliquely to the axis of rotation X of the final assembly position and moved radially and axially far enough that initially the radially projecting side of the guide vane DV of the Montageendposition or the first diffuser disk DF1 is closest.
  • fasteners FE are used to secure the vane DV of the first diffuser disc.
  • Appropriately screws are used for this purpose, which are screwed into depressions FERE, or recesses, in particular bores-provided on a first axial end face FFA1 of the guide vanes DV.
  • the depressions FERE in which the fastening elements FE have been inserted are covered by the second diffuser disk when it is in its final assembly position and at least partly abuts or approaches this first end face FFA1 of the stator vanes in this final assembly position Scope of possible manufacturing tolerances).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15184160.8A 2015-09-08 2015-09-08 Boîtier à spirales, turbomachine radiale, procédé de montage Withdrawn EP3141761A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15184160.8A EP3141761A1 (fr) 2015-09-08 2015-09-08 Boîtier à spirales, turbomachine radiale, procédé de montage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15184160.8A EP3141761A1 (fr) 2015-09-08 2015-09-08 Boîtier à spirales, turbomachine radiale, procédé de montage

Publications (1)

Publication Number Publication Date
EP3141761A1 true EP3141761A1 (fr) 2017-03-15

Family

ID=54065776

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15184160.8A Withdrawn EP3141761A1 (fr) 2015-09-08 2015-09-08 Boîtier à spirales, turbomachine radiale, procédé de montage

Country Status (1)

Country Link
EP (1) EP3141761A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108953230A (zh) * 2018-08-06 2018-12-07 南京磁谷科技有限公司 一种离心风机扩压器结构
CN112696482A (zh) * 2020-12-24 2021-04-23 钛灵特压缩机无锡有限公司 一种四级压缩模块可拆卸式离心空压机齿轮箱
US10989219B2 (en) 2019-02-04 2021-04-27 Honeywell International Inc. Diffuser assemblies for compression systems
CN117028318A (zh) * 2023-10-09 2023-11-10 浙江华擎航空发动机科技有限公司 一种扩压器总成结构及其安装方法

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1047663A (en) * 1911-05-22 1912-12-17 Franz Lawaczeck Turbine compressor or pump for elastic fluids.
US3973872A (en) * 1975-08-01 1976-08-10 Konstantin Pavlovich Seleznev Centrifugal compressor
EP0058533A1 (fr) * 1981-02-16 1982-08-25 Mitsubishi Jukogyo Kabushiki Kaisha Dispositif de diffuseur variable dans un compresseur centrifuge
US4824325A (en) 1988-02-08 1989-04-25 Dresser-Rand Company Diffuser having split tandem low solidity vanes
US4877369A (en) 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser control
US20080193288A1 (en) * 2007-02-14 2008-08-14 Borg Warner Inc. Diffuser restraint system and method
DE102010062968A1 (de) * 2010-12-13 2012-06-14 Robert Bosch Gmbh Radialverdichter für einen Turbolader, Turbolader
KR20140106975A (ko) 2013-02-27 2014-09-04 삼성테크윈 주식회사 압력 조절 장치를 구비한 압축 장치와, 이를 이용한 압력 조절 방법
WO2015077380A1 (fr) 2013-11-25 2015-05-28 Borgwarner Inc. Carter de compresseur en deux parties

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1047663A (en) * 1911-05-22 1912-12-17 Franz Lawaczeck Turbine compressor or pump for elastic fluids.
US3973872A (en) * 1975-08-01 1976-08-10 Konstantin Pavlovich Seleznev Centrifugal compressor
EP0058533A1 (fr) * 1981-02-16 1982-08-25 Mitsubishi Jukogyo Kabushiki Kaisha Dispositif de diffuseur variable dans un compresseur centrifuge
US4824325A (en) 1988-02-08 1989-04-25 Dresser-Rand Company Diffuser having split tandem low solidity vanes
US4877369A (en) 1988-02-08 1989-10-31 Dresser-Rand Company Vaned diffuser control
US20080193288A1 (en) * 2007-02-14 2008-08-14 Borg Warner Inc. Diffuser restraint system and method
DE102010062968A1 (de) * 2010-12-13 2012-06-14 Robert Bosch Gmbh Radialverdichter für einen Turbolader, Turbolader
KR20140106975A (ko) 2013-02-27 2014-09-04 삼성테크윈 주식회사 압력 조절 장치를 구비한 압축 장치와, 이를 이용한 압력 조절 방법
WO2015077380A1 (fr) 2013-11-25 2015-05-28 Borgwarner Inc. Carter de compresseur en deux parties

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108953230A (zh) * 2018-08-06 2018-12-07 南京磁谷科技有限公司 一种离心风机扩压器结构
US10989219B2 (en) 2019-02-04 2021-04-27 Honeywell International Inc. Diffuser assemblies for compression systems
CN112696482A (zh) * 2020-12-24 2021-04-23 钛灵特压缩机无锡有限公司 一种四级压缩模块可拆卸式离心空压机齿轮箱
CN117028318A (zh) * 2023-10-09 2023-11-10 浙江华擎航空发动机科技有限公司 一种扩压器总成结构及其安装方法
CN117028318B (zh) * 2023-10-09 2024-02-02 浙江华擎航空发动机科技有限公司 一种扩压器总成结构及其安装方法

Similar Documents

Publication Publication Date Title
DE69423789T2 (de) Stroemungsleiteinrichtung fuer den kompressorteil einer stroemungsmaschine
EP2108784B1 (fr) Turbomachine dotée d'un composant d'injecteur de fluide
EP2818724B1 (fr) Turbomachine et procédé
EP3141761A1 (fr) Boîtier à spirales, turbomachine radiale, procédé de montage
EP3121373B1 (fr) Roue de turbine refroidie, plus particulièrement pour un réacteur
DE102008025249A1 (de) Sammelraum und Verfahren zur Fertigung
CH710476A2 (de) Verdichter mit einer Axialverdichterendwandeinrichtung zur Steuerung der Leckageströmung in dieser.
DE102014009735B4 (de) Laufrad einer Strömungsmaschine
DE102011055373A1 (de) Kombinierter Dämpfungs- und Dichtungsstift für Turbinenlaufschaufel und verwandtes Verfahren
DE112011102807T5 (de) Abgasturbolader
EP3551890B1 (fr) Etage de retour
EP3682116A1 (fr) Compresseur radial comprenant un mécanisme à diaphragme iris pour un dispositif de charge d'un moteur à combustion interne, dispositif de charge et lamelle pour le mécanisme à diaphragme iris
DE102016113568A1 (de) Verfahren zum Herstellen eines Tandem-Leitschaufelsegments
EP3034788B1 (fr) Aube de compresseur d'une turbine a gaz
DE112015005131B4 (de) Kühlstruktur für Turbine, und Gasturbine
EP1522678A2 (fr) Méthode de fixation des aubes de machine de flux de fluide, et dispositif à cette fin
DE69318242T2 (de) Einlassregelanlage einer Turbomaschine
EP2514975B1 (fr) Turbomachine
CH701997A2 (de) Turbomaschine mit einer geformten Wabendichtung.
WO2018166716A1 (fr) Étage de retour et turbomachine à énergie fluidique radiale
EP3287611A1 (fr) Turbine à gaz et procédé de suspension d'un segment d'aube de guidage d'une turbine à gaz
DE102012215413B4 (de) Baugruppe einer Axialturbomaschine
EP3159487B1 (fr) Stator d'une turbine à gaz ayant un guidage d'air de refroidissement amélioré
DE102011121925A1 (de) Verdichter und Verfahren zum Betrieb eines Verdichters
WO2021083442A1 (fr) Ensemble aube directrice de turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20170916