EP3299629A1 - Carter de turbocompresseur, procédé de fabrication - Google Patents

Carter de turbocompresseur, procédé de fabrication Download PDF

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Publication number
EP3299629A1
EP3299629A1 EP16190517.9A EP16190517A EP3299629A1 EP 3299629 A1 EP3299629 A1 EP 3299629A1 EP 16190517 A EP16190517 A EP 16190517A EP 3299629 A1 EP3299629 A1 EP 3299629A1
Authority
EP
European Patent Office
Prior art keywords
inflow
tcc
ina1
section
axial
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Withdrawn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
EP16190517.9A
Other languages
German (de)
English (en)
Inventor
Marcus Meyer
Dieter Nass
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 EP16190517.9A priority Critical patent/EP3299629A1/fr
Priority to JP2019516133A priority patent/JP6667721B2/ja
Priority to EP17765404.3A priority patent/EP3491247B1/fr
Priority to PCT/EP2017/072436 priority patent/WO2018054691A1/fr
Publication of EP3299629A1 publication Critical patent/EP3299629A1/fr
Withdrawn legal-status Critical Current

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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
    • 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
    • F04D17/125—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 the casing being vertically split
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the invention relates to a turbocompressor housing which extends along a longitudinal axis, the turbocompressor housing having an inflow of an axial inflow section into an interior space and an outflow of an axial outflow section out of the interior.
  • the invention relates to a method for producing the turbocompressor housing.
  • Turbo compressors with corresponding housings are used in many places. There is a common need in the industry to deliver gases to a higher pressure.
  • An example of such a compressor shows the US Pat. No. 7,156,627 B2 .
  • the invention is concerned with such and similar compressors, the type of drive here is arbitrary and not of significant importance.
  • Turbo compressors, in particular radial compressors of a type in which a shaft with one or more compressor impellers is arranged between two bearings, are also referred to as single-shaft compressors. So-called single-shaft compressors are the preferred field of application of the invention.
  • Turbo compressor housings for these machines generally have a horizontal or vertical parting line.
  • turbocompressors are exposed to corrosive media, it is customary to produce these from a suitably corrosion-resistant material. Basically, it is sufficient to line or coat the turbocompressor housing in the wetted area with a corrosion-resistant material.
  • the accessibility for coating the interior surface of the turbocompressor housing is regularly very difficult, sometimes impossible for corresponding welding machines. For this reason, partial manual surfacing must therefore be used for production be performed to apply the corrosion resistant layer.
  • the complete housing is made of a corrosion resistant material, such as a corrosion resistant cast material.
  • turbocompressor housing Based on the high production costs and the high cost of materials for a turbocompressor housing, which is suitable for the transport of corrosive gases, it has the object of developing an initially defined turbocompressor housing such that with a relatively low production cost despite a cost reduction, a corrosion-resistant Housing can be produced, preferably with less effort, lower costs and an increased degree of automation.
  • turbocompressor housing has a coating in the region in which the medium to be conveyed also acts corrosive. This is the case in particular in the inflow region into the turbocompressor housing. Preferably, only the inflow section is coated corrosion-inhibiting and the outflow section does not have this coating.
  • Turbo compressors in particular radial turbo compressors, have axially between an inflow and an outflow a circumferentially extending seal which sealingly separates the axial inflow portion and inflow portion from the outflow portion. In this case, the relatively low inflow pressure always prevails in the inflow region and the differential pressure between the inflow pressure and the outflow pressure rests on this seal.
  • a plurality of circumferentially extending seals may be provided at axial distances from each other, the kaskardenartig the inflow pressure and the Abströmtik in pressure differential steps from each other.
  • the axial inflow section preferably only the axial inflow section, is corrosion resistant must be executed, because only there, the process fluid tends to condensation.
  • axial inflow section and "axial outflow section” used mean that the respective housing section has an axial extension and the respective axially extending housing section comprises an inflow or outflow. These terms do not mean that the inflow or outflow must extend axially.
  • axial inflow section and “axial outflow section may also be formulated as” axial housing section with inflow "and” axial housing section with outflow ", respectively.
  • the invention provides that a parting plane between the axial inflow section and the axial outflow section is provided and these two sections are welded together by means of a weld extending through the wall thickness.
  • This construction opens up the possibility of initially coating the inflow section on the part of an interior of the turbocompressor housing and then welding together the two axial sections. Accordingly, the accessibility for the coating of the interior of the turbocompressor housing is given and this type of coating can preferably be carried out automatically.
  • the inflow section and the outflow section can be joined together in a welded manner along a circumferentially extending weld seam extending through the wall thickness. In this way it is possible to select the coating material substantially independently of the material of the outflow section and the material of the weld.
  • the inflow section of the turbocompressor housing also comprises the sealing shoulder which keeps the potentially corrosive process medium in the inflow region away from the remaining regions of the turbocompressor housing.
  • the coating region extends from a radially extending boundary plane axially into the interior from the parting plane, the boundary plane being arranged axially between the parting plane and the abutment surface.
  • the coating is formed corrosion inhibiting. This means that the coating of the intended process gas for the compression process of the turbocompressor corrodes less quickly than the base material of the turbocompressor housing in the Einstömabites.
  • the joining seam of the weld between the inflow section and the outflow section is not located in the coated area. Accordingly, the coating material can be freely selected from the welding material for the joining of the inflow section and the outflow section.
  • At least the Einstömabêt to the longitudinal axis of the turbocompressor housing is formed rotationally symmetrical with respect to the contour of the interior.
  • the rotational symmetry should be such that automated coating is possible. Any recesses, for example for an inflow, count in the inventive Terminology of rotational symmetry for the purpose of automating the coating does not destroy the required rotational symmetry.
  • the inflow section is designed as a forged component and / or the outflow section as a cast component.
  • the following steps are carried out.
  • the axial inflow section and the axial outflow section are provided.
  • the interior of the inflow section is at least partially coated in a coating area with a coating.
  • the inflow portion and the outflow portion are welded together along a circumferentially extending, by a wall thickness extending weld in a radially extending parting plane between the axial inflow portion and the axial outflow portion.
  • FIG. 1 shows a radial turbocompressor as a single-shaft machine with a turbocompressor housing TCC according to the invention in a schematic representation as a longitudinal section.
  • the turbocompressor housing TCC extends along a longitudinal axis X.
  • the FIG. 1 shows internals of the turbocompressor, to clarify the function of the turbocompressor housing TCC.
  • a rotor R of the turbo-compressor which belongs to a to be built into the turbo compressor housing TCC bundle CART.
  • the turbo compressor housing TCC or a jacket section BCA of the turbocompressor housing TCC is closed by means of a detachable second cover CV2.
  • the opposite axial end face (left) has a first cover CV1, which in the finished state is an integral part of the turbo compressor housing TCC and is not detachably attached.
  • the side of the non-detachable first cover CV1 has an inflow INL, through which a potentially corrosive process gas flows during operation of the turbocompressor.
  • the turbocompressor shown here has two outflows EXT, since the machine is double-flowed or double-flowed - that is also formed with two inflows INL1, INL2.
  • the right side arranged inflow INL2 and outflow EXT are irrelevant to the invention.
  • the inflow INL1 leads the process gas into an interior CAC of the turbo compressor housing TCC.
  • the turbocompressor housing TCC is formed in a radially extending parting plane SPL between an axial inflow section INA1 and an axial outflow section EXA1 along a circumferentially CDR extending weld welded by a wall thickness WSE.
  • the inner space CAC of the inflow portion INA1 is at least partially provided with a coating CLD in a coating area CLA.
  • the inflow section INA1 has a shoulder SSH protruding radially inward in the inside space CAC and extending in a circumferential direction CDR.
  • the shoulder SSH is designed as a sealing surface CSF with a bearing surface facing away from the inflow INL1.
  • This sealing surface CSF seals the inflow INL1 relative to the outflow EXT to a corresponding sealing surface of the bundle CART. Accordingly, the thermodynamics of the inflow INL1 remains axially restricted to the inflow section INA1.
  • the invention proposes to coat only one coating region CLA, which extends from a radially extending boundary plane CLM axially into the interior CAC from the parting plane SPL, the boundary plane CLM being arranged axially between the parting plane SPL and the abutment surface.
  • This corrosion-inhibiting coating CLD prevents corrosion of the turbocompressor housing TCC in the inflow section INA1.
  • the joining seam of the weld between the inflow section INA1 and the outflow section EXA1 is not in the coated area. Therefore, the welding material and the material of the outflow section EXA1 can be selected independently of the material of the coating CLD.
  • the inner contour of the interior CAC of the inflow section INA1 is rotationally symmetrical, except for the recess for the inflow INL1, so that automated coating can take place, in particular build-up welding of the coating material.
  • the inflow section INA1 is formed as a forged component, the outflow section EXA1 being formed as a cast component.
  • FIG. 2 shows a flowchart of the inventive method for producing a turbo compressor housing TCC.
  • a first step a provision is made of the axial inflow section INA1 of an axial outflow section EXA1.
  • a second step b an at least partial coating of the interior CAC of the inflow section INA1 takes place with a coating CLD in a coating area CLA.
  • This step is preferably automated.
  • a third step c) the inflow section INA1 and the outflow section EXA1 are welded together along a circumferentially extending and through the entire wall thickness extending weld WSE.
  • the weld lies in a radially extending parting plane SPL between the axial inflow section INA1 and the axial outflow section EXA1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16190517.9A 2016-09-26 2016-09-26 Carter de turbocompresseur, procédé de fabrication Withdrawn EP3299629A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP16190517.9A EP3299629A1 (fr) 2016-09-26 2016-09-26 Carter de turbocompresseur, procédé de fabrication
JP2019516133A JP6667721B2 (ja) 2016-09-26 2017-09-07 ターボコンプレッサハウジングおよび製造方法
EP17765404.3A EP3491247B1 (fr) 2016-09-26 2017-09-07 Carter de turbocompresseur, procédé de fabrication
PCT/EP2017/072436 WO2018054691A1 (fr) 2016-09-26 2017-09-07 Carter de turbocompresseur, procédé de fabrication

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16190517.9A EP3299629A1 (fr) 2016-09-26 2016-09-26 Carter de turbocompresseur, procédé de fabrication

Publications (1)

Publication Number Publication Date
EP3299629A1 true EP3299629A1 (fr) 2018-03-28

Family

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP16190517.9A Withdrawn EP3299629A1 (fr) 2016-09-26 2016-09-26 Carter de turbocompresseur, procédé de fabrication
EP17765404.3A Active EP3491247B1 (fr) 2016-09-26 2017-09-07 Carter de turbocompresseur, procédé de fabrication

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP17765404.3A Active EP3491247B1 (fr) 2016-09-26 2017-09-07 Carter de turbocompresseur, procédé de fabrication

Country Status (3)

Country Link
EP (2) EP3299629A1 (fr)
JP (1) JP6667721B2 (fr)
WO (1) WO2018054691A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006126993A1 (fr) * 2005-05-24 2006-11-30 Honeywell International Inc. Compresseur turbochargeur ayant une resistance amelioree a l'erosion/corrosion
US7156627B2 (en) 2001-06-05 2007-01-02 Siemens Industrial Turbomachinery B.V. Compressor unit comprising a centrifugal compressor and an electric motor
WO2013153020A2 (fr) * 2012-04-12 2013-10-17 Nuovo Pignone Srl Procédé permettant d'empêcher la corrosion et composant obtenu au moyen d'un tel procédé
US20150267559A1 (en) * 2012-12-28 2015-09-24 Mitsubishi Heavy Industries, Ltd. Method of manufacturing rotary machine, method of plating rotary machine, and rotary machine
WO2016042002A1 (fr) * 2014-09-19 2016-03-24 Siemens Aktiengesellschaft Montage d'une turbomachine radiale par insertion axiale d'un faisceau dans une boîtier en forme de pot, le faisceau comportant un couvercle qui est maintenu de façon déplaçable axialement sur le faisceau
WO2016041800A1 (fr) * 2014-09-16 2016-03-24 Siemens Aktiengesellschaft Carter d'une turbomachine radiale à énergie fluidique et turbomachine radiale à énergie fluidique

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7156627B2 (en) 2001-06-05 2007-01-02 Siemens Industrial Turbomachinery B.V. Compressor unit comprising a centrifugal compressor and an electric motor
WO2006126993A1 (fr) * 2005-05-24 2006-11-30 Honeywell International Inc. Compresseur turbochargeur ayant une resistance amelioree a l'erosion/corrosion
WO2013153020A2 (fr) * 2012-04-12 2013-10-17 Nuovo Pignone Srl Procédé permettant d'empêcher la corrosion et composant obtenu au moyen d'un tel procédé
US20150267559A1 (en) * 2012-12-28 2015-09-24 Mitsubishi Heavy Industries, Ltd. Method of manufacturing rotary machine, method of plating rotary machine, and rotary machine
WO2016041800A1 (fr) * 2014-09-16 2016-03-24 Siemens Aktiengesellschaft Carter d'une turbomachine radiale à énergie fluidique et turbomachine radiale à énergie fluidique
WO2016042002A1 (fr) * 2014-09-19 2016-03-24 Siemens Aktiengesellschaft Montage d'une turbomachine radiale par insertion axiale d'un faisceau dans une boîtier en forme de pot, le faisceau comportant un couvercle qui est maintenu de façon déplaçable axialement sur le faisceau

Also Published As

Publication number Publication date
EP3491247B1 (fr) 2020-04-01
WO2018054691A1 (fr) 2018-03-29
JP2019529782A (ja) 2019-10-17
JP6667721B2 (ja) 2020-03-18
EP3491247A1 (fr) 2019-06-05

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