EP3581802A1 - Dispositif et procédé d'appui d'un rotor de turbomachine radiale - Google Patents

Dispositif et procédé d'appui d'un rotor de turbomachine radiale Download PDF

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Publication number
EP3581802A1
EP3581802A1 EP18177778.0A EP18177778A EP3581802A1 EP 3581802 A1 EP3581802 A1 EP 3581802A1 EP 18177778 A EP18177778 A EP 18177778A EP 3581802 A1 EP3581802 A1 EP 3581802A1
Authority
EP
European Patent Office
Prior art keywords
radial
impeller
imp
shaft
housing
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Withdrawn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
EP18177778.0A
Other languages
German (de)
English (en)
Inventor
Frederic Hilgenberg
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP18177778.0A priority Critical patent/EP3581802A1/fr
Priority to PCT/EP2019/063179 priority patent/WO2019238366A1/fr
Publication of EP3581802A1 publication Critical patent/EP3581802A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
    • 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
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2230/70—Disassembly methods

Definitions

  • the invention relates to a method for disassembling or assembling such an arrangement.
  • Arrangements of the type defined at the outset are generally used for impellers which are arranged or mounted on the fly. This means that the bearing of the shaft or the rotor - in particular the radial bearing of the rotor - is only on one axial side of the impeller / the impellers. Accordingly, the radial turbine engine impeller is attached to a shaft end of the shaft.
  • Such an arrangement as is also known from so-called geared turbo compressors, can also be used independently of a geared turbo compressor - that is, driven or driving in another way.
  • these radial turbo machine impellers - impellers for short - are connected axially, preferably by means of a Hirth toothing - to a shaft end.
  • a shaft seal for example a gas seal or mechanical seal (fluid seal) and then a radial bearing are provided in the axial continuation of the shaft.
  • an axial bearing is regularly provided, which absorbs at least part of the thrust arising from the impeller due to the pressure difference.
  • the housing that surrounds the impeller or the impellers is generally formed in one piece in the circumferential direction.
  • This advantageous embodiment is made possible because there are no obstructing components, in particular storage, on one side due to the flying mounting, which would prevent the housing from being axially joined to the shaft end.
  • the housing can optionally have a substantially radial parting joint or a cover with a radial joint course. Basically, an essentially axial-radial parting line is also conceivable, but this option does not take advantage of all the advantages of the invention.
  • the gas seal is dismantled or assembled from the process gas side or from the side of the axial inflow into the compressor, since the shaft is anchored in the gearbox on the drive side, for example in the case of a geared compressor.
  • this would also be connected to the drive machine or another work machine in the line with a coupling, so that the gas seal is also installed on the process gas side in such a case.
  • Geared turbo compressors are already known, for example, from the following publications: EP3106670-A1 . EP3061991-A1 . EP3045686-A1 . WO2016091495-A1 . WO2016062549-A1 . WO2016046037-A1 . WO2015043879-A1 . WO2014195390-A1 . WO2012104366-A1 . WO2012104153-A1 ,
  • a decisive disadvantage of a generic arrangement of conventional design is that for assembly, disassembly or inspection, in particular the gas seal, the bearing or other components that are located axially behind the impeller, either the entire drive train or output train on which the Impeller of the compressor is attached axially at the end, must be dismantled or that the entire compressor of the generic arrangement must be dismantled from the shaft end and in itself in order to reach the corresponding components located axially behind the impeller.
  • the effort involved is extremely time and cost intensive, so that maintenance and service costs undesirably reduce the likelihood of sales of such arrangements.
  • the invention proposes an arrangement of the type defined in the introduction with the additional features of claim 1.
  • the procedural claims proposed a method for disassembly and assembly according to the invention.
  • one support element can be inserted per opening, which contacts the radial turbine engine impeller to intercept at least part of the weight.
  • These at least two - preferably several - support elements make it possible, on the one hand, to hold the impeller in an axial position, at the same time preventing the impeller from tipping and fixing the radial position of the impeller.
  • the support elements preferably also have at least partially radial support arrangements, for example radial contact surfaces or contact surfaces arranged obliquely between axial alignment and radial alignment, which contact on corresponding oblique surfaces of the impeller.
  • the first closable opening and a second closable opening are provided in the first housing wall.
  • a second support element is provided projecting through the second closable opening and the radial turbine machine impeller contacts a part of the weight force in a circumferential direction at a distance from the first support element.
  • a variant is particularly preferred in which a third closable opening is provided in the first housing wall, the arrangement being designed for an operating set-up in which the first support element and the second support element support the radial turbine engine impeller against the weight from below and the third support element secures the radial turbine engine impeller spaced from the other two support elements in the circumferential direction against tipping over.
  • the arrangement has exactly three support elements and corresponding openings in the housing wall.
  • At least one support element has a radial adjustment possibility for a contact surface for contacting the radial turbomachine impeller.
  • This radial adjustment option facilitates the insertion of the corresponding support elements through the corresponding openings, since the insertion, which is usually carried out axially, can take place independently of the contacting of the impeller.
  • a particularly preferred embodiment variant is one in which each support element has at least two contact surfaces, at least one of which is configured obliquely that this inclined contact surface with increasing radial approach to the impeller results in both radial and axial bracing or fixing of the impeller.
  • At least one support element preferably all support elements, has an axial adjustment facility for one, preferably all, contact surfaces for contacting the radial turbine machine impeller of the corresponding support element.
  • At least two of three support elements have radial position adjustment devices and preferably at least some - particularly preferably all - support elements are designed to be adjustable in their axial position of the contact surfaces.
  • the axial adjustability can be designed to be combinable with the introduction of the support elements into the corresponding openings of the housing wall, preferably in the axial direction.
  • the radial adjustability of the contact surfaces of the support elements is particularly preferably designed such that at least one support element has a rotatably mounted sleeve with an eccentric bore, a support carrier being arranged in the eccentric bore such that the support carrier has at least one contact surface for contacting the impeller is formed and such that a rotation of the sleeve results in a radial displacement of the at least one contact surface in the radial direction.
  • the support elements are preferably arranged and designed to cooperate in such a way that they are suitable, in an operating position, to support the radial turbine engine impeller against the gravitational pull.
  • the method according to the invention for disassembling the arrangement provides that in a first step closable openings in the housing wall of the housing are opened, in a second step support elements are guided through this opening, in a third step the support elements are brought into contact with the radial turbine machine impeller and are stationary are attached in such a way that the radial turbomachine impeller is supported and secured, in particular the weight of the radial turbomachine impeller. In a fourth step, the shaft seal and / or the radial bearing is / are removed.
  • Assembly is carried out in the reverse order of steps and in reverse of the correspondingly described actions.
  • FIGS. 1 - 4 each show an embodiment of an arrangement AR according to the invention in different representations, so that identical reference numerals here mean identical components of an identical embodiment.
  • information such as axial, radial, tangential or circumferential direction on an axis X of a shaft SH, which is identical to the axis of rotation.
  • the arrangement AR comprises a radial turbine machine impeller IMP, a housing CAS with an axial and radial flow opening, an inlet flow opening INL and an outlet flow opening EXT, further comprising a shaft SH that extends along the axis X, at least one radial bearing RB (in the Figure 1 two radial bearings RB are shown axially spaced from each other) and at least one shaft seal SHS.
  • the shaft seal SHS seals a process pressure of a process gas PFL possibly existing in the housing CAS in such a way that essentially no process gas PFL can escape from the inside INS of the housing CAS in the region of a through opening TH.
  • the shaft SH is fixed in a bearing block BSP in a radial, axial or spatially unambiguous position by means of the at least one radial bearing RB and here additionally by means of a second radial bearing RB and an axial bearing AB outside the housing CAS.
  • a radial turbo machine impeller IMP is detachably attached to a shaft end SE of the shaft SH.
  • a Hirth toothing can preferably be provided with an axial attachment of the radial turbine machine impeller IMP to the shaft end SE.
  • the through opening TH of the housing CAS is provided for a first housing wall CW1 of the housing CAS, in this exemplary embodiment a modular design of the housing CAS with possible disassembly of the first housing wall CW1 is provided.
  • This disassembly option is used to disassemble the radial turbo machine impeller IMP from the CAS housing and, if necessary, to access other compressor components of the AR arrangement, which are located inside the INS of the CAS housing.
  • a one-piece design of the first housing wall CW1 of the housing CAS with the rest of the housing CAS is also possible.
  • closable openings OP1, OP2, OP3 are provided in the housing wall CW1, through the support elements SP1, SP2, SP3 into the interior INS of the housing CAS can be inserted so that they protrude through the housing wall CW1 and in this way - quasi from the outside - contact the radial turbine engine impeller IMP at least a part of the weight force, so that the radial turbine engine impeller in the housing CRS in a certain spatial position relative to the housing CAS, in particular radially and axially - can be fixed.
  • the individual support elements SP1, SP2, SP3 are spaced radially and in the circumferential direction CDR, at least the first support element SP1 and the second support element SP2 supporting the radial turbine engine impeller IMP from below against the gravitational acceleration g - that is, intercepting the weight of the radial turbine engine impeller IMP.
  • the upper third support element SP3 has a radial gap GAP to the radial outer edge of the impeller IMP, because this third support element SP3 essentially serves to fix the spatial position against tilting of the impeller IMP.
  • FIG. 2 the rear of the housing wall CW1 is visible, support elements SP1 and SP3 or the two closable openings OP1, OP3 being shown in their preferred radial and circumferential positions.
  • the second support element (not shown) or the second closable opening OP2 is arranged correspondingly mirror-symmetrically to an imaginary vertical plane through the axis X in the first housing wall CW1.
  • the Figures 3 and 4 show in detail the structure of a corresponding support element SP1, SP2, SP3.
  • the support element SP1, SP2, SP3 are to be fastened with fixing elements FXT virtually stationary on the first housing wall CW1 after passing through a corresponding lockable opening OP1, OP2, OP3.
  • the support element SP1 - SP3 essentially consists of an outer sleeve OSV, an inner sleeve ISV and a central bolt CBT. Contact surfaces CSF are provided on the central bolt CBT for contacting and intercepting the radial turbine engine impeller IMP.
  • the inner sleeve ISV has an eccentric bore EXC for receiving the central pin CBT.
  • the central bolt CBT shifts in the radial direction, so that in a certain circumferential position of the inner sleeve ISV the contact surfaces CSF of the support element SP1-SP3 contact corresponding contact surfaces of the radial turbine machine impeller IMP and in this way with a corresponding setting of all the provided support elements SP1-SP3 of an arrangement AR according to the invention, the radial turbine machine impeller IMP is fixedly positioned relative to the housing CAS and in particular the weight of the impeller IMP is absorbed.
  • each of the closable openings OP1, OP2, OP3 in the first housing wall CW1 of the housing CRF is opened in the first step 1.
  • support elements SP1-SP3 are guided through these openings OP1-OP3.
  • the support elements SP1 - SP3 are brought into contact with the radial turbine machine impeller and fixed in place. The attachment is carried out in such a way that the radial turbomachine impeller IMP is supported and secured, in particular the weight of the radial turbomachine impeller IMP.
  • the support elements SP1, SP2, SP3 receive the concentric bearings of the shaft SH with the impeller IMP, so that assembly and disassembly of the shaft seal SHS and the bearing RB is possible.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18177778.0A 2018-06-14 2018-06-14 Dispositif et procédé d'appui d'un rotor de turbomachine radiale Withdrawn EP3581802A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP18177778.0A EP3581802A1 (fr) 2018-06-14 2018-06-14 Dispositif et procédé d'appui d'un rotor de turbomachine radiale
PCT/EP2019/063179 WO2019238366A1 (fr) 2018-06-14 2019-05-22 Dispositif, procédé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18177778.0A EP3581802A1 (fr) 2018-06-14 2018-06-14 Dispositif et procédé d'appui d'un rotor de turbomachine radiale

Publications (1)

Publication Number Publication Date
EP3581802A1 true EP3581802A1 (fr) 2019-12-18

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ID=62636112

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18177778.0A Withdrawn EP3581802A1 (fr) 2018-06-14 2018-06-14 Dispositif et procédé d'appui d'un rotor de turbomachine radiale

Country Status (2)

Country Link
EP (1) EP3581802A1 (fr)
WO (1) WO2019238366A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116677628B (zh) * 2023-06-13 2024-03-12 湖北三峰透平装备股份有限公司 一种高速直联鼓风机

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU432760B2 (en) * 1969-05-29 1973-02-20 Henry Tippett William An improved centrifugal pump
WO2012104153A1 (fr) 2011-02-02 2012-08-09 Siemens Aktiengesellschaft Joint de séparation étagé sur un carter de transmission d'une machine à fluide
WO2012104366A1 (fr) 2011-02-02 2012-08-09 Siemens Aktiengesellschaft Ajustage angulaire accouplé d'un aubage directionnel de sortie
EP2644863A1 (fr) * 2010-11-26 2013-10-02 Mitsubishi Heavy Industries, Ltd. Outil et procédé de démontage/montage d'un dispositif de turbine
WO2014195390A1 (fr) 2013-06-06 2014-12-11 Siemens Aktiengesellschaft Compresseur à engrenage
WO2015043879A1 (fr) 2013-09-25 2015-04-02 Siemens Aktiengesellschaft Compresseur à engrenage et procédé de montage
WO2016046037A1 (fr) 2014-09-23 2016-03-31 Siemens Aktiengesellschaft Boîtier de transmission séparable à élément d'étanchéité pour jonction étagée
WO2016062549A1 (fr) 2014-10-21 2016-04-28 Siemens Aktiengesellschaft Joint de séparation à gradins installé au niveau d'un carter d'engrenage
WO2016091495A1 (fr) 2014-12-08 2016-06-16 Siemens Aktiengesellschaft Compresseur à engrenages et ensemble comprenant un entraînement et un compresseur à engrenages
EP3045686A1 (fr) 2015-01-14 2016-07-20 Siemens Aktiengesellschaft Agencement pour fixer une volute sur un boîtier de transmission et compresseur à engrenages avec un tel agencement
EP3061991A1 (fr) 2015-02-24 2016-08-31 Siemens Aktiengesellschaft Logement de compresseur, compresseur
EP3106670A1 (fr) 2015-06-15 2016-12-21 Siemens Aktiengesellschaft Turbocompresseur de transmission
EP3324063A1 (fr) * 2016-11-17 2018-05-23 General Electric Company Un système comprenant une structure de support pour un rotor

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU432760B2 (en) * 1969-05-29 1973-02-20 Henry Tippett William An improved centrifugal pump
EP2644863A1 (fr) * 2010-11-26 2013-10-02 Mitsubishi Heavy Industries, Ltd. Outil et procédé de démontage/montage d'un dispositif de turbine
WO2012104153A1 (fr) 2011-02-02 2012-08-09 Siemens Aktiengesellschaft Joint de séparation étagé sur un carter de transmission d'une machine à fluide
WO2012104366A1 (fr) 2011-02-02 2012-08-09 Siemens Aktiengesellschaft Ajustage angulaire accouplé d'un aubage directionnel de sortie
WO2014195390A1 (fr) 2013-06-06 2014-12-11 Siemens Aktiengesellschaft Compresseur à engrenage
WO2015043879A1 (fr) 2013-09-25 2015-04-02 Siemens Aktiengesellschaft Compresseur à engrenage et procédé de montage
WO2016046037A1 (fr) 2014-09-23 2016-03-31 Siemens Aktiengesellschaft Boîtier de transmission séparable à élément d'étanchéité pour jonction étagée
WO2016062549A1 (fr) 2014-10-21 2016-04-28 Siemens Aktiengesellschaft Joint de séparation à gradins installé au niveau d'un carter d'engrenage
WO2016091495A1 (fr) 2014-12-08 2016-06-16 Siemens Aktiengesellschaft Compresseur à engrenages et ensemble comprenant un entraînement et un compresseur à engrenages
EP3045686A1 (fr) 2015-01-14 2016-07-20 Siemens Aktiengesellschaft Agencement pour fixer une volute sur un boîtier de transmission et compresseur à engrenages avec un tel agencement
EP3061991A1 (fr) 2015-02-24 2016-08-31 Siemens Aktiengesellschaft Logement de compresseur, compresseur
EP3106670A1 (fr) 2015-06-15 2016-12-21 Siemens Aktiengesellschaft Turbocompresseur de transmission
EP3324063A1 (fr) * 2016-11-17 2018-05-23 General Electric Company Un système comprenant une structure de support pour un rotor

Also Published As

Publication number Publication date
WO2019238366A1 (fr) 2019-12-19

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