EP3332106A1 - Procédé de montage d'une turbomachine et turbomachine - Google Patents

Procédé de montage d'une turbomachine et turbomachine

Info

Publication number
EP3332106A1
EP3332106A1 EP16781762.6A EP16781762A EP3332106A1 EP 3332106 A1 EP3332106 A1 EP 3332106A1 EP 16781762 A EP16781762 A EP 16781762A EP 3332106 A1 EP3332106 A1 EP 3332106A1
Authority
EP
European Patent Office
Prior art keywords
outer housing
inner part
cov2
cov1
turbomachine
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Withdrawn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
EP16781762.6A
Other languages
German (de)
English (en)
Inventor
Dieter Nass
Gregor Senyk
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 EP3332106A1 publication Critical patent/EP3332106A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F04D29/403—Casings; Connections of working fluid 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
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/58—Piston ring seals

Definitions

  • the invention relates to a method for assembling a turbomachine
  • the turbomachine having an outer casing
  • the turbomachine having an inner part for placement in the outer casing
  • outer housing comprises a located along an axis réellere ⁇ ADORABLE parting line, such that the outer casing in an outer casing upper part and a lower part outer housing is formed zer ⁇ divisible
  • the inner part in operation comprises rotor parts and static components provided for rotation about the axis
  • the invention relates to a turbomachine for mounting by the method.
  • Turbo compressors which are provided for the assembly method of the type defined, are widely used, in particular, as larger ⁇ re machines.
  • a turbocompressor is already described, which has a horizontal parting line.
  • simplistic ⁇ simpler representation there is shown that a
  • a disadvantage of the previous design and mounting method is that when placing the outer housing upper part on the outer housing lower part with inserted inner part extending in the circumferential direction sealing element is regularly damaged.
  • the sealing element is pushed out more or less strongly above the parting area or pushed into a bead as a result of the compression between the outer housing lower part and the inner part in the radial direction and because of the circumferentially acting frictional force on the seal when inserting the inner part.
  • the sealing element is additionally compressed radially and pressed even more radially in the parting joint area. In the last phase of lowering the
  • axial, radial or circumferential direction always refer to the axis of the outer housing. This axis is identical or at least parallel to the axis of rotation of the turbo engine or of the Ro ⁇ tors of the turbomachine.
  • the outer casing is called outer casing because it surrounds the inner part externally. The same applies quasi vice versa (mutatis mutandis) for the inner part.
  • the parting line extending along the axis is before Trains t ⁇ substantially flat, so that a parting plane is obtained.
  • This partial joint plane extends at least parallel to the axis of the turbomachine.
  • the rotational axis of the rotor of the turbomachine is located substantially in the parting plane during operation.
  • the part of the joint plane is at least radially aligned so that a trouble-free insertion of the inner part in the outer housing is possible.
  • the outer housing has at the axial Stirnsei ⁇ th each have an opening, thus shaft ends of the rotor of the inner part axially from the outer housing frontally ⁇ out can be performed.
  • These shaft ends which are provided on at least one axial side and pass through axial openings of the outer housing, serve to transmit torques to and from the rotor of the turbomachine.
  • Such an opening is sealed in each case in the region of a gap Zvi ⁇ rule of the shaft and the static parts of the outer housing which define the opening by at least one shaft seal.
  • the outer housing on the front side ver ⁇ closing lid one of the
  • Outer housing part and the outer housing upper part formed, preferably largely cylindrical, shell structure of the outer stannumuse - an outer housing shell - the front side ver ⁇ closing to form a complete outer housing.
  • a further preferred development of the invention provides that the cover closing the outer housing on the inside abuts on abutment shoulders of the outer housing jacket in such a way that an inner pressure increased in the outer housing in relation to the ambient pressure presses these covers axially against these abutment shoulders.
  • the turbo machines according to the invention are preferably systems in which in the generic outer housing there is always an internal pressure which is higher than the external ambient pressure during normal operation. More preferably, the respective end side cover provided in the terminology of the invention is part of the IN ⁇ nenteils and sets Tire- in the process according to the invention for mounting in the outer housing bottom part together with the rotor and optionally other non-rotating components.
  • this opening points in the circumferential direction between the opening contour and the shaft surface formed gap, which is preferably sealable by means of at least one Wellendich ⁇ tion.
  • this shaft seal is attached to the respective lid.
  • the lid is also carrier of a radial bearing and possibly also on at least one axial side of a thrust bearing.
  • the Anbrin ⁇ supply the various components on the cover has the particular advantage that the alignment work of the shaft seal and the respective bearings are fanned each other strongly agreed and the position and manufacturing tolerance chains are shortened, so that reporting expenses at constant production and from ⁇ a better precision can be achieved.
  • the inner housing is at least from ⁇ sectionally cylindrical, so that an axial displacement of the inner housing in the outer housing, at least within the limits of the requirements of the invention is possible.
  • the outer housing may be at least from cut ⁇ example be cylindrical, so that no axial collisions take place between the inner housing and the outer housing in the context of the present invention axial displacement.
  • Between the inner housing and the outer housing can be provided for the purpose of axial displacement, a sliding bearing of the corresponding cylinder sections of the inner housing outer contour and the outer housing inner contour.
  • At least in the context of axial displaceability of the contemplatge ⁇ housing should have a longer Axialerstre- ckung the cylindrical geometry with respect to the inner contour, so that the inner housing can be displaced in the outer housing axially largely resist ⁇ was free.
  • the seal which extends circumferentially around the inner housing, when lowering the inner part in the
  • Outer housing shell on the outer housing lower part radially is substantially free of contact, it is advantageous if in the corresponding seal at insertion opposite axial position, the inner surface of the outer housing has a recess which is radially widened with respect to the axially adjacent ⁇ be ⁇ sealing surface.
  • the sealing surface is one that comes in the after ⁇ Axial displacement of the inner housing relative to the outer housing, circumferentially extending seal for sealing contact.
  • This depression can be designed as a groove extending in the circumferential direction.
  • this groove preferably has a in the order of the Dich ⁇ tion (order of magnitude here means a groove depth of about 20% - 100% of the radial dimension of the seal cross-section, the chamfer may have between 50% -100% depth of the groove depth and, for example, in 15 ° - Be executed 20 °) formed bevel, which prevents the seal on the outer housing with the on ⁇ occurs in the sealed gap can be damaged in the context of the axial displacement of the inner housing.
  • order of magnitude means a groove depth of about 20% - 100% of the radial dimension of the seal cross-section
  • the chamfer may have between 50% -100% depth of the groove depth and, for example, in 15 ° - Be executed 20 °) formed bevel, which prevents the seal on the outer housing with the on ⁇ occurs in the sealed gap can be damaged in the context of the axial displacement of the inner housing.
  • Figures 1 5 different steps of erfindungsge ⁇ MAESSEN method of the assembly procedure in a schematic representation
  • FIG. 6 shows a schematic longitudinal section through a partial joint plane of a turbomachine according to the invention
  • FIG. 3 4, 5 is designated VII, VIII.
  • Figures 1 to 5 show schematically from partially different perspectives the flow of a method according to the invention for mounting a turbomachine TCO invention.
  • a schematic representation of the figure 6 shows a rapid Diale half of a longitudinal section in a parting plane PLC along an axis X - is synonymous here with a Rota ⁇ tion axis, a turbomachine TCO invention.
  • Figures 7 and 8 each show a detail which is shown in Figures 3, 4, 5 with VII, VIII.
  • FIG. 1 shows the provision of a
  • the outer housing OC extends along an axis X, which on the one hand is a longitudinal axis of the outer housing OC and on the other hand largely coincides ⁇ with the axis of rotation (hereinafter also simply referred to as axis X) of a rotor RO (shown in Figure 6) for rotation during the Operating rotor parts RE, eg impellers IMP.
  • the outer housing OC has a parting line SP extending along the axis X in a part-joint plane SPS.
  • the outer housing OC has at the axial end faces FF1, FF2 each have a closable by means of a cover COV1, COV2 opening OP.
  • FIG. 2 shows a step b) of the method according to the invention, during which an inner part IP is inserted into the outer housing lower part LP.
  • the radial Einset ⁇ zen of the inner part IP takes place in a horizontal orientation the axis X as far as possible following the gravity G until the axis X of the inner part IP - ie the axis of rotation ⁇ tion of the rotor RO is largely congruent with the axis X of the outer housing OC, so that the inner part IP in O ogepatuse OC comes indirectly or directly to the radial support.
  • Outer housing upper part UP on the outer housing lower part LP surrounding the inner part IP is placed radially.
  • Outer housing shell UP designated components form in the assembled state s ⁇ an outer housing jacket having the front-side axial openings OP. Together with the In ⁇ nenteil IP are provided for closing these openings cover cov1 been introduced as a part of the inner part into the outer housing part LP COV2.
  • the outer housing OC is designed in such a way that these covers COV1, COV2 come into contact axially from the inside against abutment shoulders CSH in the finished assembled state. When the internal pressure is increased, the covers COV1, COV2 are pressed sealingly against these abutment shoulders CSH, additional sealing elements (not shown in the drawings) being provided for the purpose of sealing.
  • FIG 3 shows that the axial position of the inner part IP to the outer housing OC corresponds to a first axial position AX1, so that a circumferentially extending seal SL of the outer surface of the inner part IP is in the same axial position as on the inner side.
  • Side of the outer casing OC provided recess REZ, so that the seal SL initially does not come into contact with the outer casing OC.
  • FIG. 4 shows the method step d), in which the inner part IP is displaced axially relative to the outer housing OC.
  • the recess REZ is provided with a bevel, so that the seal SL in the sealing position in which a radial contact with the sealing surface SLS under Quet ⁇ research of the seal SL is formed, is not damaged by the axial inlet.
  • the lid may also be carriers of bearings BEA, in particular a radial bearing and possibly also at least on one axial side of a thrust bearing.
  • the lid is also particularly suitable as a carrier of a shaft seal SSL, as shown in Figure 6.
  • the figures also show that during the axial displacement in step d), a cover COV1 likewise receives its axial end position.
  • Another advantageous possible ⁇ ness to displace the inner part IP this exporting ⁇ approximately example in which the displacement force is applied indirectly to the inner part IP with the provided on the other side cover COV2 on the inner part IP.
  • FIG. 5 shows that the two covers COV1, COV2 are fastened or secured against axial displacement in each case with fastening elements FE on the respective axial end faces FF1, FF2 in their respective cover end positions CAX1, CAX2.
  • the inner part IP can be moved substantially independently of the covers COV1, COV2.
  • the inner part IP can be moved substantially independently of the covers COV1, COV2.
  • the pressure conditions in the turbomachine TCO can Be ⁇ drove be formed such that the inner part IP remains in the axial end position AX2 due to axial thrusts.
  • a mechanical fuse can be provided, which can be realized for example in a mechanical clamping. This clamping can be introduced or secured, for example, through an opening in the outer housing OC or through an opening on at least one cover COVl, COV2 in a manner not shown in the figures.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Abstract

L'invention concerne un procédé de montage d'une turbomachine (TCO), la turbomachine (TCO) présentant un boîtier externe (OC), une partie interne (IP) destinée à être disposée dans le boîtier externe (OC), le boîtier externe (OC) présentant un joint de séparation (SP) s'étendant le long d'un axe (X), de telle manière que le boîtier externe (OC) est formé de manière à pouvoir être séparé en un élément supérieur de boîtier externe (UP) et un élément inférieur de boîtier externe (LP), la partie interne (IP) comprenant des éléments statiques (SE) et éléments rotoriques (RE) conçus pour tourner autour de l'axe (X) lors du fonctionnement, la partie interne (IP) présentant au moins un joint d'étanchéité (SL) s'étendant dans la direction circonférentielle pour étanchéifier une fente (GP) entre la partie interne (IP) et une surface d'étanchéité (SLS) du boîtier externe (OC), le procédé comprenant les étapes suivantes : a) fourniture de l'élément inférieur du boîtier externe (LP); b) insertion de la partie interne (IP) dans la partie inférieure du boîtier externe (LP), dans une première position axiale (AX1); c) assemblage de l'élément inférieur du boîtier externe (LP) et de la partie supérieure du boîtier externe (UP); d) déplacement par coulissement axial de la partie interne (IP) dans le boîtier externe (OC) par rapport au boîtier externe (OC), depuis la première position axiale (AX1) jusqu'à une position finale axiale (AX2), de sorte que le joint d'étanchéité (SL) vient en contact avec la surface d'étanchéité (SLS). Le procédé permet d'éviter des problèmes d'étanchéité et de montage.
EP16781762.6A 2015-11-10 2016-10-12 Procédé de montage d'une turbomachine et turbomachine Withdrawn EP3332106A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15193848.7A EP3168443A1 (fr) 2015-11-10 2015-11-10 Procede de montage d'une turbomachine et turbomachine
PCT/EP2016/074486 WO2017080742A1 (fr) 2015-11-10 2016-10-12 Procédé de montage d'une turbomachine et turbomachine

Publications (1)

Publication Number Publication Date
EP3332106A1 true EP3332106A1 (fr) 2018-06-13

Family

ID=54548034

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15193848.7A Withdrawn EP3168443A1 (fr) 2015-11-10 2015-11-10 Procede de montage d'une turbomachine et turbomachine
EP16781762.6A Withdrawn EP3332106A1 (fr) 2015-11-10 2016-10-12 Procédé de montage d'une turbomachine et turbomachine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP15193848.7A Withdrawn EP3168443A1 (fr) 2015-11-10 2015-11-10 Procede de montage d'une turbomachine et turbomachine

Country Status (5)

Country Link
US (1) US20180320597A1 (fr)
EP (2) EP3168443A1 (fr)
CN (1) CN108350810A (fr)
RU (1) RU2018119379A (fr)
WO (1) WO2017080742A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3770441A4 (fr) * 2018-04-27 2021-03-24 Mitsubishi Heavy Industries Compressor Corporation Compresseur et son procédé de fabrication
JP7565690B2 (ja) * 2020-02-07 2024-10-11 三菱重工コンプレッサ株式会社 圧縮機の製造方法及び圧縮機

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH592262A5 (fr) * 1975-07-04 1977-10-14 Bbc Brown Boveri & Cie
US4730832A (en) * 1985-09-13 1988-03-15 Solar Turbines Incorporated Sealed telescopic joint and method of assembly
JP4062811B2 (ja) * 1999-03-11 2008-03-19 株式会社Ｉｈｉ 可変容量型過給機のガスシール装置
DE102006027237A1 (de) * 2005-06-14 2006-12-28 Alstom Technology Ltd. Dampfturbine
CN103384753B (zh) * 2011-02-28 2015-07-08 阿尔斯通技术有限公司 带有在导叶支架与壳体之间的密封装置的涡轮
US8769816B2 (en) * 2012-02-07 2014-07-08 Siemens Aktiengesellschaft Method of assembling a gas turbine engine
DE102012202466B3 (de) 2012-02-17 2013-07-11 Siemens Aktiengesellschaft Montage einer Strömungsmaschine
DE102012203144A1 (de) * 2012-02-29 2013-08-29 Siemens Aktiengesellschaft Strömungsmaschine
DE102014218936A1 (de) * 2014-09-19 2016-03-24 Siemens Aktiengesellschaft Radialturbofluidenergiemaschine, Verfahren zur Montage

Also Published As

Publication number Publication date
US20180320597A1 (en) 2018-11-08
CN108350810A (zh) 2018-07-31
RU2018119379A3 (fr) 2019-11-28
EP3168443A1 (fr) 2017-05-17
RU2018119379A (ru) 2019-11-28
WO2017080742A1 (fr) 2017-05-18

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