WO2017076584A1 - Élément intérieur pour turbomachine, turbomachine et procédé de montage - Google Patents

Élément intérieur pour turbomachine, turbomachine et procédé de montage Download PDF

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Publication number
WO2017076584A1
WO2017076584A1 PCT/EP2016/074284 EP2016074284W WO2017076584A1 WO 2017076584 A1 WO2017076584 A1 WO 2017076584A1 EP 2016074284 W EP2016074284 W EP 2016074284W WO 2017076584 A1 WO2017076584 A1 WO 2017076584A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
stator
inner part
turbomachine
sta
Prior art date
Application number
PCT/EP2016/074284
Other languages
German (de)
English (en)
Inventor
Dieter Nass
Steffen Petri
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2017076584A1 publication Critical patent/WO2017076584A1/fr

Links

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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F04D29/40—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
    • F04D29/622—Adjusting the clearances between rotary and stationary parts
    • 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
    • F05D2260/00—Function
    • F05D2260/02—Transport and handling during maintenance and repair

Definitions

  • the invention relates to an inner part of a turbomachine for arrangement in an outer casing of the turbomachine, wherein the inner part for rotation in operation provided parts of a Ro ⁇ gate and formed as operating in operation parts of a stator, wherein the rotor extends along an axis.
  • the invention relates to a Turboma ⁇ machine with the inner part and a method for mounting the turbomachine.
  • Turbo compressor and method of the type defined above are already known from the patent application EP 2 045 472 AI.
  • the method described in this patent application for mounting the turbomachine provides that an inner part of the tur ⁇ bomaschine comprising the rotor and a stator is inserted as a fully assembled module axially in a circumferentially unge ⁇ divides outer housing.
  • the insertion opening into the cup-shaped outer housing, which can also be referred to as Topfge ⁇ housing is axially closed after reaching the end position of the inner part by means of a front-side cover.
  • the axial end faces of the outer housing or frontal cover are each provided with a passage opening through which one shaft end of the rotor is axially led out of the outer housing.
  • This shaft end can serve on the one hand for supporting the rotor and on the other hand for transmitting torques in front of or on the rotor of the turbomachine.
  • a shaft seal is usually provided for sealing the gap between the opening contour and the shaft surface of the rotor or rotor.
  • the shaft end is used on an axial side of the attachment of a so-called horsetail, which can also be referred to as an extension.
  • the horsetail is essentially an axial extension of the rotor at an axial shaft end.
  • This extension is used for the exhaust support of the inner part against the force of gravity in the Pha ⁇ se of the axial insertion into the pot-shaped outer housing, in which the inner part is a ⁇ is guided already partly in the outer housing, but the axial shaft end (without extension) containing the Introduces insertion movement, not yet protrudes from the axially frontal opening of the outer housing.
  • this extension which can be designed as a so-called horsetail (axially divisible), this vertically oriented load, so that the Inner housing largely without friction-increasing normal force acting on the outer housing can be inserted axially.
  • a disadvantage of the known method is that a special effort must be made to support the stator relative to the rotor of the inner part, so that it does not come to uncontrolled contacts and power transmissions between the rotor and the stator.
  • there is a large number of shaft seals in each turbomachine which can be designed, for example, as labyrinth seals. Regardless, it comes from the associated construction shaft seal type in the turbo engine in the area of the shaft seals usually most likely would be to Kunststoffetz- because the radial plays are performed at least there in the interests of the least possible Sekundärströ ⁇ regulations.
  • the ⁇ se precautions must for example be designed so that on the introduction of the leading side of the inner part these precautions can be removed by the axially frontal opening of the outer housing. This need may require special precautions on the outer housing, which can be costly to manufacture and expensive to install and handle.
  • the invention has set itself the task, the cost and effort in the context of the assembly for the purpose of supporting the stator relative to the rotor of the inner part of a turbomachine reduce machine and still not increase the risk of BeJedi ⁇ supply.
  • the inner part of a turbo-machine is a component which can generally include all parts of the rotor, but need not necessarily comprise.
  • the inner part comprises some standing parts surrounded by the rotor, which are referred to here as a stator.
  • a preferred application of the invention relates to turbomachines designed as radial machines, in which a radial deflection takes place between the individual stages of the rotor in the stator. This radial deflection takes place by ⁇ means of a circumferentially extending channel surrounding the rotor.
  • These deflections are collectively referred to as return stages and usually include so-called intermediate floors, which are at least formed in a dividing groove in the circumferential direction in a parting joint axially not teilba- ren.
  • shaft seal means in the accessory
  • shaft seal means the sealing of a gap between a rotor and a stator, not just one
  • the individual intermediate bottoms can be combined axially and radially by means of a shell divided over or in the circumferential direction axially over adjacent intermediate bottoms, so that the stator of the inner part forms a unit firmly joined together and attached to one another.
  • the individual intermediate floors may be fastened to one another in their part-joint plane by means of fastening elements and be combined axially relative to one another in another, if appropriate, manner.
  • the inner part has an at least provisionally firmly assembled stator, so that the inner part forms a transportable unit for itself.
  • the rotor is therefore arranged in the inner part form ⁇ conclusively, because the wheels (this document be ⁇ uses the terms “impeller” and “wheels” synonym both individually and in compound terms) of the rotor in the return stages of the stator an axially unlimited Prevent mobility.
  • the stator is axially movable from a first axial position to a second axial position relative to the stator.
  • a support shoulder extending in the circumferential direction is respectively provided on the stator and on the rotor radially concentrically opposite at two axially spaced locations, so that the rotor and the stator can be supported radially relative to one another by means of this support shoulder.
  • these support shoulders should be rotationally symmetrical, so that the support of the stator by means of the rotor relative to the weight of the stator is possible regardless of the circumferential position of the rotor.
  • the support shoulder also extends rotationally symmetrically in the circumferential direction in the stator, so that, for example, it is also possible to raise the entire inner part while attaching the stop means to the stator, so that the rotor can be raised indirectly via the stator of the inner part.
  • Impeller Here, the blades act on the wheel disc as stiffening ribs and prevent buckling of the wheel disc under the load.
  • the abutment shoulder can also be provided on a cover plate of the impeller, in which case the forces must be transmitted from the weight of the stator via Impellerschaufein between the wheel disc and the cover plate of the respective impeller. This must be taken into account when designing the blades.
  • the support shoulder is provided at each of the outermost radial end of the wheel disc or the cover plate, so that does not create a separate paragraph in example, the wheel disc additional axial space requirement.
  • the axial displaceability from the first axial position into the second axial position of the rotor relative to the stator of the inner part is expediently also made possible by an axially wider ge ⁇ stalteten wheel side space, so that the wheel disc in the context of the axial displacement in the extended width of
  • the wheel disk in the region of the Anla ⁇ trained rotationally symmetric - convex in cross-section - be formed so that it over a part of the circumference ge ⁇ insignificant force-related elastic deformations of Rad ⁇ disc or the stator in the region of the respective investment shoulder presupposed comes to a substantially linear edition.
  • line-shaped means that the extension of the support surface in the circumferential direction is longer than in the axial direction.
  • the abutment shoulder also rotationally symmetrical conical - in cross section obliquely to the axis or axis of rotation - each be formed, so that the two abutment shoulder surfaces are oriented parallel to zueinan ⁇ axially parallel alignment of the stator and the rotor.
  • the conical bevel should be here before ⁇ Trains t oriented such that the rotor relative to the stator at a contact pressure force is pressed perpendicularly to the axis in Rich ⁇ tung an axial stop of the slope of the cone, so that an uncontrolled sliding off of the system ⁇ shoulders together is excluded.
  • An advantageous development of the invention provides that the axial relative position of the stator and the rotor of the In ⁇ nenteils each other by means of at least one Befest Trentsele ⁇ mentes is fixable.
  • the axial Relative position on an axial side by means of a securing element in a boundary region between the stator and the rotor, which is accessible from the outside, is fixed to at least one circumferential position by means of the securing element.
  • the rotor or the shaft of the rotor of the fastening element can be radially ⁇ clamped, the fastener simultaneously contacted an axial reference surface of the stator, so that an axial movement at least unidirectional, preferably bidirectional nal between the rotor and the stator is blocked.
  • a complete backup of the axial position can also follow by means of two such fasteners.
  • the axial end faces of the outer housing or frontal cover are each provided with a passage opening, through which in each case a shaft end of the rotor can be axially guided out of the outer housing.
  • This shaft end can serve on the one hand for permanent or transitional mounting of the rotor and on the other hand for transmitting torques in front of or on the rotor of the turbomachine.
  • the inventive method provides that initially the outer housing is provided. Subsequently, an axi ⁇ ale extension in the sense of the aforementioned horsetail to the rotor at a shaft end is mounted rigidly so that the inner part raised by the extension - or intercepted in terms of weight - can be.
  • the inner part can be lifted to ⁇ at least on one axial side. It is not necessary that the entire inner part can be raised as a free end of this axial extension.
  • the connection between the extension and the shaft end must be rigid, so that the torques or bending moments arising from the transverse force can be transmitted to an axially spaced support of the extension.
  • the inner part is inserted by means of the exten ⁇ tion in the outer housing, wherein the rotor to the stator of the inner part befin- in the first axial det.
  • the axial extension or horsetail cites these insertion and ⁇ ser extension is axially supported outside by a front side axial hole of the outer housing, so that a normal force between the inner part and the outer housing currency ⁇ end of the insertion operation at least reduced becomes.
  • This axial displacement of the rotor relative to the stator can take place with the aid of the horsetail, wherein the stator of the inner part in the outer housing, the rotor is relieved of the weight and the rotor maneuvered without this additional load in the second axial position ⁇ who can.
  • Figure 1 shows a schematic longitudinal section through a turbomachine according to the invention during the axial insertion of the inner part in the
  • Figure 2 is a schematic representation of Aufla ⁇ shoulders between a rotor and a stator of an inner part in one
  • FIG. 3 shows a detail of FIG. 2, where it is labeled III,
  • FIG. 4 shows a detail from FIG. 2, in which the rotor is in a second axial position relative to the stator;
  • FIGS. 5 to 7 are each a schematic representation of
  • Steps of the method according to the invention rens for mounting a device according to the invention
  • Figure 1 shows part of a turbomachine TCO with an in ⁇ nenteil IP.
  • the inner part IP is mounted in Figure 1 by means of an axial extension EXT to a shaft end of the rotor RO SHE in an outer casing OC is ⁇ leads in the axial direction.
  • the inner part IP comprises parts of a rotor RO provided for rotation and elements of a stator STA which are designed as stationary parts during operation.
  • the inner part ⁇ IP is a transportable unit itself, which be ⁇ vorzugt at the point of commissioning the Turbomaschi ⁇ ne TCO with the outer casing OC is assembled.
  • the Au ⁇ tgepur OC is formed as an undivided in the circumferential direction so-called pot-shaped housing.
  • the outer housing front side is provided with an axial opening so that the inner part IP can be inserted axially into the technicallygePFu ⁇ se OC.
  • a lid is preferably COV axially on a shaft end SHE of ro tors RO slid and mounted there, so that this de ⁇ ckel COV posi ⁇ tioniert with the axial insertion of the inner part IP also for the purpose of attachment to the outer casing OC is.
  • the rotor RO comprises a shaft SH and a plurality of impellers IMP or impeller shrunk onto the shaft.
  • the stator STA comprises a plurality of impellers IMP formed between the individual impellers
  • Return stages BST each having a fluidic return channel, the radially outward of the Impeller IMP deflected flow of a process fluid back to radially inward deflected.
  • the return stages are equipped with aerodynamic guiding means, guide vanes for directing the flow of the process fluid.
  • the return stages BST which are also referred to as intermediate floors, provided with a parting line, the extends in a plane which is paral lel ⁇ substantially perpendicular to the axis X.
  • Return stages BST is also provided with a parting groove holder CR (this holder may also be referred to as an inner housing) is provided, which secures the return stages BST in the desired axial and radial position to each other.
  • this holder may also be referred to as an inner housing
  • the return stages BST are attached directly to each other, z-B. screwed together.
  • the individual stages of the turbomachine TCO are sealed to one another by means of at least one shaft seal SSL.
  • the shaft seal SSL seals Zvi ⁇ rule a cover disc of the impeller CW IMP and
  • the impeller IMP has, in addition to the cover plate on blades BL and a wheel HW. By means of the wheel disc HW, the impeller IMP is attached to the shaft SH of the rotor RO with a shaft-hub connection.
  • the Be ⁇ fastening secures the impeller IMP in the axial, radial and tangential (against rotation) direction.
  • the rotor RO is designed to be displaceable relative to the stator STA between a first axial position API and a second axial position AP2.
  • a corresponding Axi ⁇ alspielauslegung the shaft seals SSL is provided and the impeller side WSR which firmly located an axial clearance between the impellers and the stator STA IMP are axially formed corresponding ready.
  • the impeller side WSR which firmly located an axial clearance between the impellers and the stator STA IMP are axially formed corresponding ready.
  • the first axial position API are located at two axially spaced locations (ALI, AL2) each one in the circumferential direction CD kannre- ckende support shoulder SPS respectively to the stator STA and to the rotor RO each radially concentrically opposite, so that the rotor RO and the stator STA by means of the support ⁇ shoulders SPS are supported radially to each other.
  • FIG. 5 shows the provision of the outer housing OC.
  • FIG. 6 shows how, in the context of step b), an extension EXT has been attached axially to a shaft end SHE of the rotor RO of the inner part IP.
  • the inner part IP has already been partially inserted axially into the outer housing OC, wherein the axial extension EXT leads the insertion movement axially.
  • Step d) is shown schematically in FIG. 7, wherein FIGS. 3, 4 show in their detailed reproduction the radial abutment of the abutment shoulders SPS against each other in the first axial position API at the two axial points AL1, AL2.
  • Figure 7 also shows that the cover COV of the outer casing OC is brought together with the inner part IP axially into its final position before it is fixed to the outer housing by means of OC buildin ⁇ actuating elements.
  • the shaft end SHE which follows the axial movement is held by means of a support SUP ⁇ 'in the radial position.
  • the inner part can also be supported by the stator STA by means of a support SUP '. Because it becomes complex in heavier designs to absorb the torque from the weight force over the shaft, As a rule, the support via the inner part IP is then preferred.

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

Abstract

L'invention concerne un élément intérieur (IP) d'une turbomachine (TCO) destiné à être agencé dans un carter extérieur (OC) de la turbomachine (TCO), l'élément intérieur (IP) présentant des éléments d'un rotor (RO) conçus pour tourner pendant le fonctionnement et des éléments d'un stator (STA) réalisés en tant qu'éléments fixes pendant le fonctionnement, le rotor 5RO) s'étendant le long d'un axe (X). L'invention concerne également une turbomachine munie de l'élément intérieur et un procédé de montage de la turbomachine. L'invention vise à permettre un montage simplifié et sans risque d'endommagement. À cet effet, l'élément intérieur (IP) est réalisé de telle manière que le rotor (RO) peut se déplacer axialement par rapport au stator (STA) d'une première position axiale (API) à une seconde position axiale (AP2). Dans la première position axiale (API), des épaulements d'appui (SPS) s'étendant en direction périphérique (CD), opposés concentriquement et radialement, sont ménagés respectivement sur le stator (STA) et sur le rotor (RO) en au moins deux points espacés l'un de l'autre axialement, de sorte que le rotor (RO) et le stator (STA) peuvent être en appui radialement l'un par rapport à l'autre par l'intermédiaire des épaulements d'appui (SPS), les épaulements d'appui (SPS) étant configurés de telle manière que dans la seconde position axiale (AP2), les épaulements d'appui (SPS) du rotor (RO) et du stator (STA) ne sont pas radialement opposés.
PCT/EP2016/074284 2015-11-05 2016-10-11 Élément intérieur pour turbomachine, turbomachine et procédé de montage WO2017076584A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP15193213.4A EP3165772A1 (fr) 2015-11-05 2015-11-05 Partie interne pour une turbomachine, turbomachine et procédé de montage
EP15193213.4 2015-11-05

Publications (1)

Publication Number Publication Date
WO2017076584A1 true WO2017076584A1 (fr) 2017-05-11

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PCT/EP2016/074284 WO2017076584A1 (fr) 2015-11-05 2016-10-11 Élément intérieur pour turbomachine, turbomachine et procédé de montage

Country Status (2)

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EP (1) EP3165772A1 (fr)
WO (1) WO2017076584A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017223791A1 (de) 2017-12-27 2019-06-27 Siemens Aktiengesellschaft Wellendichtungsanordnung einer Turbomaschine, Turbomaschine
EP3514396A1 (fr) 2018-01-22 2019-07-24 Siemens Aktiengesellschaft Dispositif pourvu d'un rotor et de deux paliers

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3537587A1 (de) * 1985-10-31 1987-04-23 Proizv Ob Nevskij Z Im V I Radialverdichter
EP0257098A1 (fr) * 1986-02-20 1988-03-02 Proizvodstvennoe Obiedinenie 'nevsky Zavod' Imeni V.I.Lenina Compresseur centrifuge
EP2045472A1 (fr) 2007-10-05 2009-04-08 Siemens Aktiengesellschaft Procédé pour le montage de turbomachines et son dispositif de réalisation

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3537587A1 (de) * 1985-10-31 1987-04-23 Proizv Ob Nevskij Z Im V I Radialverdichter
EP0257098A1 (fr) * 1986-02-20 1988-03-02 Proizvodstvennoe Obiedinenie 'nevsky Zavod' Imeni V.I.Lenina Compresseur centrifuge
EP2045472A1 (fr) 2007-10-05 2009-04-08 Siemens Aktiengesellschaft Procédé pour le montage de turbomachines et son dispositif de réalisation

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017223791A1 (de) 2017-12-27 2019-06-27 Siemens Aktiengesellschaft Wellendichtungsanordnung einer Turbomaschine, Turbomaschine
EP3514396A1 (fr) 2018-01-22 2019-07-24 Siemens Aktiengesellschaft Dispositif pourvu d'un rotor et de deux paliers
WO2019141812A1 (fr) 2018-01-22 2019-07-25 Siemens Aktiengesellschaft Ensemble comprenant un rotor et deux paliers

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Publication number Publication date
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