EP2846001B1 - Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé - Google Patents

Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé Download PDF

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Publication number
EP2846001B1
EP2846001B1 EP13183274.3A EP13183274A EP2846001B1 EP 2846001 B1 EP2846001 B1 EP 2846001B1 EP 13183274 A EP13183274 A EP 13183274A EP 2846001 B1 EP2846001 B1 EP 2846001B1
Authority
EP
European Patent Office
Prior art keywords
rotor
sealing ring
outer sealing
housing
gas turbine
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.)
Active
Application number
EP13183274.3A
Other languages
German (de)
English (en)
Other versions
EP2846001A1 (fr
Inventor
Walter Gieg
Petra Kufner
Rudolf Stanka
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES13183274T priority Critical patent/ES2935815T3/es
Priority to EP13183274.3A priority patent/EP2846001B1/fr
Priority to EP14150517.2A priority patent/EP2846002B1/fr
Priority to ES14150518T priority patent/ES2752555T3/es
Priority to ES14150517T priority patent/ES2762511T3/es
Priority to EP14150518.0A priority patent/EP2846003B1/fr
Priority to US14/477,492 priority patent/US10125627B2/en
Priority to US14/584,811 priority patent/US9416676B2/en
Priority to US14/584,867 priority patent/US9822657B2/en
Publication of EP2846001A1 publication Critical patent/EP2846001A1/fr
Priority to US16/058,535 priority patent/US11268398B2/en
Priority to US16/191,706 priority patent/USRE48320E1/en
Application granted granted Critical
Publication of EP2846001B1 publication Critical patent/EP2846001B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/10—Basic functions
    • F05D2200/11—Sum
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
    • 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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making
    • Y10T29/49233—Repairing, converting, servicing or salvaging
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/53—Means to assemble or disassemble
    • Y10T29/53983—Work-supported apparatus

Definitions

  • the present invention relates to a method for dismantling a rotor, in particular the foremost rotor, of a gas turbine, a method for assembling such a rotor and a tool for fixing at least one further rotor during such assembly or disassembly.
  • a low-pressure gas turbine with a housing and a duct is known, in which a plurality of rotors are arranged one behind the other in order to extract energy from a gas.
  • the outer diameter of the channel and the rotors arranged one behind the other increase in the flow direction.
  • a foremost rotor with the smallest outer diameter is first inserted into the conical channel from the rear against the direction of flow, then another rotor with a larger outer diameter etc. up to the rearmost rotor with the largest outer diameter.
  • all rear rotors must first be dismantled in the reverse order, before the foremost rotor can finally be pulled backwards out of the conical channel.
  • the foremost rotor is usually subjected to the highest mechanical and/or thermal stresses, so it is most often dismantled for inspection and/or maintenance purposes.
  • An object of an embodiment of the present invention is to improve the inspection and/or maintenance of a gas turbine.
  • Claim 11 protects a tool for use in a method according to the invention.
  • Advantageous embodiments of the invention are the subject matter of the dependent claims.
  • One aspect of the present invention relates to a method for dismantling a rotor of a gas turbine.
  • the gas turbine can in particular be a low-pressure gas turbine or turbine stage, preferably of an aircraft engine, and have a housing and a channel in which the rotor is arranged and which diverges in a flow direction.
  • a housing part of a multi-part overall housing is also referred to as housing for short.
  • a contour, in particular a diameter, of the channel can widen in the direction of flow, in particular at least essentially monotonously and/or in steps.
  • a guide vane can be arranged in the direction of flow before and/or after one or more rotors, in particular between adjacent rotors.
  • the rotor to be dismantled is a first or frontmost or most upstream rotor in the direction of flow, and the further rotor or rotors are correspondingly rearward or more downstream rotors.
  • an axial position upstream in the direction of flow is referred to as a front position or front, and an axial position downstream in the direction of flow is referred to as a rear position or rear.
  • the rotor to be dismantled has one or more rotor blades distributed in the circumferential direction and a rotor disk.
  • the rotor blades can be detachably, in particular form-fittingly, preferably by means of profiled blade roots, or permanently, in particular materially, fastened to the rotor disk, preferably integrally or as so-called BLISK together with the rotor disk.
  • the rotor blades have outer shrouds radially on the outside, which together form an outer ring; in another embodiment, the rotor blades have no outer shroud.
  • an outer contour, in particular an outer diameter, of the moving blades of the rotor, in particular of an outer ring of the rotor, widens in the flow direction.
  • the outer ring can have one or more axially spaced radial flanges or sealing tips, which extend radially outwards.
  • an outside diameter of a front radial flange is smaller than an outside diameter of a rear radial flange.
  • a maximum outside diameter of the rotor to be dismantled is in its rear half in the flow direction.
  • An outer sealing ring is arranged between the rotor and the housing.
  • the outer sealing ring of a gas turbine is a first or frontmost or most upstream outer sealing ring in the direction of flow.
  • the outer sealing ring can be detachably attached to the channel or housing.
  • an axial flange of the outer sealing ring that is at the rear in the direction of flow can be hooked into a corresponding groove in the housing, which in a further development can be formed by a guide grid attached to the housing.
  • the outer sealing ring has a run-in coating and/or a honeycomb seal radially on the inside or facing the rotor.
  • an inner contour, in particular an inner diameter, of the outer sealing ring expands in the flow direction, in particular monotonically, preferably in one or more paragraphs.
  • a shoulder of the inner surface of the mounted outer sealing ring is opposite a radial flange of an outer ring of the rotor to be dismantled, and another shoulder is opposite a further radial flange of the outer ring.
  • a minimum, in particular frontmost, inner diameter of the outer sealing ring is smaller than a maximum outer diameter of the rotor, in particular than a rearmost outer diameter of an outer ring, preferably than an outer diameter of a (rearmost) radial flange of the outer ring.
  • the rotor to be dismantled is dismantled or axially displaced counter to the direction of flow, in particular forwards out of the housing.
  • the outer sealing ring whose - smaller - minimum inner diameter would come into conflict with its - larger - maximum outer diameter when the rotor is moved, is first moved axially counter to the direction of flow, in particular forwards out of the housing.
  • the rotor itself can then also be displaced axially counter to the direction of flow, in particular forward out of the housing.
  • a rotor in particular the foremost rotor, can be dismantled directly, in particular without dismantling rear rotors. In this way, inspection and/or maintenance, in particular replacement, of the rotor can be simplified.
  • the outer sealing ring can easily be displaced axially out of the channel counter to the direction of flow. If, on the other hand, the minimum (internal) diameter of the section of the channel in front of it in the displacement direction is smaller, this is not possible. Therefore, according to one aspect of the present Invention for dismantling first the outer sealing ring, the maximum outer diameter of which is greater than a minimum (inner) diameter of the channel, divided in the circumferential direction into two or more, preferably at least 16, in particular at least 32 parts. The outer sealing ring parts can then be shifted radially inwards or towards an axis of rotation of the gas turbine and in this way can also be guided past the smaller inner diameter of the channel.
  • outer sealing ring parts can also be displaced purely radially and/or purely axially, at least in sections or in part. For example, the entire outer sealing ring or parts of the outer sealing ring can first be displaced by an axial distance counter to the direction of flow, for example until the channel blocks it. The outer sealing ring parts can then be displaced radially inwards only, or with a further axial displacement superimposed, so that they can pass through the channel.
  • the outer sealing ring parts are also tilted in addition to being shifted axially and/or radially, in particular in order to release them from a circumferential groove of the housing before they are shifted axially.
  • the outer sealing ring parts can, at least essentially, be shifted axially and optionally radially without tilting or do not have to be tilted beforehand for the axial displacement.
  • it can be provided that the outer sealing ring or the outer sealing ring parts are initially displaced axially without tilting.
  • the outer sealing ring is fastened to the housing in a frictionally engaged, detachable manner and without a positive fit counter to the direction of flow.
  • this is understood in particular to mean that the outer sealing ring is fastened to the housing in a detachable and friction-locked manner is that it can be displaced axially, in particular macroscopically or by at least 5 mm, against the direction of flow after the frictional connection has been released, without this being opposed by a radial shoulder of a frictional contact surface of the housing for the frictional connection with the outer sealing ring, in particular a wall of a circumferential groove.
  • the outer sealing ring can be releasably and frictionally fastened to the housing by a one-part or multi-part braced so-called C-ring ("C-clip").
  • the outer sealing ring can be positively secured or fixed to the housing in a further development, in particular by a shoulder on one side, with a circumferential groove being referred to as a shoulder on two or both sides in contrast to such a shoulder on one side.
  • the outer sealing ring is secured or fixed in a form-fitting manner on the housing in the circumferential direction.
  • the outer sealing ring can have one or more radial projections, which extend radially outwards from an outer peripheral surface of the outer sealing ring for frictional engagement with a radially opposite inner peripheral surface of the housing and engage in corresponding axial grooves of the housing, which in particular on an in Flow direction front face of the housing can be arranged.
  • the housing can have one or more radial projections, which extend radially inward from an inner peripheral surface of the housing for frictional engagement with a radially opposite outer peripheral surface of the outer sealing ring and engage in corresponding axial grooves of the outer sealing ring, which in particular on a rear end face in the direction of flow of the outer sealing ring can be arranged.
  • An extent of a radial projection in the circumferential direction can be less than, equal to or greater than a distance in the circumferential direction between two circumferentially adjacent walls of two circumferentially adjacent grooves.
  • the outer sealing ring and the housing are fastened to one another with a friction fit, and not in a form-fitting manner, or only in the circumferential direction and/or in the direction of flow, but not against the Flow direction secured or fixed, in particular not by means of a circumferential groove.
  • an initial tilting of the outer sealing ring or parts of the outer sealing ring can be avoided by initially displacing them axially counter to the direction of flow.
  • the rotor to be dismantled in its assembly position can prevent a radial displacement of the outer sealing ring parts.
  • the rotor is initially or before the radial displacement of the outer sealing ring parts axially displaced in the direction of flow. In this way (additional) space can be made available for the radial displacement of the outer sealing ring parts radially inwards, possibly with superimposition of an axial displacement counter to the flow direction.
  • the housing can be connected to a connecting flange on its front face.
  • this connection flange can be part of a high-pressure turbine, which is upstream of a low-pressure turbine, part of an upstream combustion chamber or the like, or a connecting piece thereto.
  • the connection flange can also be part of a transport cover for closing the channel or the like.
  • a connecting flange connected to the housing and whose inner diameter facing the rotor is smaller than the maximum outer diameter of the outer sealing ring is detached from the housing.
  • a connection flange without a through opening is also referred to as a connection flange whose inner diameter facing the rotor is equal to zero and is therefore smaller than the maximum outer diameter of the outer sealing ring.
  • one or more further rotors of the gas turbine can be supported or mounted radially and/or axially via the rotor to be dismantled. If the rotor is dismantled without first dismantling the other rotors, this support or bearing is omitted. Accordingly, in one embodiment, one or more further rotors of the gas turbine are fixed in another way before the axial displacement of the rotor to be dismantled counter to the direction of flow. For this purpose, they can be fixed in particular by means of a detachable tool that is detachably attached to at least one of the other rotors, in particular frictionally and/or positively, and which in turn is supported. In particular, the tool can be supported on the housing of the gas turbine, preferably in a frictionally and/or form-fitting manner.
  • one aspect of the present invention relates to a tool for fixing one or more additional rotors during assembly or disassembly of a rotor of a gas turbine according to a method described here, in particular its use for fixing one or more additional rotors when assembling or disassembling a rotor of a gas turbine using a method described here.
  • the tool has a fastening means for positive and/or frictional fastening to the housing and/or one or more other rotors of the gas turbine.
  • the fastening means can in particular have one or more recesses and/or projections for positive fastening and/or one or more clamping means, in particular screws, for frictional fastening.
  • the tool has a radial flange for attachment to the housing and an axial web for reaching through one or more further rotors radially on the inside and being attached to them.
  • One aspect of the present invention relates to the initial assembly or reassembly of the rotor, in particular a foremost rotor in the flow direction from the front into the housing.
  • the assembly can be carried out essentially in reverse to the disassembly explained above, so that additional reference is made to this.
  • the rotor to be assembled is first displaced axially in the direction of flow, in particular into the housing, and then the outer sealing ring is displaced axially in the direction of flow, particularly into the housing.
  • parts of the outer sealing ring are shifted radially towards the housing of the gas turbine and then joined together to form the outer sealing ring, in particular braced in the circumferential direction and/or connected in a form-fitting manner.
  • This radial displacement can also be superimposed, at least in sections or phases, with an axial displacement of the entire outer sealing ring or the parts of the outer sealing ring.
  • the rotor After the radial displacement of the outer sealing ring parts, the rotor is displaced axially counter to the direction of flow. As a result, room for movement for the radial displacement can be created at times.
  • a connecting flange whose inner diameter facing the rotor is smaller than the maximum outer diameter of the outer sealing ring is connected to the housing, preferably detachably.
  • the outer sealing ring can be fastened, preferably detachably, to the housing or a connection of the outer sealing ring to the housing can be closed.
  • a C-ring can be fitted, which frictionally clamps the outer sealing ring and housing.
  • one or more further rotors can be fixed during assembly, in particular by means of a detachable tool and/or on the housing.
  • a corresponding fixation or the tool can be released.
  • FIG. 1 shows a low-pressure gas turbine 1 with a housing 3 and a duct 5, which runs in a flow direction (from left to right in 1 ) diverges in that its diameter increases essentially monotonically in the flow direction.
  • a rotor 19 which is at the front in the direction of flow and a plurality of further, rear rotors 21, 23 and 25 are arranged one behind the other in the direction of flow in the channel.
  • Guide vanes 11, 13, 15 and 17 are arranged between or in front of the rotors and are attached to the housing.
  • the housing On its front face (left in 1 ) the housing is detachably connected to a connecting flange 9 of a high-pressure turbine upstream of the low-pressure turbine 1, on its rear end face (on the right in 1 ) with an outlet housing 7.
  • An outer sealing ring 27, 29, 31 and 33 is arranged between each rotor and the housing.
  • the rotor 19 to be dismantled has a plurality of rotor blades distributed in the circumferential direction, of which 1 one shown partially, and a rotor disk (not shown) to which the blades are attached.
  • Figures 2A-C 1 shows steps of a method for dismantling a rotor of a gas turbine of an aircraft engine according to an embodiment of the present invention, essentially those explained above, on the basis of an enlarged partial illustration 1 corresponds, so that corresponding elements are denoted by identical reference symbols and reference is made alternately to the rest of the description and only differences are discussed.
  • the rotor blades have outer shrouds radially on the outside, which together form an outer ring.
  • the outer diameter of this outer ring increases in the flow direction.
  • the outer ring has two axially spaced radial flanges or sealing tips 19a (cf. Figure 2A ) extending radially outward with an outer diameter of a front radial flange (left in Figure 2A ) is smaller than an outer diameter of a rear radial flange (right in Figure 2A ).
  • a rear axial flange (right in Figure 2A ) of the outer sealing ring is hung between the housing and a subsequent guide vane 13, a front axial flange (on the left in Figure 2A ) of the outer seal ring is secured to the housing by means of a C-ring 45.
  • the outer sealing ring is fastened to the housing counter to the direction of flow, without a form fit, frictionally and detachably: this can be seen, in particular, from the sequence of figures described below Figure 2A ⁇ Figure 2B that the outer sealing ring after loosening the C-ring axially against the direction of flow (to the left in Figure 2A ) can be displaced without being prevented by a stop on the frictional contact surface between the outer sealing ring and the housing.
  • the inner peripheral surface of the housing 3 for frictional engagement with the radially opposite outer peripheral surface of the outer sealing ring 27 has a plurality of radial projections 3.1 (cf. Figure 2B ) which extend radially inwards and are inserted into axial grooves in a rear (right in 2 ) Engage the end face of the outer sealing ring in order to secure or define it in a form-fitting manner on the housing in the circumferential direction and in the direction of flow.
  • the outer sealing ring has a running-in coating 59 designed as a honeycomb seal radially on the inside or facing the rotor.
  • the inner diameter of the outer sealing ring increases monotonically in several steps in the direction of flow, with one step of the mounted outer sealing ring being attached to a radial flange (on the left in Figure 2A ) of the outer ring of the rotor to be dismantled, another shoulder of the assembled outer sealing ring is opposite another radial flange (on the right in Figure 2A ) of the outer ring.
  • a minimum front inner diameter d 27 of the outer sealing ring 27 is smaller than a maximum outer diameter D 19 of the rotor 19, in particular than the outer diameter of its rearmost radial flange 19a.
  • connection flange 9 connected to the housing 3 (cf. 1 ), whose inner diameter facing the rotor (right in 1 ) is smaller than the maximum outer diameter D 27 of the outer sealing ring (cf. Figure 2A ), detached from the housing 3.
  • the outer sealing ring 27 is first shifted axially against the direction of flow and then divided into two or more parts, which are then shifted radially inwards or towards an axis of rotation of the gas turbine and in this way are also guided past the smaller inner diameter of the channel. as in Figure 2C indicated by arrows. As indicated by these arrows, this radial inward displacement is superimposed by a further axial displacement of the outer sealing ring or its parts counter to the direction of flow.
  • the rotor 19 itself is then also pushed axially forwards out of the housing 3 counter to the direction of flow and is thus dismantled directly without dismantling the rear rotors 21 , 23 and 25 . In this way, inspection and/or maintenance, in particular replacement, of the rotor can be simplified.
  • the tool has a radial flange 101 for attachment to the housing 3 and an axial web 102 as well as attachment means 103, 104-106 for positive and/or frictional attachment to the housing 3 and the other rotors 21, 23 and 25.
  • the fastening means can in particular have one or more recesses and/or projections for positive fastening and/or one or more clamping means, in particular screws, for frictional fastening (not shown).
  • a first assembly or reassembly of the foremost rotor 19 in the direction of flow from the front into the housing 3 takes place essentially in reverse to the disassembly explained above, so that additional reference is made to this.
  • the outer sealing ring 27 is detachably fastened to the housing 3 by putting on the C-ring 45, the outer sealing ring and housing are frictionally clamped and the rotor 19 is shifted axially counter to the direction of flow (cf. Figure 2B with reverse arrow direction).
  • the tool 101-106 is then released and the connecting flange 9 is detachably connected to the housing 3.
  • FIG. 3 shows in 2 corresponding representation a part of a gas turbine, 4 an enlargement of a detail of a frictional contact surface between the outer ring and the housing, and figure 5 a section along the line VV in 4 .
  • Elements that correspond to one another are denoted by identical reference symbols, so that reference is made to the above description and only differences are discussed below.
  • the outer sealing ring 27 is fastened to the housing 3 counter to the direction of flow, without a form fit, frictionally and releasably by the C-ring 45: after loosening the C-ring, the outer sealing ring can be moved axially counter to the direction of flow (to the left in 3 ) can be moved without being prevented by a stop on the frictional contact surface between the outer sealing ring and the housing.
  • the outer peripheral surface of the outer sealing ring 27 has a plurality of radial projections 27.1 for frictional engagement with the radially opposite inner peripheral surface of the housing 3, which extend radially outwards and are inserted in axial grooves 3.2 in a front (left in Figures 3-5 ) Engage the end face of the housing in order to secure or set the outer sealing ring in a form-fitting manner on the housing in the circumferential direction and in the direction of flow.
  • the extent of the radial projections 27.1 in the circumferential direction is greater than a distance in the circumferential direction between two walls that are adjacent in the circumferential direction of two axial grooves 3.2 that are adjacent in the circumferential direction.
  • the designation groove and projection does not imply any restriction of generality, since in the case of a plurality of grooves and projections distributed in the circumferential direction, one or the other can be regarded as a groove or projection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Claims (11)

  1. Procédé permettant le démontage d'un rotor (19), en particulier le plus en avant, d'une turbine à gaz (1) comportant un carter (3) et un canal (5) divergeant dans un sens d'écoulement et dans lequel est disposé le rotor (19), comportant l'étape de :
    déplacement axial d'une bague d'étanchéité extérieure (27) radialement opposée au rotor (19) et dont le diamètre intérieur minimal (d27) est inférieur à un diamètre extérieur maximal (D19) du rotor (19) dans le sens contraire au sens d'écoulement ; et comportant l'étape suivante de :
    déplacement axial du rotor (19) dans le sens contraire au sens d'écoulement, en particulier hors du carter (3) ; caractérisé en ce que le rotor (19) est déplacé axialement dans le sens d'écoulement avant le déplacement radial des pièces de bague d'étanchéité extérieure.
  2. Procédé selon la revendication précédente, comportant les étapes de :
    division de la bague d'étanchéité extérieure (27) dont le diamètre extérieur maximal (D27) est supérieur à un diamètre minimal (ds) du canal (5) ; puis de déplacement radial des pièces de bague d'étanchéité extérieure vers un axe de rotation de la turbine à gaz (1).
  3. Procédé selon l'une des revendications précédentes, caractérisé en ce que, avant le déplacement axial de la bague d'étanchéité extérieure (27) dans le sens contraire au sens d'écoulement, une bride de raccordement (9) reliée au carter (3) et dont le diamètre intérieur faisant face au rotor (19) est inférieur au diamètre extérieur maximal (D27) de la bague d'étanchéité extérieure (27) est désolidarisée du carter (3).
  4. Procédé selon l'une des revendications précédentes, caractérisé en ce que, avant le déplacement axial de la bague d'étanchéité extérieure (27) dans le sens contraire au sens d'écoulement, une liaison de la bague d'étanchéité extérieure (27) avec le carter (3), en particulier une bague en C (45), est désolidarisée.
  5. Procédé selon l'une des revendications précédentes,
    caractérisé en ce qu'au moins un rotor supplémentaire (21, 23, 25) de la turbine à gaz (1) est fixé, en particulier au moyen d'un outil amovible (101-106) et/ou sur le carter (3).
  6. Procédé permettant le montage d'un rotor (19), en particulier le plus en avant, d'une turbine à gaz (1) comportant un carter (3) et un canal (5) divergeant dans un sens d'écoulement, comportant l'étape de :
    déplacement axial du rotor (19) dans le sens d'écoulement, en particulier dans le carter (3) ; et comportant l'étape suivante de :
    déplacement axial d'une bague d'étanchéité extérieure (27) opposée radialement au rotor (3) et dont le diamètre intérieur minimal (d27) est inférieur à un diamètre extérieur maximal (D19) du rotor (3) dans le sens d'écoulement, caractérisé en ce que le rotor (19) est déplacé axialement dans le sens opposé au sens d'écoulement après le déplacement radial des pièces de bague d'étanchéité extérieure.
  7. Procédé selon la revendication précédente, comportant les étapes de :
    déplacement radial de pièces de la bague d'étanchéité extérieure (27) vers le carter (3) de la turbine à gaz (1) ; puis de
    assemblage des pièces pour former la bague d'étanchéité extérieure (27), dont le diamètre extérieur maximal (D27) est supérieur à un diamètre minimal (ds) du canal (5).
  8. Procédé selon l'une des revendications 6 à 7, caractérisé en ce qu'après le déplacement axial de la bague d'étanchéité extérieure (27) dans le sens d'écoulement, une bride de raccordement (9), dont le diamètre intérieur faisant face au rotor (19) est inférieur au diamètre extérieur maximal (D27) de la bague d'étanchéité extérieure (17), est reliée au carter (3).
  9. Procédé selon la revendication 8, caractérisé en ce qu'après le déplacement axial de la bague d'étanchéité extérieure dans le sens d'écoulement, une liaison de la bague d'étanchéité extérieure avec le carter, en particulier une bague en C (45), est fermée.
  10. Procédé selon l'une des revendications précédentes 6 à 8,
    caractérisé en ce qu'une fixation, en particulier au moyen d'un outil amovible (101-106) et/ou sur le carter (3), d'au moins un rotor supplémentaire (21, 23, 25) de la turbine à gaz (1) est désolidarisée.
  11. Outil (101 -106) permettant de fixer au moins un rotor supplémentaire (21, 23, 25) lors du montage ou du démontage d'un rotor (19) d'une turbine à gaz (1) selon un procédé selon l'une des revendications précédentes, comportant un moyen de fixation (103-106) permettant la fixation par complémentarité de forme et/ou par friction au carter (3) et/ou à au moins un rotor supplémentaire (21, 23, 25) de la turbine à gaz (1), l'outil présentant une bride radiale pour la fixation au carter et une nervure axiale afin de venir en prise radialement à l'intérieur d'un ou de plusieurs rotors supplémentaires et d'être fixé à ceux-ci.
EP13183274.3A 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé Active EP2846001B1 (fr)

Priority Applications (11)

Application Number Priority Date Filing Date Title
ES13183274T ES2935815T3 (es) 2013-09-06 2013-09-06 (Des)montaje de un rotor de una turbina de gas, en particular delantero
EP13183274.3A EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
ES14150518T ES2752555T3 (es) 2013-09-06 2014-01-09 Turbina de gas, procedimiento de montaje y desmontaje correspondiente de una rejilla de rodete de una turbina de gas
ES14150517T ES2762511T3 (es) 2013-09-06 2014-01-09 Turbina de gas
EP14150518.0A EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz
EP14150517.2A EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz
US14/477,492 US10125627B2 (en) 2013-09-06 2014-09-04 Method for disassembly and assembly of a rotor of a gas turbine
US14/584,811 US9416676B2 (en) 2013-09-06 2014-12-29 Gas turbine
US14/584,867 US9822657B2 (en) 2013-09-06 2014-12-29 Gas turbine
US16/058,535 US11268398B2 (en) 2013-09-06 2018-08-08 Gas turbine with axially moveable outer sealing ring with respect to housing against a direction of flow in an assembled state
US16/191,706 USRE48320E1 (en) 2013-09-06 2018-11-15 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13183274.3A EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé

Publications (2)

Publication Number Publication Date
EP2846001A1 EP2846001A1 (fr) 2015-03-11
EP2846001B1 true EP2846001B1 (fr) 2023-01-11

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EP13183274.3A Active EP2846001B1 (fr) 2013-09-06 2013-09-06 Procédés de montage et de démontage d'un rotor d'une turbine à gaz, et outil associé
EP14150518.0A Active EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz
EP14150517.2A Active EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz

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EP14150518.0A Active EP2846003B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz, procédés de montage et de démontage associés d'un rotor d'une turbine à gaz
EP14150517.2A Active EP2846002B1 (fr) 2013-09-06 2014-01-09 Turbine à gaz

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US (5) US10125627B2 (fr)
EP (3) EP2846001B1 (fr)
ES (3) ES2935815T3 (fr)

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Also Published As

Publication number Publication date
US20180347388A1 (en) 2018-12-06
US9416676B2 (en) 2016-08-16
EP2846001A1 (fr) 2015-03-11
US11268398B2 (en) 2022-03-08
USRE48320E1 (en) 2020-11-24
EP2846002A1 (fr) 2015-03-11
ES2752555T3 (es) 2020-04-06
EP2846003A1 (fr) 2015-03-11
EP2846003B1 (fr) 2019-10-16
US20150192026A1 (en) 2015-07-09
ES2762511T3 (es) 2020-05-25
US9822657B2 (en) 2017-11-21
EP2846002B1 (fr) 2019-11-20
ES2935815T3 (es) 2023-03-10
US20150071769A1 (en) 2015-03-12
US20150192028A1 (en) 2015-07-09
US10125627B2 (en) 2018-11-13

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