EP2846001A1 - Procédés de montage et de démontage d'un rotor d'une turbine à gaz, outil et turbine à gaz associés - Google Patents

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

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Publication number
EP2846001A1
EP2846001A1 EP13183274.3A EP13183274A EP2846001A1 EP 2846001 A1 EP2846001 A1 EP 2846001A1 EP 13183274 A EP13183274 A EP 13183274A EP 2846001 A1 EP2846001 A1 EP 2846001A1
Authority
EP
European Patent Office
Prior art keywords
rotor
sealing ring
housing
outer sealing
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.)
Granted
Application number
EP13183274.3A
Other languages
German (de)
English (en)
Other versions
EP2846001B1 (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 EP13183274.3A priority Critical patent/EP2846001B1/fr
Priority to ES13183274T priority patent/ES2935815T3/es
Priority to EP14150517.2A priority patent/EP2846002B1/fr
Priority to EP14150518.0A priority patent/EP2846003B1/fr
Priority to ES14150517T priority patent/ES2762511T3/es
Priority to ES14150518T priority patent/ES2752555T3/es
Priority to US14/477,492 priority patent/US10125627B2/en
Priority to US14/584,867 priority patent/US9822657B2/en
Priority to US14/584,811 priority patent/US9416676B2/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
    • 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
    • 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 disassembling a, in particular foremost, rotor of a gas turbine, a method for mounting such a rotor and a tool for fixing at least one further rotor in such assembly or disassembly and a gas turbine particularly suitable for this purpose.
  • a low-pressure gas turbine with a housing and a channel is known, in which several rotors are arranged in succession in order to extract energy from a gas.
  • the outer diameter of the channel and the successively arranged rotors increase in the direction of flow.
  • a first rotor with the smallest outer diameter is introduced against the direction of flow from the rear into the conical channel, then another rotor with a larger outer diameter, etc. to the rearmost rotor with the largest outer diameter.
  • all rear rotors have to be disassembled in the reverse order, firstly consuming, before finally the foremost rotor can be pulled backwards out of the conical channel.
  • the foremost rotor is usually exposed to the highest mechanical and / or thermal stresses, so it is most often disassembled 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 13 presents a tool for use in a device according to the invention Process under protection, claim 15 a particularly suitable for such a method gas turbine.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • One aspect of the present invention relates to a method for disassembling a rotor of a gas turbine. Another aspect relates to a gas turbine particularly suitable for this purpose. Accordingly, the following explanations apply equally to a method and / or a gas turbine according to an aspect or advantageous embodiments of the present invention.
  • the gas turbine may in particular be a low-pressure gas turbine or turbine stage, preferably 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 referred to as housing for short.
  • a contour, in particular a diameter, of the channel can expand in the direction of flow, in particular at least substantially monotonically and / or in steps.
  • one or more further rotors are arranged.
  • a guide grid can be arranged in the flow direction before and / or after one or more rotors, in particular between adjacent rotors.
  • the rotor to be disassembled is a first or foremost or upstream rotor in the direction of flow, or the rotor or rotors corresponding to the latter, or rotors which are more downstream. Accordingly, in the present case, an axial upstream position in the flow direction is referred to as the front position or the front, an axial position downstream in the flow direction corresponding to the rear position and the rear, respectively.
  • the rotor to be disassembled has, in one embodiment, one or more circumferentially distributed blades and a rotor disc.
  • the blades can be releasably, in particular form-fitting, preferably by means of profiled blade feet, or permanently, in particular materially secured, attached to the rotor disk, preferably integrally formed or as so-called BLISK together with the rotor disk.
  • the blades radially outwardly outer shrouds, which together form an outer ring, in another embodiment, the blades are outer dead band.
  • an outer contour, in particular an outer diameter, of the rotor blades, in particular of an outer ring of the rotor, widens in the direction of flow.
  • the outer ring may have one or more axially spaced radial flanges or sealing tips that extend radially outward.
  • an outer diameter of a front radial flange is smaller than an outer diameter of a rear radial flange.
  • a maximum outside diameter of the rotor to be disassembled lies in its rear half in the direction of flow.
  • an outer sealing ring is arranged between the rotor and the housing. Accordingly, in one embodiment, the outer sealing ring of a gas turbine according to one aspect of the present invention, in the flow direction, first or foremost or upstream offereddichtring.
  • the outer sealing ring may be releasably secured to the channel or housing.
  • a rear axial flow in the axial direction of the outer sealing ring may be suspended in a corresponding groove of the housing, which may be formed in a development by a fixed to the housing guide grid.
  • the outer sealing ring radially inward or facing the rotor has an inlet lining and / or a honeycomb seal.
  • an inner contour, in particular an inner diameter, of the outer sealing ring in the flow-through direction expands, in particular monotonously, preferably in one or more shoulders.
  • a shoulder of the inner surface of the assembled outer sealing ring is opposite to a radial flange of an outer ring of the rotor to be dismantled, a further shoulder being another radial flange of the outer ring.
  • a minimum, in particular foremost, inner diameter of the outer sealing ring is smaller than a maximum outer diameter of the rotor, in particular as a rearmost outer diameter of an outer ring, preferably as an outer diameter of a (rearmost) radial flange of the outer ring.
  • the rotor to be disassembled is disassembled or axially displaced, in particular forward toward the direction of flow, out of the housing.
  • the outer sealing ring whose - smaller - minimum inner diameter would come into conflict with its - larger - maximum outer diameter upon displacement of the rotor, moves axially counter to the throughflow direction, in particular out of the housing. Subsequently, the rotor itself can then be moved axially against the flow direction, in particular forward out of the housing.
  • the inspection and / or maintenance, in particular an exchange, of the rotor can be simplified.
  • the outer sealing ring If the maximum outer diameter of the outer sealing ring is smaller than the minimum (inner) diameter of the section of the channel in front of it in the direction of displacement, the outer sealing ring can easily be displaced axially out of the channel against the direction of flow. If, however, the minimum (Inside) diameter of the direction of displacement in front of him section of the channel is smaller, this is not. Therefore, according to one aspect of the present invention for disassembly, the outer seal whose maximum outer diameter is greater than a minimum (inner) diameter of the channel is circumferentially divided into two or more, preferably at least 16, more preferably at least 32 parts. Subsequently, the outer sealing ring parts can be displaced radially inwards or to a rotational axis of the gas turbine and in this way also past the smaller inner diameter of the channel.
  • outer sealing ring parts can also be displaced, at least in sections or partially, purely radially and / or purely axially.
  • the entire outer sealing ring or outer sealing ring parts can first be displaced by an axial path length in the direction opposite to the throughflow direction, for example until they block up through the channel. Subsequently, the outer sealing ring parts can be moved purely radially or radially inwards with superimposition of a further axial displacement, so that they can pass through the channel.
  • the outer sealing ring parts are also tilted in addition to an axial and / or radial displacement, in particular in order to release them from axial displacement from a circumferential groove of the housing.
  • the outer sealing ring parts can, on the other hand, be displaced axially and, if necessary, radially, at least essentially, without tilting, or do not have to be tilted in advance for axial displacement.
  • it can be provided that the outer sealing ring or the outer sealing ring parts are initially initially displaced axially without tilting.
  • the outer sealing ring on the housing is frictionally engaged, detachable and counter to the direction of flow attached form-fitting.
  • the outer sealing ring on the housing is releasably and frictionally mounted so that it can be displaced axially against the flow direction, in particular macroscopically or by at least 5 mm after loosening the frictional engagement, without that a radial shoulder of a Friction contact surface of the housing for frictional connection with the outer sealing ring opposite, in particular a wall of a circumferential groove.
  • the outer sealing ring can be attached to the housing in one embodiment by a one-part or multi-part strained so-called C-ring (“C-clip”) releasably and frictionally mounted or be.
  • the outer sealing ring on the housing In a flow direction, the outer sealing ring on the housing, however, be positively secured or fixed in a development, in particular by a one-sided paragraph, in the present case a circumferential groove in contrast to such a one-sided paragraph is referred to as two- or two-sided paragraph.
  • the outer sealing ring is secured or fixed in a form-fitting manner to the housing.
  • the outer sealing ring may have one or more radial projections which extend radially outwardly 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 at an in front in the flow direction End face of the housing can be arranged.
  • the housing may have one or more radial projections which extend radially inwardly from an inner peripheral surface of the housing for frictional engagement with a radially opposed outer peripheral surface of the outer sealing ring and engage corresponding axial grooves of the outer sealing ring, in particular at a rear end face in the flow direction the outer sealing ring can be arranged.
  • An extent of a radial projection in the circumferential direction may be smaller, 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 frictionally secured to each other in one embodiment and are not secured or fixed in the circumferential direction and / or in the flow direction, but not counter to the direction of flow, in particular not by means of a circumferential groove.
  • an initial tilting of the outer sealing ring or outer sealing ring parts can be avoided by initially displacing them axially against the direction of flow.
  • the rotor is first displaced axially or in the flow direction before or before the radial displacement of the outer sealing ring parts.
  • the outer sealing ring or outer sealing ring parts are initially displaced axially counter to the direction of flow without first having to displace or displace the rotor in the throughflow direction.
  • connection flange may in particular 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 for this purpose.
  • connection flange may also be part of a transport cover for closing the channel or the like.
  • a connection flange connected to the housing whose inner diameter facing the rotor is smaller than the maximum outer diameter of the outer sealing ring, detached from the housing.
  • a connecting flange without through-hole is referred to as a connecting flange, the inner diameter facing the rotor is equal to zero and thus smaller than the maximum outer diameter of the outer sealing ring.
  • a, in particular frictional, connection of the outer sealing ring with the housing, in particular a C-ring solved.
  • one or more further rotors of the gas turbine can be radially and / or axially supported or mounted via the rotor to be dismantled. In a disassembly of the rotor without prior disassembly of the other rotors eliminates this support or storage. Accordingly, in one embodiment, one or more further rotors of the gas turbine are otherwise fixed against the axial displacement of the rotor to be dismantled against the direction of flow. For this purpose, they can be fixed in particular by means of a detachable tool that is detachably, in particular frictionally and / or positively secured to at least one of the other rotors and in turn is supported. The tool can in particular, preferably frictionally and / or positively, be supported on the housing of the gas turbine.
  • one aspect of the present invention relates to a tool for fixing one or more further rotors in the 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 further rotors in the assembly or disassembly of a rotor of a gas turbine according to a method described here.
  • the tool has, in one embodiment, a fastening means for positive and / or frictional fastening to the housing and / or one or several other rotors of the gas turbine.
  • the fastening means may in particular have one or more recesses and / or projections for the positive fastening and / or one or more clamping means, in particular screws, for frictional fastening.
  • the tool includes a radial flange for attachment to the housing and an axial web for radially and internally engaging and attaching one or more other rotors.
  • One aspect of the present invention relates to the first or re-assembly of the rotor, in particular a frontmost rotor in the direction of flow from the front into the housing.
  • the assembly can essentially be carried out in the opposite way to the dismantling explained above, so that reference is additionally made to this.
  • the rotor to be mounted is displaced axially in the direction of flow, in particular into the housing, and then the outer sealing ring is axially displaced in the direction of flow, in particular into the housing.
  • parts of the outer sealing ring are displaced radially toward the housing of the gas turbine and then joined together to form the outer sealing ring, in particular clamped in the circumferential direction and / or connected in a form-fitting manner.
  • This radial displacement can also be superposed with an axial displacement of the entire outer sealing ring or the outer sealing ring parts, at least in sections or in phases.
  • the rotor is moved axially against the flow direction after the radial displacement of the outer sealing ring parts. As a result, temporarily movement space for the radial displacement can be created.
  • a connecting flange whose inner diameter facing the rotor is smaller than the maximum outer diameter of the outer sealing ring, with the housing, preferably releasably connected.
  • the outer sealing ring preferably releasably attached to the housing or a connection of the outer sealing ring to the housing can be closed.
  • a C-ring can be placed, the outer sealing ring and housing frictionally clamped.
  • 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 solved.
  • Fig. 1 shows a low-pressure gas turbine 1 with a housing 3 and a channel 5, in a flow direction (from left to right in Fig. 1 ) diverges by its diameter is substantially monotonously expanded in the direction of flow.
  • a front in the flow direction of the rotor 19 and a plurality of further, rear rotors 21, 23 and 25 are arranged one behind the other in the flow direction.
  • the housing At its front end (left in Fig. 1 ), the housing is releasably connected to a connection flange 9 of a low-pressure turbine 1 upstream high-pressure turbine, at its rear end (right in Fig. 1 ) with an outlet housing. 7
  • an outer sealing ring 27, 29, 31 and 33 is arranged between each rotor and the housing.
  • the dismantling rotor 19 has a plurality of circumferentially distributed blades, of which in Fig. 1 a partially shown, and a rotor disk (not shown) on which the blades are mounted.
  • Fig. 2A-C shows on the basis of an enlarged partial view steps of a method for disassembling a rotor of a gas turbine of an aircraft engine according to an embodiment of the present invention, which substantially the above explained Fig. 1 corresponds, so that corresponding elements are denoted by identical reference numerals and alternately referred to the rest of the description and will be discussed only differences.
  • the blades have on the outside radially outer shrouds, which together form an outer ring.
  • the outer diameter of this outer ring widens in the flow direction.
  • the outer ring has two axially spaced radial flanges or sealing tips 19a (cf. Fig. 2A ) which extend radially outward, wherein an outer diameter of a front radial flange (left in Fig. 2A ) is smaller than an outer diameter of a rear radial flange (right in FIG Fig. 2A ).
  • a rear axial flange (right in Fig. 2A ) of the outer sealing ring between the housing and a subsequent guide grid 13 mounted, a front axial flange (left in Fig. 2A ) of the outer sealing ring is fixed to the housing by means of a C-ring 45.
  • the outer sealing ring is frictionally and releasably attached to the housing against the flow direction without frictional locking: it can be seen, in particular with reference to the sequence of figures described below Fig. 2A ⁇ Fig. 2B in that, after loosening the C-ring, the outer sealing ring is axially opposite to the direction of flow (to the left in FIG Fig. 2A ) is displaceable without being hindered by a stop of the friction 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 (see. Fig. 2B ), which extend radially inward and in axial grooves in a rear direction of flow (right in Fig. 2 Engage the end face of the outer sealing ring, in order to secure or fix it in the circumferential direction and in the direction of flow in a form-fitting manner to the housing.
  • the outer sealing ring facing radially inward or facing the rotor, has an inlet lining 59 designed as a honeycomb seal.
  • the inner diameter of the outer sealing ring extends monotonously in the flow direction in several paragraphs, with a shoulder of the assembled outer sealing ring a radial flange (left in Fig. 2A ) of the outer ring of the rotor to be disassembled, a further shoulder of the mounted outer sealing ring another radial flange (right in Fig. 2A ) of the outer ring.
  • a minimum, foremost 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 as the outer diameter of its rearmost radial flange 19 a.
  • connection of the outer sealing ring 27 is released with the housing 3 in the form of the C-ring 45, as in Fig. 2B indicated by an arrow.
  • the outer sealing ring 27 is first displaced axially against the flow direction and then divided into two or more parts, which are then displaced radially inward or toward a rotational axis of the gas turbine and in this way are also guided past the smaller inner diameter of the channel, as in Fig. 2C indicated by arrows. This inward radial displacement is, as indicated by these arrows, superimposed on a further axial displacement of the outer sealing ring or its parts counter to the direction of flow.
  • the rotor 19 is then displaced axially outward against the direction of flow forward out of the housing 3 and so directly without Dismantling of the rear rotors 21, 23 and 25 dismantled. In this way, the inspection and / or maintenance, in particular an exchange, of the rotor can be simplified.
  • the tool has a radial flange 101 for attachment to the housing 3 and an axial web 102 and a fastening means 103, 104 - 106 for positive and / or frictional fastening to the housing 3 and the further rotors 21, 23 and 25.
  • the fastening means may 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 or re-assembly of the foremost rotor 19 in the direction of flow from the front into the housing 3 takes place substantially inversely to the dismantling explained above, so that reference is additionally made to this.
  • the rotor 19 to be mounted and then the outer sealing ring 27 are first displaced axially into the housing 3 in the throughflow direction.
  • the parts of the outer sealing ring are displaced radially to the housing of the gas turbine and then joined together to form the outer sealing ring, in particular clamped in the circumferential direction and / or positively connected (see. Fig. 2C in the reverse direction of the arrow).
  • This radial displacement is superposed with the axial displacement of the entire outer sealing ring or the outer sealing ring parts.
  • a last step cf. Fig. 2B ⁇ Fig.
  • FIG. 3 shows in Fig. 2 corresponding representation of a part of a gas turbine according to another embodiment of the present invention
  • Fig. 4 an enlarged detail of a Reibtrust Structure between outer ring and housing
  • Fig. 5 a section along the line VV in Fig. 4
  • Corresponding elements are designated by identical reference numerals, so that reference is made to the above description and will be discussed below only differences.
  • the extent of the radial projections 27.1 in the circumferential direction is greater than a distance in the circumferential direction between two circumferentially adjacent walls of two circumferentially adjacent axial grooves 3.2.
  • the term groove and projection includes no restriction of generality, since in some circumferentially distributed grooves and projections in each case 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)
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
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
ES13183274T ES2935815T3 (es) 2013-09-06 2013-09-06 (Des)montaje de un rotor de una turbina de gas, en particular delantero
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
ES14150517T ES2762511T3 (es) 2013-09-06 2014-01-09 Turbina de gas
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
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
US14/584,867 US9822657B2 (en) 2013-09-06 2014-12-29 Gas turbine
US14/584,811 US9416676B2 (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

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EP2846001A1 true EP2846001A1 (fr) 2015-03-11
EP2846001B1 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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US10370996B2 (en) 2016-08-23 2019-08-06 United Technologies Corporation Floating, non-contact seal with offset build clearance for load imbalance
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DE102016222608A1 (de) 2016-11-17 2018-05-17 MTU Aero Engines AG Dichtungsanordnung für eine Leitschaufelanordnung einer Gasturbine
JP6684698B2 (ja) * 2016-12-12 2020-04-22 三菱重工エンジン＆ターボチャージャ株式会社 ターボチャージャ
US20190218928A1 (en) * 2018-01-17 2019-07-18 United Technologies Corporation Blade outer air seal for gas turbine engine
CN108533333B (zh) * 2018-05-05 2023-10-13 宁波天生密封件有限公司 一种汽轮机插管密封装置及其使用方法
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine
FR3083563B1 (fr) * 2018-07-03 2020-07-24 Safran Aircraft Engines Module d'etancheite de turbomachine d'aeronef
FR3092861B1 (fr) * 2019-02-18 2023-02-10 Safran Aircraft Engines Ensemble de turbomachine comportant un taquet sur un jonc d'etancheite
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Also Published As

Publication number Publication date
US20150071769A1 (en) 2015-03-12
EP2846002A1 (fr) 2015-03-11
US11268398B2 (en) 2022-03-08
US20180347388A1 (en) 2018-12-06
EP2846001B1 (fr) 2023-01-11
ES2935815T3 (es) 2023-03-10
EP2846003A1 (fr) 2015-03-11
US9416676B2 (en) 2016-08-16
ES2752555T3 (es) 2020-04-06
EP2846002B1 (fr) 2019-11-20
US20150192026A1 (en) 2015-07-09
ES2762511T3 (es) 2020-05-25
US10125627B2 (en) 2018-11-13
USRE48320E1 (en) 2020-11-24
EP2846003B1 (fr) 2019-10-16
US20150192028A1 (en) 2015-07-09
US9822657B2 (en) 2017-11-21

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