EP3976320B1 - Outil pour maintenir l'arbre haute pression d'un mécanisme de propulsion d'avion - Google Patents

Outil pour maintenir l'arbre haute pression d'un mécanisme de propulsion d'avion Download PDF

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Publication number
EP3976320B1
EP3976320B1 EP20729011.5A EP20729011A EP3976320B1 EP 3976320 B1 EP3976320 B1 EP 3976320B1 EP 20729011 A EP20729011 A EP 20729011A EP 3976320 B1 EP3976320 B1 EP 3976320B1
Authority
EP
European Patent Office
Prior art keywords
end cap
shaft
shaft end
fastening
pressure
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
EP20729011.5A
Other languages
German (de)
English (en)
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EP3976320A1 (fr
Inventor
Jan SAßMANNSHAUSEN
Eugen Roppelt
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.)
Lufthansa Technik AG
Original Assignee
Lufthansa Technik 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.)
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Publication date
Application filed by Lufthansa Technik AG filed Critical Lufthansa Technik AG
Publication of EP3976320A1 publication Critical patent/EP3976320A1/fr
Application granted granted Critical
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
    • B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same
    • 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
    • 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
    • F05D2230/72—Maintenance
    • 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
    • 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
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/432—PTFE [PolyTetraFluorEthylene]

Definitions

  • the invention relates to a tool for holding and axially fixing the high-pressure shaft of an aircraft engine when the high-pressure turbine stage is dismantled, and its use.
  • the high-pressure shaft is mounted on one side in a non-rotating front bearing mount ("front bearing compartment") with a fixed bearing designed as a roller bearing, which is arranged in front of the high-pressure compressor module.
  • a fixed bearing designed as a roller bearing, which is arranged in front of the high-pressure compressor module.
  • another rolling bearing is provided as a floating bearing. If only the front bearing mount is removed - e.g. for maintenance purposes - the high-pressure shaft is secured axially solely by one on the high-pressure turbine module attached retainer. If only the high-pressure turbine module is removed, axial securing is provided solely by the fixed bearing of the front bearing mount.
  • the object of the present invention is to create a tool and a use of this tool with which the disadvantages of the prior art can be avoided or at least reduced.
  • the tool according to the invention it is possible to completely secure the high-pressure shaft of an aircraft engine in the axial direction when the high-pressure turbine stage is dismantled and at the same time to hold it in the radial direction via the spring element in such a way that the weight force acting on the high-pressure shaft when the high-pressure turbine stage is mounted can be simulated via the predetermined spring force .
  • the high-pressure shaft is therefore not completely fixed in the radial direction, but is only loaded with a spring force corresponding to the weight force mentioned, with which the shaft is held in the required, desired position on the one hand, but on the other hand no undesired stresses due to a fixed bearing at the rear end of the high-pressure shaft in these are entered.
  • the axial securing is achieved through the interaction of the shaft end cap receptacle, which prevents movement of the high-pressure shaft with the shaft end cap element fitted through the axial limitation in the first direction, in particular e.g. in the direction of the shaft end cap element, and a shaft connected to it, which with its fixing element causes an axial movement the high pressure wave relative to the shaft end cap receptacle opposite to the first direction (e.g., away from the shaft end cap member).
  • the high-pressure shaft can thus be completely fixed relative to the shaft end cap receptacle in the axial direction, while only a predetermined force is exerted in the radial direction, with the high-pressure shaft being at least slightly opposite each other in the radial direction of the shaft end cap mount can move, especially since there is no fixed bearing in this direction.
  • the desired mounting and axial fixing of the high-pressure shaft of an aircraft engine thus takes place with the fixing of the shaft end cap receptacle.
  • the spring element can be adjusted with regard to the spring force.
  • the spring force specified for a specific engine, a specific engine variant (ie one of several variants of an engine type) and/or a specific engine type can be set. It may also be possible, if necessary, to readjust the spring force when the tool is in the mounted state on an engine.
  • the fixing element on the shaft of the connector element can be designed for a non-positive connection with the inside of the hollow high-pressure shaft. However, it is preferably designed for a positive connection with the high-pressure shaft.
  • the fixing element can interact with undercuts that are regularly present in high-pressure shafts of an aircraft turbine due to an inner diameter that changes in the axial direction.
  • the fixing element can, for example, be a bolt arranged on the free end of the shaft to be inserted into the high-pressure shaft and extending around a latch on both sides of the shaft, which is preferably pivotable perpendicular to its longitudinal axis and/or to the axis of the shaft.
  • the fixing element In the pivoted state, the fixing element can be inserted into the hollow high-pressure axis, while in the non-pivoted state the latch extends maximally in the radial direction and can thus interact with a contact surface inside the hollow shaft.
  • An actuating device for example a cable pull, can be provided for actively pivoting the bolt.
  • the bolt has an asymmetrical weight distribution in relation to the shaft. In this case, simply by rotating the shaft, the bolt can be moved into a vertical orientation or an orientation pivoted relative to the shaft.
  • a fastening element is therefore preferably provided for stationary fastening of the tool on the aircraft engine when the high-pressure turbine stage is dismantled, with a fastening area for fastening the shaft end cap receptacle thereon.
  • the fastening element can be designed to fasten the tool to a flange of the combustion chamber.
  • the detachable attachment of the tool can be achieved with screws, for example.
  • the fastening element is preferably to be fastened in a predetermined position on the aircraft engine.
  • the attachment area can preferably be designed in such a way that the tool can actually only be attached to the engine in a single predetermined position. This can be achieved, for example, by adapting the fastening area and in particular the bores provided thereon for engaging screws with a precise fit to the fastening points provided on the engine.
  • the spring element at least is also arranged on the fastening element or fastened to it, a predetermined alignment of the spring element can be achieved by properly fastening the tool to the aircraft engine in order to be able to simulate weight forces, for example.
  • the abutment and/or contact surfaces of the shaft end cap element and/or the fixing element intended for contact with the high-pressure shaft are made of a material that is softer than the material of the high-pressure shaft, preferably plastic, more preferably PTFE. As a result, damage to the high-pressure shaft can be effectively prevented when using the tool according to the invention.
  • the high-pressure turbine of an aircraft engine is first dismantled.
  • the rear end of the high-pressure shaft protrudes from the engine.
  • the high-pressure shaft is still axially fixed by the fixed bearing of the high-pressure shaft, which is provided, for example, in a front bearing mount close to the high-pressure compressor.
  • the shaft end cap element is then first placed on the turbine-side end of the high-pressure shaft and the shank of the connector element with the fixing element is inserted into the high-pressure shaft.
  • the shaft end cap receptacle is then fitted around the shaft end cap element and connected to the shank of the connector element when the connection of the connector element to the high-pressure shaft has been completed by the fixing element, such that the parts of the tool according to the invention mounted on the high-pressure shaft are stationary in the axial direction in relation to the high-pressure shaft.
  • the high-pressure shaft can then be fixed in the axial direction with respect to the engine by suitably fastening the shaft end cap receptacle, a certain mobility in the radial direction being retained due to the mobility of the shaft end cap element and the shaft end cap receptacle.
  • a predetermined spring force can be exerted in the radial direction on the shaft end cap element and thus on the high-pressure shaft if required.
  • the attachment of the shaft end cap receptacle can preferably be achieved by a fastener as described above, which allows for fixed attachment to the engine itself.
  • the spring element is preferably not yet installed during the fastening of the shaft end cap receptacle, but is only attached later.
  • the fastening element is fastened to the engine, for example to the combustion chamber flange, using the means provided for this purpose in such a way that the fastening area of the fastening element is suitable for fastening the shaft end cap receptacle thereto is arranged.
  • the shaft end cap mount is then fastened to the fastening area, preferably in an axially and/or radially variable manner, i.e. the shaft end cap mount and the fastening area do not have a fixed, defined relative position to one another for fastening, but can be connected to one another so that they are displaced relative to one another in the axial and/or radial direction.
  • the connection or attachment can be force-locked.
  • a predetermined spring force can be applied to the shaft end cap element in the radial direction via the already mentioned spring element, in particular in order to simulate the weight of the high-pressure turbine otherwise acting on the high-pressure shaft.
  • the spring element can preferably be arranged on or connected to the fastening element.
  • FIG 1 a first exemplary embodiment of a tool 1 according to the invention is shown, with the individual components of the tool explained below being assembled.
  • FIG 2 the tool 1 is shown in the state of use
  • Figure 3d finally shows a section through the tool 1 in the state of use according to FIG figure 2 .
  • Figures 2 and 3 also show parts of an aircraft engine, namely the rear end of the high-pressure shaft 80 and the end region of the combustion chamber 81 with a peripheral flange 82.
  • the tool 1 comprises a shaft end cap element 2, the inside diameter of which is adapted to the diameter of the turbine-side end of the high-pressure shaft of an aircraft engine for which the tool 1 is intended.
  • the shaft end cap element 2 can be separated from the other components of the tool 1 and is designed in such a way that it can be plugged onto the end in question of the high-pressure shaft.
  • the shaft end cap element 2 is arranged in a shaft end cap receptacle 3, which limits or prevents a movement of the shaft end cap element 2 in the first direction indicated by the arrow 90, but at the same time allows a radial movement of the shaft end cap element 2 to a certain extent.
  • the inner radius of the shaft end cap receptacle 3, which is also cap-shaped in this embodiment, is larger than the outer radius of the shaft end cap element 2.
  • the fixing element 6 is here, as follows with reference to the figure 3 explained, for the form-fitting connection with the high-pressure shaft 80 as a pivotable about the axis 7, extending on both sides of the shaft 5 bolt 8 is formed, which has an asymmetric weight distribution compared to the shaft 5. Due to this asymmetrical weight distribution, in which the center of gravity of the bolt 8 is located in the vertical orientation, which can be changed depending on the rotation of the shaft 5, below or above the axis 7, the bolt 8 moves either into the in figure 1 shown position for axial fixation or in a position angled relative to the shaft 5, in which the connector element 4 can be inserted into a high-pressure shaft of an engine or removed again.
  • a guide element 5' made of soft plastic is also provided on the shaft 5, with which it is ensured that the shaft 5 itself does not come into contact with the inner wall of the high-pressure shaft 80 and can possibly cause damage there.
  • the shaft end cap receptacle 3 is attached to the attachment area 9 of an attachment element 10 .
  • the fastening area 9 is designed in the form of a sleeve or bushing and is attached to the outer diameter of the shaft end cap receptacle 3 adjusted so that it can be variably fastened not only axially in the fastening area 9, but also to a certain extent in the axial direction.
  • the shaft end cap receptacle 3 has a certain amount of play in relation to the fastening area 9 before it can be fixed in the desired axial and radial position by the screws 11 .
  • a spring element 12 is also arranged on the fastening element 10 and is stationary relative to the latter when the shaft end cap receptacle 3 has been fixed on the fastening element 10 .
  • the spring element 12 protrudes through the shaft end cap receptacle 3 and is designed to apply its spring force to the shaft end cap element 2 in the radial direction (cf. figure 3 ).
  • the spring element 12 can be adjusted via the adjusting screw 13 with regard to the spring force exerted on the shaft end cap element 2 .
  • the fastening element 2 has three brackets 14 for fastening to the flange 82 of the combustion chamber 81 of an aircraft engine (cf. figure 2 ) on.
  • the brackets 14 are arranged and designed in such a way that the fastening element 10 can only be fastened to the aircraft engine in a predetermined position. Due to this clear position in the assembled state, it can be ensured that the spring element 12 arranged on the fastening element 10 is aligned vertically in the assembled state and can simulate a weight force of a high-pressure turbine stage otherwise acting on the turbine-side end.
  • the shaft end cap element 2 and fixing element 6 components that come into direct contact with the high-pressure shaft when the tool 1 is used are made entirely of plastic or are at least provided with a plastic layer on the corresponding contact surfaces. Because plastic, such as
  • PTFE which is usually softer than the material of the high-pressure shaft, can effectively prevent any damage to the high-pressure shaft.
  • the shaft end cap element 2 is slipped onto this exposed end 84 of the high-pressure shaft 80 ( Figure 3b ). Due to its inner radius adapted to the diameter of the high-pressure shaft 80, the shaft-end cap element 2 sits securely on the high-pressure shaft 80, with the shape of the cap ensuring that the shaft-end cap element 2 actually remains on the turbine-side end 84 of the high-pressure shaft 80.
  • the shaft 5 is kept away from the inner wall of the high-pressure shaft 80 by the guide element 5 ′.
  • the shaft end cap receptacle 3 is fitted around the shaft end cap element 2 and the connection between the shaft 5 of the connector element 4 is established ( Figure 3d ).
  • the already assembled components 2-4 of the tool 1 can be fixed in the axial direction relative to the high-pressure shaft 80: an axial movement of the shaft end cap element 2 relative to the high-pressure shaft 80 is prevented by the correspondingly limiting shaft end cap mount 3, which is in turn fixed by the tension with the connector element 4 in the axial direction.
  • the fastening element 10 is mounted ( Figure 3e ).
  • the fastening element 10 is fastened via the cantilevers 14 in the only possible position on the rear flange 82 of the combustor 80, on which at least one high-pressure turbine stage is otherwise fastened.
  • the shaft end cap receptacle 3 lies within the fastening area 9 and can be finely positioned therein until it is fixed in the desired position by the screws 11.
  • the spring element 12 provided on the fastening element 10 can then be finely adjusted via the adjusting screw 13, so that a predetermined spring force is exerted on the shaft end cap element 2, which is still basically movable radially, which simulates the weight of the high-pressure turbine stage(s) otherwise mounted at this point.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gripping On Spindles (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)

Claims (12)

  1. Outil (1) pour le maintien et la fixation axiale de l'arbre haute pression creux (80) d'un moteur d'avion lorsque l'étage de turbine haute pression est démonté, comprenant
    - un élément de capuchon d'extrémité d'arbre (2) ayant un rayon intérieur adapté à un diamètre d'arbre prédéfini, pour l'enfichage sur l'extrémité côté turbine (84) de l'arbre haute pression (80), caractérisé en ce que l'outil comprend en outre
    - un logement de capuchon d'extrémité d'arbre (3) pour la réception mobile radialement et limitée axialement dans une première direction de l'élément de capuchon d'extrémité d'arbre (2), et
    - un élément de liaison (4) pouvant être fixé sur le logement de capuchon d'extrémité d'arbre (3) avec une tige (5) insérable dans l'arbre haute pression, comprenant un élément de fixation (6) pour le blocage axial du logement de capuchon d'extrémité d'arbre (3),
    un élément de ressort (12) fixe par rapport au logement de capuchon d'extrémité d'arbre (3) étant prévu pour appliquer une force de ressort prédéfinie sur l'élément de capuchon d'extrémité d'arbre (2) dans la direction radiale.
  2. Outil selon la revendication 1, caractérisé en ce que l'élément de ressort (12) est réglable en ce qui concerne la force de ressort.
  3. Outil selon l'une quelconque des revendications précédentes, caractérisé en ce que l'élément de fixation (6) est configuré pour la liaison par complémentarité de forme avec l'arbre haute pression (80).
  4. Outil selon l'une quelconque des revendications précédentes, caractérisé en ce que l'élément de fixation (6) est un verrou pivotant (8) s'étendant vers les deux côtés de la tige (5).
  5. Outil selon la revendication précédente, caractérisé en ce que le verrou (8) présente une répartition de poids asymétrique par rapport à la tige (5).
  6. Outil selon l'une quelconque des revendications précédentes, caractérisé en ce qu'un élément de fixation (10) est prévu pour la fixation fixe de l'outil (1) sur le moteur d'avion lorsque l'étage de turbine haute pression est démonté, avec une zone de fixation (9) pour la fixation du logement de capuchon d'extrémité d'arbre (3) sur celui-ci.
  7. Outil selon la revendication 6, caractérisé en ce que la zone de fixation (9) et/ou le logement de capuchon d'extrémité d'arbre (3) sont configurés pour fixer le logement de capuchon d'extrémité d'arbre (3) de manière variable axialement et/ou radialement par rapport à la zone de fixation (9).
  8. Outil selon la revendication 6 ou 7, caractérisé en ce que l'élément de fixation (10) est configuré pour la fixation à une bride (82) de la chambre de combustion (81) du moteur d'avion.
  9. Outil selon l'une quelconque des revendications 6 à 8, caractérisé en ce que l'élément de fixation (10) est conçu de manière à ne pouvoir être fixé au moteur d'avion que dans une seule position prédéfinie.
  10. Outil selon l'une quelconque des revendications précédentes, caractérisé en ce que les surfaces d'appui et/ou de contact de l'élément de capuchon d'extrémité d'arbre (2) et/ou de l'élément de fixation (6) prévues pour le contact avec l'arbre haute pression (80) sont en un matériau plus mou que le matériau de l'arbre haute pression (80), de préférence en matière plastique, de manière davantage préférée en PTFE.
  11. Utilisation d'un outil (1) selon l'une quelconque des revendications précédentes pour le maintien et la fixation axiale de l'arbre haute pression (80) d'un moteur d'avion, avec les étapes suivantes :
    a) le démontage du ou des étages de turbine haute pression du moteur d'avion ;
    b) l'enfichage de l'élément de capuchon d'extrémité d'arbre (2) sur l'extrémité côté turbine (84) de l'arbre haute pression (80) ;
    c) l'insertion de la tige (5) de l'élément de liaison (4) avec l'élément de fixation (6) dans l'arbre haute pression (80) ;
    caractérisée en ce que l'utilisation comprend en outre les étapes suivantes :
    d) la disposition du logement de capuchon d'extrémité d'arbre (3) autour de l'élément de capuchon d'extrémité d'arbre (2) ;
    e) la liaison de l'élément de liaison (4) au logement de capuchon d'extrémité d'arbre (3) de telle sorte que le logement de capuchon d'extrémité d'arbre (3) est fixé axialement par l'élément de fixation (6) de l'élément de liaison (4) ; et
    f) l'application d'une force de ressort sur l'élément de capuchon d'extrémité d'arbre (2) dans la direction radiale par l'élément de ressort (12) fixe par rapport au logement de capuchon d'extrémité d'arbre (3) .
  12. Utilisation selon la revendication 11, caractérisée en ce que, pour la fixation de l'outil (1) dans la direction axiale par rapport au moteur d'avion, un élément de fixation (10) pouvant être fixé au moteur d'avion avec une zone de fixation (9) pour la fixation du logement de capuchon d'extrémité d'arbre (3) sur celui-ci est prévu.
EP20729011.5A 2019-05-24 2020-05-22 Outil pour maintenir l'arbre haute pression d'un mécanisme de propulsion d'avion Active EP3976320B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019114029.3A DE102019114029A1 (de) 2019-05-24 2019-05-24 Werkzeug zur Halterung der Hochdruckwelle eines Flugzeugtriebwerks
PCT/EP2020/064253 WO2020239620A1 (fr) 2019-05-24 2020-05-22 Outil pour maintenir l'arbre haute pression d'un mécanisme de propulsion d'avion

Publications (2)

Publication Number Publication Date
EP3976320A1 EP3976320A1 (fr) 2022-04-06
EP3976320B1 true EP3976320B1 (fr) 2023-06-21

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EP20729011.5A Active EP3976320B1 (fr) 2019-05-24 2020-05-22 Outil pour maintenir l'arbre haute pression d'un mécanisme de propulsion d'avion

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Country Link
US (1) US11530624B2 (fr)
EP (1) EP3976320B1 (fr)
CN (1) CN113874169B (fr)
DE (1) DE102019114029A1 (fr)
ES (1) ES2950271T3 (fr)
WO (1) WO2020239620A1 (fr)

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Publication number Publication date
EP3976320A1 (fr) 2022-04-06
DE102019114029A1 (de) 2020-11-26
WO2020239620A1 (fr) 2020-12-03
US20220243619A1 (en) 2022-08-04
CN113874169B (zh) 2023-05-30
CN113874169A (zh) 2021-12-31
US11530624B2 (en) 2022-12-20
ES2950271T3 (es) 2023-10-06

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