• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Tool (31) for attaching an outer shroud (7) to an assembly (32) comprising at least one inner hub (12) and a plurality of blades (16), said tool (31) comprising: - a connection interface ( 35) with a lifting system; - an attachment interface (36) of said outer shroud (7), said attachment interface (36) comprising: • a bearing surface capable of coming to rest on a face of a flange of said outer shroud ( 7); • a centering surface adapted to be inserted into a hole of said flange; • at least one attachment element (41) capable of attaching said outer shroud (7); - Centering means (42) of said tool (31) with respect to said assembly (32) - Support means (43) of said tool (31) on said assembly (32); - adjustment means (44) of said bearing means (43) relative to said attachment interface (36).
    公开号:FR3069229A1
    申请号:FR1756892
    申请日:2017-07-20
    公开日:2019-01-25
    发明作者:Alain Meyer Julien；Jeremie Nunge
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    TOOL FOR FIXING AN EXTERNAL SHAFT OF AN INTERMEDIATE HOUSING OF A TURBOMACHINE
    TECHNICAL AREA
    The present invention relates in particular to a tool for fixing an external shell of an intermediate casing of a turbomachine and to a method of fixing said external shell.
    STATE OF THE ART
    A propulsion unit comprises a double-flow turbomachine integrated in an annular external casing.
    The turbomachine comprises for example from upstream to downstream in the direction of flow of the gases, a fan and a gas generator comprising one or more stages of compressor, low pressure and high pressure, a combustion chamber, one or more stages of turbine, high pressure then low pressure, and an exhaust nozzle.
    The external casing comprises in particular a fan casing and an external shroud of an intermediate casing flanged to each other.
    The intermediate casing is for example situated longitudinally between the low pressure compressor and the high pressure compressor. The intermediate casing includes an internal hub and an external ferrule extending around the internal hub and forming with the latter a portion of the secondary vein. The outer shell is connected to the inner hub by guide vanes (substantially radial with respect to the longitudinal axis of the turbomachine), better known by the acronym OGV for "Outlet Guide Vane", and distributed regularly.
    Each OGV blade comprises a blade with an aerodynamic profile, of elongated shape, delimited longitudinally by a leading edge disposed upstream in the direction of flow of the gases in the intermediate casing, and by a trailing edge opposite the leading edge. . The blade is further delimited radially between an internal platform and an external platform. The internal and external platforms are respectively mounted on the internal hub and the external ferrule of the intermediate casing.
    Traditionally, the outer shell of the intermediate casing is welded to an assembly comprising the inner hub on which OGV blades are mounted.
    To respect the desired geometric tolerances, upstream of the mounting of the outer shroud, it is known to machine external platforms of OGV vanes, called reference blades, mounted on the inner hub of the assembly.
    Such an assembly makes it possible to comply with the desired geometric tolerances, namely in particular the predetermined coaxiality tolerance between the outer shroud and the inner hub as well as the predetermined cylindricity tolerance associated with the outer shroud. Compliance with these tolerances is essential to guarantee the correct positioning of the fan casing, and consequently compliance with the radial clearances required between the fan and the fan casing.
    However, such an assembly is expensive and not very flexible. In addition, difficulties are encountered when an OGV dawn must be replaced following, for example, an impact with a foreign body (birds, hail, etc.).
    To overcome the aforementioned drawbacks and in particular the machining step, a variant consists in bolting the OGV vanes to the ferrules while wedging the external ferrule relative to the internal hub. Thus, shims of variable thicknesses are introduced between each external platform and the external shell.
    However, to set up such an alternative, it is necessary to have a tool for fixing the outer shroud, in particular making it possible to comply with the aforementioned desired geometric tolerances.
    The present invention therefore aims to provide a tool for fixing an outer shell of an intermediate casing making it possible to comply with the above-mentioned desired geometric tolerances.
    STATEMENT OF THE INVENTION
    To this end, the invention provides a tool for fixing an external shroud of an intermediate casing of a turbomachine to an assembly comprising at least one internal hub and a plurality of guide vanes for a secondary flow, each comprising a platform. internal shape fixed to said internal hub and an external platform capable of being fixed to said external shell, said tool comprising:
    - A connection interface with a lifting system, so as to allow the movement of said tool;
    - an attachment interface of said ferrule external to said tool, said attachment interface comprising:
    • a support surface capable of coming to bear on one face of a flange of said outer shell;
    • a centering surface capable of fitting into a hole in said flange of said outer shell;
    • at least one fastening element capable of reversibly attaching said ferrule external to said tool when said bearing surface is in abutment on said face of said flange and said centering surface is inserted into said hole;
    - means for centering said tool with respect to said assembly;
    - means for supporting said tool on said assembly;
    - Means for adjusting the position of said support means relative to said attachment interface.
    Such a tool makes it possible to comply with the desired geometric tolerances, namely in particular the predetermined coaxiality tolerance between the outer shroud and the inner hub as well as the predetermined cylindricity tolerance associated with the outer shroud.
    Compliance with these tolerances thus makes it possible to guarantee the correct positioning of the fan casing, and consequently compliance with the radial clearances required between the fan and the fan casing. Compliance with these tolerances also makes it possible to guarantee the correct positioning of the interfaces for fixing the coupling rods to the mast and the respect of the shapes located on the outer periphery of the outer shell (for example grooves).
    The tool according to the invention may include one or more of the following characteristics, taken in isolation from one another or in combination with each other:
    - said support surface and said centering surface are formed in a shouldered ring attached to a chassis of said tool;
    - Said fastening element comprises a fixed sole relative to said chassis and a movable jaw relative to said sole;
    - said support surface is annular plane and said centering surface is cylindrical;
    - said chassis comprises:
    • a crown on which said shouldered ring is attached;
    • at least three connecting elements defining said connecting interface, said connecting elements being opposite to said ring and being regularly distributed along a profile having a center of symmetry;
    - Said tool comprises four connecting elements distributed regularly according to a square profile;
    - said adjustment means comprise a linear actuator comprising a body fixed relative to said attachment interface and an internal member movable relative to said body, said support means being integral with said member;
    - Said centering means comprise a guide surface capable of coming to center said tool relative to said assembly;
    - Said guide surface is defined by said body of said actuator.
    The second object of the invention is a method of fixing an external shroud of an intermediate casing of a turbomachine to an assembly comprising at least one internal hub and a plurality of guide vanes for a secondary flow each comprising a internal platform fixed to said internal hub and an external platform capable of being fixed to said external shell, by means of a tool as described above, the method comprising:
    - A step of lifting said tool on which said outer shell is mounted;
    a step of centering said tool relative to said assembly;
    - A step of positioning said outer shell in a position for fixing to said assembly;
    - A step of wedging said outer shell relative to said assembly;
    - a step of fixing said ferrule external to said assembly;
    in which, during said stages of lifting, centering, positioning, wedging and fixing, a bearing surface of said tool is in abutment on a face of a flange of said outer shell, a centering surface of said tool is inserted into a hole in said flange of said outer shroud, and said outer shroud is held on said tool via at least one fastening element.
    DESCRIPTION OF THE FIGURES
    The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings in which:
    - Figure 1 is a longitudinal half-section view of a turbomachine comprising an intermediate casing;
    - Figure 2 is a detail view in longitudinal half-section of an outer shell of the intermediate casing of Figure 1;
    - Figures 3 to 6 are perspective views of a method of fixing the outer shell of the intermediate casing to an assembly being in a first mounting state;
    - Figure 7 is a perspective view of a method of fixing the outer shell of the intermediate casing to an assembly being in a second mounting state, and;
    - Figure 8 is a perspective view of a method of fixing the outer shell of the intermediate casing to an assembly located in a third mounting state.
    DETAILED DESCRIPTION
    In Figure 1 is shown a propulsion unit 1, in particular for aircraft, comprising a turbomachine with integrated double flow 2 in an annular external casing 3. The turbomachine 2 comprises from upstream to downstream in the gas flow direction, a fan 4 and a gas generator comprising one or more compressor stages, low pressure 5 and high pressure, a combustion chamber, one or more stages turbine, high pressure then low pressure, and an exhaust nozzle.
    The rotors of the turbomachine 2 are movable in rotation about a longitudinal axis X of the turbomachine 2.
    The external casing 3 comprises in particular a fan casing 6 and an external ferrule 7 of an intermediate casing 8 flanged to one another.
    By convention in the present application, the expression "longitudinally" or "longitudinal" means any direction parallel to the axis X, and by "radially >> or" radial >> any direction perpendicular to the axis X. Similarly, by convention in the present application, the terms "internal >> and" external >> are defined radially with respect to the axis X. Finally, the terms "upstream" and "downstream" are defined with respect to the direction of circulation gases in the propulsion unit 1.
    The air flow driven by the blower 4 is separated by a spout of an inter-vein structure 9 into a primary air flow entering the gas generator of the turbomachine 2 and a secondary air flow participating so predominant to the thrust supplied by the turbomachine 2. The secondary air flow flows around the gas generator in a secondary flow 10. The primary air flow flows in a primary flow 11.
    According to the embodiment illustrated in the figures and in particular Figure 1, the intermediate casing 8 is located longitudinally between the low pressure compressor 5 and the high pressure compressor.
    More specifically, the intermediate casing 8 comprises an internal hub 12 and an external ferrule 7 extending around the hub 12 and forming with the latter a portion of the secondary stream 10. The internal hub 12 further comprises an annular opening 14 defining a portion of the primary vein 11. The portion of the secondary vein 10 is radially separated from the portion of the primary vein 11 by an interveinous compartment 15 integrated in the inter-vein structure 9, the compartment 15 being for example intended for the passage of easements .
    The outer shroud 7 is connected to the inner hub 12 by guide vanes 16 (substantially radial relative to the longitudinal axis X of the turbomachine 2), better known by the acronym OGV for "Outlet Guide Vane", and distributed evenly around the axis X. Some of these OGV vanes 16 are configured to withstand external forces and form the framework of the intermediate casing 8, and are therefore called structural. It is noted that these structural vanes are more commonly called "arms".
    As illustrated in FIGS. 1 and 2, the intermediate casing 8 comprises an upstream flange 17 fixed to a downstream flange 18 of the fan casing 6 via a plurality of bolts distributed regularly around the axis X.
    Each OGV blade comprises a blade 19 with an aerodynamic profile, of elongated shape, delimited longitudinally by a leading edge disposed upstream in the direction of flow of the gases in the intermediate casing 8, and by a trailing edge opposite the edge d 'attack. The blade 19 is further delimited radially between an internal platform 20 and an external platform 21. The internal and external platforms 20, 21 are respectively fixed to the internal hub 12 and to the external ferrule 7 of the intermediate casing 8 via removable fastening elements 22 (here screws and / or bolts).
    According to the embodiment illustrated in the figures and in particular Figure 1, the portion of the inter-vein structure 9 located longitudinally upstream of the intermediate casing 8 supports in particular the stator 23 of the low pressure compressor 5. The blower 4 comprises a plurality of 'vanes 24 each comprising a blade with an aerodynamic profile delimited radially by a free external end facing the fan casing 6 and a foot fixed to a fan disc 25. The rotor 26 of the low pressure compressor 5 is fixed to the fan disc 25. The fan disc 25 is linked in rotation to a shaft 27 of a bearing 28, the base 29 of which is fixed to an annular flange 30 projecting from the internal hub 12.
    On one or more mounting stations, the outer shroud 7 of an intermediate casing 8 is fixed, via a tool 31, to an assembly 32, 33, 34 comprising at least the inner hub 12 and a plurality of OGV blades 16. The outer shroud 7 is mounted flat, and in other words the axis X is vertical and perpendicular to the ground of the mounting station (s).
    Tool 31 includes at least:
    - A connection interface 35 with a lifting system, so as to allow the movement of the tool 31;
    an attachment interface 36 of the outer shell 7 to the tool 31, the attachment interface 36 comprising:
    • a support surface 37 capable of coming to bear on an upstream face 38 of the upstream flange 17 of the outer shell 7;
    • a centering surface 39 capable of fitting into a hole 40 in the upstream flange 17 of the outer shell 7;
    • at least one attachment element 41 capable of reversibly attaching the outer shell 7 to the tool 31 when the bearing surface 37 is in abutment on the upstream face 38 of the upstream flange 17 and the centering surface 39 is inserted into hole 40;
    - centering means 42 of the tool 31 relative to the assembly 32, 33, 34;
    - Support means 43 of the tool 31 on the assembly 32, 33, 34;
    - means 44 for adjusting the position of the support means 43 relative to the attachment interface 36.
    According to the embodiment illustrated in the figures and in particular Figures 5, the bearing surface 37 of the attachment interface 36 is annular plane and the centering surface 39 is cylindrical, the bearing surface 37 is substantially perpendicular at the centering surface 39. The positioning of the outer ring 7 on the attachment interface 36 of the tool 31 (via the bearing surfaces 37 and centering 39) is then formed by a plane support connection and short centering (isostatic positioning).
    As illustrated in the figures, the bearing surface 37 and the centering surface 39 of the attachment interface 36 are formed in a shouldered ring 45 attached to a chassis 46 of the tool 31. The chassis 46 is welded. The chassis 46 comprises a lower ring 47 on which the shouldered ring 45 is attached and an upper plate 48 connected to the ring 47 via four uprights 49 distributed evenly. The crown 47 and the plate 48 are ribbed. The crown 47 is centered on the axis X when the external ferrule 7 is mounted on the attachment interface 36 of the tool 31.
    In general, to increase the stability of the tool 31, the connection interface 35 is defined by at least three connection elements 50 distributed regularly along a plane profile having a center of symmetry, namely a triangular, rectangular profile, rhombic, etc.
    According to the embodiment illustrated in the figures, the chassis 46 comprises four lifting hands 50 defining the connection interface 35 with the lifting system, each of the lifting hands 50 being mounted on an upright 49 at the upper plate 48 so as to form a square profile. The lifting hands 50 are able to be hooked by the lifting system.
    The lifting system, for example a winch, makes it possible to move the outer shroud 7 mounted on the tool 31 from a storage area to the assembly 32, 33, 34 on which the outer shroud 7 must be fixed. The lifting system is for example mounted movable in translation on the mounting station (s) by means of a suspension bridge. The lifting system comprises, for example, a windable cable (respectively unwindable) provided with a lifting hook.
    As illustrated in FIGS. 4 to 8, to move the tool 31, the lifting system comprises a sling comprising four strands 51 joined at one of their ends by means of a ring engaged in the hook lifting. Each strand 51 comprising a hook at its free end capable of being linked to a lifting hand 50 of the connection interface 35 of the tool 31.
    As illustrated in FIGS. 4 to 8, the attachment interface 36 comprises twelve attachment elements 41 distributed regularly. Each fastening element 41 comprises a sole 52 attached to the crown 47 of the chassis 46 and a jaw 53 movable relative to the sole 52. The jaw 53 is capable of coming into contact with a downstream face 54 of the upstream flange 17 opposite the upstream face 38 of the upstream flange 17. In order not to damage the downstream face 54 of the upstream flange 17, the jaw 53 is provided with a pad 55 (for example made of rubber). The jaw 53 is capable of being tightened manually via a handle.
    The adjustment means 44 comprise a linear actuator 56 comprising a body 57 fixed relative to the attachment interface 36 and an internal member 58 movable relative to the body 57, the support means 43 being integral with the member 58 .
    As illustrated in Figures 4 to 8, the body 57 is attached to a central base connected to the upper plate 48 via four arms 59 so as to form a cross. The linear actuator 56 is a linear screw actuator 56. The member 58 is movable in translation vertically (along the X axis). The member 58 of the actuator 56 is set in motion manually by the operator via a crank 60 placed at the level of the crown. The rotational movement generated by the crank 60 is transmitted to the actuator 56 by rods connected via cardan shafts and guided via bearings added to the chassis 46.
    As illustrated in FIGS. 4 to 8, the centering means 42 comprise a guide surface 61 capable of coming to center the tool 31 relative to the assembly 32, 33, 34. The guide surface 61 is defined by the body 57 of the actuator 56 and is cylindrical, the guide surface 61 being coaxial with the axis X.
    As illustrated in FIGS. 4 to 8, the support means 43 comprise a support surface 62 capable of coming to bear the tool 31 on the assembly 32, 33, 34. The support surface 62 is defined by the free end of the member 58 and is here in the form of a disc, the support surface 62 being substantially perpendicular to the axis X.
    The tool 31 is configured to allow the mounting of the outer shell 7 in different mounting states.
    According to a first mounting state illustrated in FIGS. 3 to 6, the assembly 32 comprises the internal hub 12, at least eight OGV blades 16 mounted on the internal hub 12 (advantageously all of the blades 16 mounted on the internal hub 12 ) and an adapter 63. The adapter 63 is removed after mounting the outer shroud 7 on the assembly 32.
    As illustrated in FIGS. 3 to 6, the adapter 63 comprises a sheath 64 and a seat 65. The seat 65 comprises a plate 66 for connection with the sheath 64 and a base 67 for connection with the flange 30 of the hub internal 12, the plate 66 and the base 67 being connected via three feet 68 distributed evenly around the axis X.
    More specifically, the sheath 64 is centered on X and comprises a bore configured to receive the guide surface 61 of the centering means 42. The plate 66 internally comprises a drilled hole (centered on the axis X) defining a shoulder configured to receive the support surface 62 of the support means 43. The base 67 is of annular shape, bearing on the flange 30 of the internal hub 12 and is centered relative to the latter (centered on X) via six centering pins 69.
    According to a second mounting state illustrated in FIG. 7, the assembly 33 comprises the internal hub 12, at least eight OGV blades 16 mounted on the internal hub 12 (advantageously all of the blades 16 mounted on the internal hub 12) and the bearing 28 for guiding the fan 4 and the rotor 26 of the low pressure compressor 5.
    According to a third mounting state illustrated in FIG. 8, the assembly 34 comprises the internal hub 12, at least eight OGV blades 16 mounted on the internal hub 12 (advantageously all of the blades 16 mounted on the internal hub 12), the bearing 28, the fan disc 25 and the rotor 26 of the low pressure compressor 5.
    The external shell 7 of the intermediate casing 8 is fixed to the assembly 32, 33, 34 comprising at least one internal hub 12 and a plurality of guide vanes 16 fixed to the internal hub 12, by means of tool 31, is produced according to a method comprising at least the following steps:
    - A step of lifting the tool 31 on which the outer shroud 7 is mounted;
    a step of centering said tool 31 relative to said assembly 32, 33, 34;
    - A step of positioning the outer shell 7 relative to the assembly 32, 33, 34 in a position for fixing to said assembly 32, 33, 34;
    - A step of wedging said outer shell 7 relative to said assembly 32, 33, 34;
    a step of fixing said external shell 7 to said assembly 32, 33, 34.
    During the lifting, centering, positioning, wedging and fixing steps, the bearing surface 37 of the attachment interface 36 is in abutment on the upstream face 38 of the upstream flange 17, the centering surface 39 of the attachment interface 36 is inserted into the hole 40 of the upstream flange 17, and the external ferrule 7 is held to the tool 31 via the attachment elements 41.
    According to the embodiment illustrated in the figures, during the lifting step, the outer shell 7 mounted on the attachment interface 36 of the tool 31 is notably lifted via the lifting system from its storage area.
    During the centering step, the guide surface 61 of the tool 31 (centering means 42) is notably inserted into a housing of the assembly 32, 33, 34 (here the bore of the adapter 63 or shaft 27 of the bearing) so as to center the tool 31 (and consequently the external ferrule
    7) relative to the assembly 32, 33, 34.
    During the positioning step, the support surface 62 of the tool 31 (support means 43) is notably supported on a stop of the assembly 32, 33, 34 (here the shoulder of the plate 66 or a stop 70 made in the shaft 27 of the bearing 28) so as to support the tool 31 on the assembly 32, 33, 34. Then, the vertical position of the tool 31 (and by way consequence of the outer shroud 7) is adjusted via the crank 60 actuated for example by an operator (under reverse to give slack at the level of the cable of the lifting system) so as to place the outer shroud 7 in a position for fixing to the assembly 32, 33, 34 (Figure 6).
    During the wedging step, shims of variable thicknesses (for example from 0.8 mm to 2.2 mm) are introduced between each external platform 21 and the external shell 7 so that the axis of the external shell 7 mounted is included in a theoretical cylindrical centered on the axis of the assembly 32, 33, 34 and having a predetermined diameter defined by a tolerance of coaxiality.
    During the fixing step, fixing elements 22 (here screws and / or bolts) are put in place so as to fix the external ferrule 7 to the assembly 32, 33, 34.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Tool (31) for fixing an external ferrule (7) of an intermediate casing (8) of a turbomachine (2) to an assembly (32, 33, 34) comprising at least one internal hub (12) and one plurality of guide vanes (16) of a secondary flow each comprising an internal platform fixed to said internal hub (12) and an external platform capable of being fixed to said external ferrule (7), said tool (31 ) including:
    - a connection interface (35) with a lifting system, so as to allow the displacement of said tool (31);
    - an attachment interface (36) of said external ferrule (7) to said tool (31), said attachment interface (36) comprising:
    • a support surface (37) capable of coming to bear on one face (38) of a flange (17) of said external ferrule (7);
    • a centering surface (39) able to be inserted in a hole (40) of said flange (17) of said external ferrule (7);
    • at least one attachment element (41) capable of reversibly attaching said external ferrule (7) to said tool (31) when said bearing surface (37) is in abutment on said face (38) of said flange ( 17) and said centering surface (39) is inserted into said hole (40);
    - centering means (42) of said tool (31) relative to said assembly (32, 33, 34);
    - support means (43) of said tool (31) on said assembly (32, 33, 34);
    - adjustment means (44) of the position of said support means (43) relative to said attachment interface (36).
    [2" id="c-fr-0002]
    2. Tool (31) according to claim 1, characterized in that said bearing surface (37) and said centering surface (39) are formed in a shouldered ring (45) attached to a frame (46) of said tool ( 31).
    [3" id="c-fr-0003]
    3. Tool (31) according to claim 2, characterized in that said attachment element (41) comprises a sole (52) fixed relative to said frame (46) and a jaw (53) movable relative to said sole ( 52).
    [4" id="c-fr-0004]
    4. Tool (31) according to one of the preceding claims, characterized in that said bearing surface (37) is annular plane and said centering surface (39) is cylindrical.
    [5" id="c-fr-0005]
    5. Tool (31) according to one of claims 2 to 3, characterized in that said chassis (46) comprises:
    - a crown (47) on which said shoulder ring (45) is attached;
    - At least three connection elements (50) defining said connection interface (35), said connection elements (50) being opposite to said ring (47) and being distributed regularly according to a profile having a center of symmetry.
    [6" id="c-fr-0006]
    6. Tool (31) according to claim 5, characterized in that said tool (31) comprises four connecting elements (50) regularly distributed along a square profile.
    [7" id="c-fr-0007]
    7. Tool (31) according to one of the preceding claims, characterized in that said adjustment means (44) comprise a linear actuator (56) comprising a body (57) fixed relative to said attachment interface (36) and an internal member (58) movable relative to said body (57), said support means (43) being integral with said member (58).
    [8" id="c-fr-0008]
    8. Tool (31) according to one of the preceding claims, characterized in that said centering means (42) comprise a guide surface (61) capable of coming to center said tool (31) relative to said assembly (32, 33 , 34).
    [9" id="c-fr-0009]
    9. Tool (31) according to claim 8 when it depends on claim 7, characterized in that said guide surface (61) is defined by said body (57) of said actuator (56).
    [10" id="c-fr-0010]
    10. Method for fixing an external shroud (7) of an intermediate casing (8) of a turbomachine (2) to an assembly (32, 33, 34) comprising at least one internal hub (12) and a plurality guide vanes (16) of a secondary flow each comprising an internal platform fixed to said internal hub (12) and an external platform capable of being fixed to said external ferrule (7), by means of a tool (31) according to one of claims 1 to 9, the method comprising:
    - A step of lifting said tool (31) on which is mounted said external ferrule (7);
    - a step of centering said tool (31) relative to said assembly (32, 33, 34);
    - a step of positioning said external ferrule (7) in a position for fixing to said assembly (32, 33, 34);
    - a step of wedging said outer shell (7) relative to said assembly (32, 33, 34);
    - a step of fixing said external ferrule (7) to said assembly (32, 33, 34);
    wherein, during said lifting, centering, positioning, wedging and fixing steps, a bearing surface (37) of said tool (31) is supported on one face (38) of a flange (17) from said outer shroud (7), a centering surface (39) of said tool (31) is inserted into a hole (40) of said flange (17) of said outer shroud (7), and said outer shroud (7) is maintained at said tool (31) via at least one fastening element (41).
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    同族专利:
    公开号 | 公开日
    US20200025040A1|2020-01-23|
    US20210115814A9|2021-04-22|
    FR3069229B1|2019-07-26|
    CN208759379U|2019-04-19|
    US11268407B2|2022-03-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20030147742A1|2002-02-01|2003-08-07|Thomas Erik C.|Gas turbine impeller alignment tool and method|
    DE102015214665A1|2015-07-31|2017-02-02|MTU Aero Engines AG|Flexible mounting device for the sequential and tension-free assembly of a component from individual modules|WO2020217003A1|2019-04-26|2020-10-29|Safran Aircraft Engines|Tool for removing a fan disc from a module|
    WO2020249399A1|2019-06-12|2020-12-17|Safran Aircraft Engines|Turbojet engine fan casing|US4562631A|1984-10-05|1986-01-07|Welch William R|Adjusting tool and means for adjusting the axial position of a tractor wheel and hub with respect to an axle|FR3076236B1|2017-12-28|2019-12-06|Safran Aircraft Engines|TOOL FOR DISASSEMBLING AN ANNULAR PART OF A TURBOMACHINE, METHOD FOR DISASSEMBLY AND ASSEMBLY THEREOF|
    US11261574B1|2018-06-20|2022-03-01|Emrgy Inc.|Cassette|
    法律状态:
    2019-01-25| PLSC| Publication of the preliminary search report|Effective date: 20190125 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 4 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1756892A|FR3069229B1|2017-07-20|2017-07-20|TOOL FOR ATTACHING AN EXTERNAL VIROLE OF AN INTERMEDIATE CARTER OF A TURBOMACHINE|
    FR1756892|2017-07-20|FR1756892A| FR3069229B1|2017-07-20|2017-07-20|TOOL FOR ATTACHING AN EXTERNAL VIROLE OF AN INTERMEDIATE CARTER OF A TURBOMACHINE|
    CN201821107408.9U| CN208759379U|2017-07-20|2018-07-13|For the outer collar of the intermediate casing of turbine to be fixed to the tool of unit|
    US16/037,964| US11268407B2|2017-07-20|2018-07-17|Tool for fixing an outer collar of an intermediate casing of a turbomachine|
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