• 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:
    Carter (10), in particular exhaust, for a turbomachine, comprising an inner hub (14) having an axis (A) of revolution and an outer annular ferrule (16) extending around the hub, said ferrule being configured to defining with the hub an annular flow vein of a gas flow and being rigidly connected to the hub by arms (20a, 20b), the hub comprising at a longitudinal end a scalloped annular flange having solid portions regularly distributed around said axis and spaced from each other by hollow portions, characterized in that the hub is made by welding assembly of several angular hub sectors which are arranged circumferentially end to end around said axis, each sector being connected to a hub sector adjacent by a longitudinal weld bead (30) which extends over substantially the entire axial extent of the hub and which is substantially axially aligned with a hollow portion of said flange.
    公开号:FR3051831A1
    申请号:FR1654734
    申请日:2016-05-26
    公开日:2017-12-01
    发明作者:Benoit Argemiro Matthieu Debray；Dominique Michel Fouquet；Gregory Ghosarossian-Prillieux；Guillaume Sevi；Patrick Sultana；Guy Vieillefond
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Turbomachine exhaust casing and its manufacturing process
    TECHNICAL AREA
    The present invention relates to a casing, in particular of exhaust, of an aircraft turbine engine, and to its method of manufacture.
    STATE OF THE ART
    In known manner, a turbomachine exhaust casing comprises an inner hub and an outer annular shell extending around the hub and an axis of revolution. The shell is configured to define with the hub an annular flow stream of a gas flow and is rigidly connected to the hub by substantially radial arms relative to the aforementioned axis.
    An exhaust casing is mounted downstream (with reference to the flow of gas in the turbomachine) of a turbine and the flow of gas through the exhaust casing is the flow of combustion gas leaving the turbine .
    A turbomachine may comprise other similar casings such as an intermediate casing. An intermediate casing is interposed between a low pressure compressor and a high pressure compressor of the turbomachine, and is therefore traversed by a flow of low pressure compressor gas and intended to supply the high pressure compressor.
    This type of housing may comprise at its longitudinal ends fastening flanges to other members of the turbomachine. The hub of the casing comprises for example at a longitudinal end a scalloped annular flange having solid portions regularly distributed around the axis of revolution and spaced apart from each other by hollow portions. In the case of an exhaust casing, this flange makes it possible to connect the casing to an ejection cone of the turbomachine situated downstream.
    In the present art, such a housing is manufactured by assembling several pieces. The hub is made in one piece and the arms and the shell, sectorized or not, are reported and fixed on the hub.
    The present invention proposes in particular an improvement in the manufacture of this type of housing.
    SUMMARY OF THE INVENTION To this end, the invention proposes a casing, in particular an exhaust casing, for a turbomachine, comprising an inner hub having an axis A of revolution and an outer annular shell extending around the hub, said ferrule being configured to define with the hub an annular flow vein of a gas flow and being rigidly connected to the hub by arms, the hub having at one longitudinal end a scalloped annular flange having solid portions regularly distributed about said axis and spaced apart from each other by hollow portions, characterized in that the hub is made by welding assembly of a plurality of angular hub sectors which are circumferentially disposed end to end about said axis, each sector being connected to an adjacent hub sector by a longitudinal weld bead which extends over substantially the entire axial extent of the hub and which is substantially axially aligned with a hollow portion of said flange. The invention proposes a new way of manufacturing a casing, particularly exhaust, not by means of an initially monobloc hub but a sectorized hub, that is to say formed by sector assembly. These hub sectors are welded, preferably by electron beam (FE), given the material thicknesses of the elements to be welded.
    By the geometry of the hub, during the assembly phase, the electron beam can be passed through several skins simultaneously - in the region of the aforementioned flange. The FE welding is then called "triple-skins", the beam can cross simultaneously three skins namely the flange, an annular stiffener of the hub and the ferrule.
    FE welding is capable of this but crossing multiple thicknesses requires more power and results in less stability in the weld quality achieved.
    The design of flanges, such as the aforementioned flange, must take into account several functional and mechanical dimensioning requirements, which results in thicknesses of material, a number of screws, a number and size of festoons or hollow parts, in accordance with cost and mass requirements.
    The proposed solution consists of the geometric optimization of the aforementioned flange to facilitate the hub welding procedure, in particular by limiting the number of skins crossed.
    For that, the thickness of the flange can be increased to allow, with iso-mechanical capacity, to widen and to deepen the festoons. The angular positioning of the festoons is optimized so that each weld zone between two hub sectors is aligned with a festoon. This zone thus becomes a "double-skin" (or "single-skin") welding zone if the electron beam does not need to pass through a stiffener, which makes it possible to better control the welding, in particular FE .
    The casing according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other: the hub sectors are made of foundry, the number of hub sectors is equal to number of casing arms, - each hub sector is initially formed in one piece with a radially inner portion of one of said arms, - the radially outer end of each of said arms is welded to the radially inner end of a radially outer portion of this arm, the radially inner portion of each arm is substantially located between two adjacent solid parts; two solid parts of the flange are thus located substantially on either side of the arm, which ensures a good load distribution, - the radially inner portion of each arm is substantially located between a first longitudinal plane passing through the axis A and one of the solid portions of said flange, and a second longitudinal plane passing through the axis and another adjacent of these solid parts, the radially inner portion of each arm is substantially located halfway between the two adjacent solid parts, each arm has a lower surface and an upper surface, each weld bead extending between the intrados of a first arm and the upper surface of a second adjacent arm and being located closer to the upper surface of the second arm than to the lower surface of the first arm, and - the hollow portions each comprise a substantially rectilinear median edge and tangential to a circumference centered on the axis A; the angular position of the festoons or hollow parts is thus optimized so that each weld zone between two hub sectors is covered by a festoon in its rectilinear part.
    The present invention also relates to a turbomachine comprising at least one housing as described above.
    The present invention also relates to a method of manufacturing a casing, in particular an exhaust casing, for a turbomachine, this casing comprising an inner hub and an outer annular shell extending around the hub and an axis A of revolution, said ferrule being configured to define with the hub an annular flow vein of a gas flow and being rigidly connected to the hub by arms, the hub having at one longitudinal end a scalloped annular flange having solid portions regularly distributed around said axis and spaced from each other by hollow portions, characterized in that it comprises a step of joining by welding a plurality of angular hub sectors which are arranged circumferentially end to end about said axis, each hub sector being connected to a adjacent hub sector by a longitudinal weld bead extending substantially to the axial extent of the hub and which is substantially axially aligned with a hollow portion of said flange.
    Preferably, the welding is performed by electron beam. The hub sectors may be made of foundry, and each comprise a flange sector.
    Advantageously, for producing each weld bead, the electron beam is inclined with respect to said axis, for example radially outwardly from a longitudinal end downstream to an upstream longitudinal end of the housing, and is moved in a plane substantially longitudinal passing through said axis and said cord to achieve without crossing the material of said flange.
    The hollow portions of the flange may be either pre-roughed before assembly of the hub, or machined after assembly. The part that will be remanufactured (material drop) can serve as a "cleat" welding.
    This solution improves the feasibility, stability and quality of the assembly process and therefore its cost (because less retouching necessary) and thus allows the overall integrated optimized design of the flange hub.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a schematic half-view in axial section of a downstream part of a turbomachine, and shows an exhaust casing; FIG. 2 is a diagrammatic perspective view of an exhaust casing, seen from the front since 3 is a diagrammatic perspective view of an exhaust casing according to the invention, and FIG. 3a shows in perspective the hub sectors that make up this casing, FIG. 4 is a partial schematic view. FIG. in axial section of an exhaust casing. FIGS. 5 and 6 are diagrammatic perspective views of the casing of FIG. 3, and shows a downstream flange of this casing, and FIG. 7 is a partial schematic perspective view of the exhaust casing of FIG.
    DETAILED DESCRIPTION
    Figures 1 and 2 show a housing 10, here exhaust, an aircraft engine.
    In a conventional manner, a turbomachine comprises a gas generator comprising, from upstream to downstream, in the flow direction of the gas flows, at least one compressor, a combustion chamber, and at least one turbine. Downstream of the turbine 12 is located the exhaust casing 10 which essentially comprises an inner hub 14 and an outer annular shell 16 which extends around the hub and an axis A of revolution which is the axis longitudinal axis of the turbomachine. In the present application, the terms "radial" and "radially" refer to the axis of revolution of the hub or housing.
    The ferrule 16 and the hub 14 together define an annular duct 18 for the flow of combustion gases leaving the turbine 12.
    The ferrule 16 and the hub 14 are rigidly connected to one another by arms 20 that are substantially radial with respect to the axis A. The arms 20 may be inclined with respect to planes passing through the axis A.
    The casing 10 comprises flanges 22 for attachment to other elements of the turbomachine. These attachment flanges 22 are located at the longitudinal ends upstream and downstream of the housing. In the example shown, the shell 16 comprises an annular flange 22a, 22b at each of its longitudinal ends upstream and downstream. The upstream flange 22a is attached to a downstream end of a casing of the turbine 12 and the downstream flange 22b is attached to an upstream end of an exhaust nozzle 24.
    The hub 14 comprises at its downstream longitudinal end an annular flange 22c for attachment to an upstream end of an exhaust cone 26 surrounded by the nozzle 24.
    The flange 22c is scalloped, that is to say that it comprises solid parts regularly distributed around the axis A and spaced from each other by hollow portions.
    In the prior art, the housing 10 is manufactured by connecting and fixing the ferrule 16 and the arms 18 on a hub 14 which is integral and made in one piece, generally foundry.
    FIG. 3 illustrates a principle of the invention consisting of manufacturing such a housing from a sectorized hub 14 and thus formed by the assembly of several hub sectors 14 'arranged circumferentially end to end and fixed to each other by welding, preferably by electron beam or FE welding.
    FIG. 3a shows hub sectors 14 'which each comprise a radially inner portion 20a of an arm. The number of sectors 14 'is here equal to the number of arms 20 and each hub sector 14' is associated with a radially inner portion 20a of an arm. The hub sector 14 'and the arm portion 20a are formed of a single casting. Radially outer portions 20b of the arms are then attached and fixed on the portions 20a, and the shell, sectorized or not, is also reported and fixed on the portions 20b. The fixing of the different parts of the housing can be achieved by welding, preferably FE.
    In the case of a FE welding and as shown in Figures 3 and 4, each hub sector 14 'is connected to an adjacent hub sector by a longitudinal weld bead 30 which extends over substantially the entire axial extent hub.
    For producing each weld bead, the electron beam is inclined with respect to the axis A, for example radially outwardly from a longitudinal end downstream to an upstream longitudinal end of the housing, and is moved in a plane substantially longitudinal passing through the axis and the cord to achieve and which corresponds to the plane of the sheet of the drawing of Figure 4.
    The reference 34 in FIG. 4 denotes the electron beam. It is oriented towards the zone to be welded, that is to say at the level of the junction zone between two longitudinal edges facing two adjacent hub sectors. The beam 34 passes here successively three skins or walls, namely the edges to be welded, an inner annular stiffener 32 of the hub, and the flange 22c. Indeed, the solid portions 22c1 of the flange 22c are located on the path of the beam and are therefore pass through the latter. This is not the case of the hollow parts 22c2. This particular case is naturally related to the angle of inclination of the electron beam vis-à-vis the axis A, but this angle can be imposed by the general shape of the housing.
    As mentioned in the foregoing, the FE welding is able to pass through several skins but this requires more power and results in less stability in the weld quality obtained. The invention overcomes this problem through the axial alignment of the weld bead 30 between two hub sectors 14 'with a hollow portion 22c2 of the scalloped flange 22c.
    Figures 5 to 7 illustrate the invention.
    It can be seen in these figures that the radially inner portion 20a of each arm 20 is substantially situated between a first longitudinal plane PI passing through the axis A and one of the solid portions 22c1 of the flange, and a second longitudinal plane P2 passing through the axis A and another adjacent 22c1 of these solid parts. The solid portions 22c1 are located midway from the portion 20a of the arm. In other words, the solid parts are placed symmetrically on either side of this portion of the arm.
    Each arm 20 has a lower surface 36 and an upper surface 37. Each weld bead 30 extends between the intrados of a first arm and the extrados of a second adjacent arm and is located closer to the upper surface of the second. arm than the lower surface of the first arm in the example shown.
    The hollow portions 22c2 of the flange 22c each comprise a median edge 38 substantially rectilinear and tangential to a circumference C1 centered on the axis A. The solid portions 22c1 also each comprise a substantially rectilinear median edge and tangential to a circumference C2 centered on the Axis A. These solid parts 22c1 are further pierced with orifices 40 for passing means of the screw-nut type.
    Figure 7 illustrates the passage of the electron beam 34 at the region of the flange 22c. It can be seen that, because of the axial alignment of the zone to be welded with a hollow portion 22c2 of the flange 22c, or even of the resizing of the flange, in particular in thickness and / or in radial dimension, the beam does not cross the flange 22c. The welding can thus be of the double skin type if the beam must pass through the stiffener 32, which is the case in the example shown.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A housing (10), in particular an exhaust, for a turbomachine, comprising an inner hub (14) having an axis (A) of revolution and an outer annular shell (16) extending around the hub, said ferrule being configured to define with the hub an annular duct (18) for flow of a gas stream and being rigidly connected to the hub by arms (20), the hub having at one longitudinal end a scalloped annular flange (22) having solid parts (22c1) regularly distributed around said axis and spaced from each other by hollow portions (22c2), characterized in that the hub is made by welding assembly of several angular hub sectors which are arranged circumferentially end to end around of said axis, each sector being connected to an adjacent hub sector by a longitudinal weld bead (30) which extends over substantially the entire axial extent of the hub and which is preferably aligned axially with a hollow portion of said flange.
    [2" id="c-fr-0002]
    2. Housing (10) according to the preceding claim, wherein the number of hub sectors (14 ') is equal to the number of arms (20) of the housing.
    [3" id="c-fr-0003]
    3. Carter (10) according to the preceding claim, wherein each hub sector (14 ') is initially formed in one piece with a radially inner portion (20a) of one of said arms.
    [4" id="c-fr-0004]
    4. Carter (10) according to the preceding claim, wherein the radially inner portion (20a) of each arm is substantially located between two adjacent solid parts.
    [5" id="c-fr-0005]
    5. Carter (10) according to one of the preceding claims, wherein each arm (20) has a lower surface (36) and an upper surface (37), each weld extending between the intrados of a first arm and the extrados of a second arm adjacent and being located closer to the upper surface of the second arm than the lower surface of the first arm.
    [6" id="c-fr-0006]
    6. Housing (10) according to one of the preceding claims, wherein the hollow portions (22c2) each comprise a median edge (38) substantially rectilinear and tangential to a circumference centered on the axis A.
    [7" id="c-fr-0007]
    7. Turbomachine, in particular an aircraft, comprising at least one housing according to one of the preceding claims.
    [8" id="c-fr-0008]
    8. A method of manufacturing a housing (10), in particular exhaust, for a turbomachine, this housing comprising an inner hub (14) and an outer annular shell (16) extending around the hub and a axis A of revolution, said ferrule being configured to define with the hub an annular duct (18) for flow of a gas flow and being rigidly connected to the hub by arms (20), the hub having at one longitudinal end a scalloped flange (22) having solid portions (22c1) uniformly distributed about said axis and spaced apart from each other by hollow portions (22c2), characterized in that it comprises a step of joining by welding several angular sectors of hub which are arranged circumferentially end to end about said axis, each hub sector being connected to an adjacent hub sector by a longitudinal weld bead which extends substantially t the entire axial extent of the hub and which is substantially axially aligned with a recessed portion of said flange.
    [9" id="c-fr-0009]
    9. Method according to the preceding claim, wherein the welding is performed by electron beam (34).
    [10" id="c-fr-0010]
    10. Method according to the preceding claim, wherein, for producing each weld bead (30), the electron beam (34) is inclined relative to said axis, for example radially outwardly from a downstream longitudinal end. towards an upstream longitudinal end of the housing, and is moved in a substantially longitudinal plane passing through said axis and said bead to be produced without passing through the material of said flange.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3463737B1|2020-07-01|Turbomachine exhaust casing and method of manufacturing the same
    EP2735706B1|2016-06-22|Vane diffuser of an axial turbomachine compressor and method for manufacturing same
    FR2930592A1|2009-10-30|TURBINE DISPENSER FOR A TURBOMACHINE
    CA2858797C|2020-03-10|Turbomachine compressor guide vanes assembly
    FR2972027A1|2012-08-31|ANNULAR TURBOMACHINE COMBUSTION CHAMBER COMPRISING IMPROVED DILUTION ORIFICES
    FR3056251A1|2018-03-23|REINFORCED EXHAUST CASE AND METHOD OF MANUFACTURE
    FR2943984A1|2010-10-08|Propeller for turbine engine e.g. open rotor type turbine engine, of aircraft, has hub comprising two annular type portions that are fixed to each other and defining part of recess opening
    EP3109406B1|2018-03-07|Axial turbomachine compressor casing
    EP3521569B1|2021-03-31|Structural casing for an axial turbine engine
    CA2831522A1|2012-10-11|Sealing ring for a turbine stage of an aircraft turbomachine, comprising slotted anti-rotation pegs
    FR3017928B1|2019-07-26|TURBOMACHINE WITH EXTERNAL FLANGE OF "SANDWICH" COMBUSTION CHAMBER
    EP3420198B1|2020-05-20|Flow-straightener for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction
    FR3051832B1|2019-09-06|PROCESS FOR MANUFACTURING A TURBOMACHINE EXHAUST CASE
    BE1026460B1|2020-02-06|STRUCTURAL HOUSING FOR AXIAL TURBOMACHINE
    EP2031255B1|2015-12-23|Vane, collar and assembly for synchronising ring stage of a compressor, turbomachine comprising such a compressor and method of assembly by welding between a collar and a vane.
    BE1026199B1|2019-11-12|EXTERIOR VIROLE IN TWO PARTS
    WO2021219949A1|2021-11-04|Intermediate flow-straightening casing with monobloc structural arm
    EP3350415B1|2019-07-17|Nozzle sector for a turbine engine with differentially cooled blades
    FR3037926A1|2016-12-30|TURBOMACHINE EXHAUST HOUSING WITH IMPROVED DESIGN
    EP3947919A1|2022-02-09|Dynamic seal for a turbomachine comprising a multi-layer abradable part
    CA3059196A1|2018-10-11|Reinforced axial diffuser
    FR3055145A1|2018-02-23|ANGULAR TURBOMACHINE STATOR VANE SECTOR
    FR3064297A1|2018-09-28|TURBINE FOR A TURBOMACHINE, SUCH AS A TURBOREACTOR
    同族专利:
    公开号 | 公开日
    FR3051831B1|2018-05-18|
    CN109070258B|2021-01-15|
    US11060418B2|2021-07-13|
    US20200326071A1|2020-10-15|
    CN109070258A|2018-12-21|
    EP3463737B1|2020-07-01|
    WO2017203126A1|2017-11-30|
    EP3463737A1|2019-04-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20060000077A1|2003-03-21|2006-01-05|Volvo Aero Corporation|A method of manufacturing a stator component|
    US20100111685A1|2007-03-30|2010-05-06|Volvo Aero Corporation| gas turbine engine component, a turbojet engine provided therewith, and an aircraft provided therewith|
    US20110262277A1|2008-12-18|2011-10-27|Volvo Aero Corporation|Gas turbine composite workpiece to be used in gas turbine engine|
    US20150204212A1|2012-06-15|2015-07-23|United Technologies Corporation|High durability turbine exhaust case|FR3095233A1|2019-04-16|2020-10-23|Safran Aircraft Engines|Exhaust casing of a turbomachine with improved aerodynamics|JPH0953410A|1995-08-16|1997-02-25|Toshiba Corp|Nozzle diaphragm|
    US20080105659A1|2006-11-02|2008-05-08|General Electric Company|High temperature electron beam welding|
    FR2992353B1|2012-06-21|2016-12-30|Snecma|ASSEMBLY OF AN EXHAUST CONE AND EXHAUST CASE IN A GAS TURBINE ENGINE|
    EP2808595B1|2013-05-27|2018-11-21|Safran Aero Boosters SA|Container and method for its manufacture|
    FR3010147B1|2013-08-28|2015-08-21|Snecma|ISOSTATICAL SUSPENSION OF A TURBOREACTOR BY DOUBLE REAR SUPPORT|
    WO2015068227A1|2013-11-06|2015-05-14|V¼¸V©þZgýV¼vWvÝWµ¡V¯±U¯ªXu´|Turbine blade and manufacturing method therefor|
    US9512740B2|2013-11-22|2016-12-06|Siemens Energy, Inc.|Industrial gas turbine exhaust system with area ruled exhaust path|FR3051832B1|2016-05-26|2019-09-06|Safran Aircraft Engines|PROCESS FOR MANUFACTURING A TURBOMACHINE EXHAUST CASE|
    CN112091393B|2020-09-16|2021-09-21|中国航发贵州黎阳航空动力有限公司|Assembly welding method and welding electrode for annular thin-wall sheet metal part of gas turbine|
    法律状态:
    2017-04-28| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-01| PLSC| Search report ready|Effective date: 20171201 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1654734A|FR3051831B1|2016-05-26|2016-05-26|TURBOMACHINE EXHAUST CASE AND METHOD FOR MANUFACTURING THE SAME|
    FR1654734|2016-05-26|FR1654734A| FR3051831B1|2016-05-26|2016-05-26|TURBOMACHINE EXHAUST CASE AND METHOD FOR MANUFACTURING THE SAME|
    US16/301,386| US11060418B2|2016-05-26|2017-05-15|Turbomachine exhaust casing and method for manufacturing same|
    PCT/FR2017/051167| WO2017203126A1|2016-05-26|2017-05-15|Turbomachine exhaust casing and method for manufacturing same|
    CN201780029267.5A| CN109070258B|2016-05-26|2017-05-15|Turbine exhaust casing and method of manufacturing the same|
    EP17752160.6A| EP3463737B1|2016-05-26|2017-05-15|Turbomachine exhaust casing and method of manufacturing the same|
    [返回顶部]