• 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:
    The invention relates to an assembly for an aircraft turbojet engine, comprising a central gas ejection element (1) and a connecting flange (9) interposed between, upstream, a metal outlet (22a) of a turbojet engine and, downstream, the central element (1). The connecting flange comprises an annular part (9a) and flexible lugs (11) having axially: - a first end (11a) where the lug is connected to said annular part, and - a second free end (11b), projecting radial towards the outside with respect to the first end and towards which said tab is fixed with the central element (1).
    公开号:FR3084916A1
    申请号:FR1857457
    申请日:2018-08-10
    公开日:2020-02-14
    发明作者:Eric Conete；Benoit Carrere
    申请人:Safran Ceramics SA；
    IPC主号:
    专利说明:

    FLEXIBLE FIXING EJECTION CONE
    FIELD The present invention relates to an assembly located at the rear (downstream end) of an aircraft turbojet to optimize the flow of hot gases expelled by the turbojet, and possibly absorb at least some of the noise generated by [the interaction of these hot gases, coming from the internal engine parts (combustion chamber, turbine (s), with the ambient air and with the flow of cold air expelled by the fan of the turbojet engine.] [002] More specifically, the invention relates to the connection between what is often referred to as an "ejection cone" and, located just upstream, a gas outlet from the turbojet engine.
    Typically the ejection cone is completed (surrounded) by a part called "primary nozzle", these elements being commonly designated by the English words "plug" or "tail cone" for the ejection cone and " nozzle ”or“ primary nozzle ”for the nozzle.
    The "ejection cone" is intended to be positioned downstream of the (part) turbine of the turbojet, around which the primary nozzle is placed concentrically. The ejection cone and the primary nozzle are both fixed to a casing of the turbojet engine by a fixing system by flanges.
    [005] Thus is already known per se, an assembly for an aircraft turbojet engine, comprising:
    a central gas ejection element, annular around an axis (X) and adapted so that gas is ejected by the turbojet engine around it, from upstream to downstream, and
    - a connecting flange interposed between, upstream, a so-called metal outlet of a turbojet engine and, downstream, the central element, to connect them together.
    The aforementioned X axis is the longitudinal axis, or axis of rotation, of the turbomachine (in particular of the fan 20 and the moving blades of the engine 12).
    The central gas ejection element may correspond to the aforementioned ejection cone (referenced 1 below), or at least to the upstream part 1a below.
    A conventional ejection cone 1 is shown in Figure 1, in which the upstream (AM) and downstream (AV) of the structure along a motor axis (axis X above) are located respectively on the left and to the right of the figure.
    More generally, is illustrated in Figure 1, an aircraft gas turbojet engine 10 whose central part, forming the engine 12 to gas turbine (s), is mounted inside a set 14 of nacelle of engine, as is typical of an aircraft designed for subsonic operation. The nacelle assembly 14 generally comprises an engine nacelle (“core” in English) 16 and a blower nacelle 18 surrounding a blower 20 located axially upstream of the engine 12.
    Axially downstream, the motor 12 comprises at least one turbine (which may be a low pressure turbine) and, further downstream, an exhaust casing 22 comprising an internal annular ferrule 22a and an external annular ferrule 22b delimiting between them a downstream part of the primary stream 24 in which the combustion gases from the combustion chamber of the engine 12 circulate.
    Axially, the internal annular ferrule 22a is connected to the ejection cone 1, which may include an upstream part 1 a (commonly designated by the term "front plug"), of substantially cylindrical shape, and a downstream part 1b ( commonly referred to as "rear plug"), conical in shape.
    Connect (fix) together the aforementioned metal outlet of the turbojet, which can be said internal annular shell 22a, and said central element, which can be said upstream part 1a of the ejection cone 1, is difficult. In fact, as seen in FIG. 2, it can be complicated to fix together axially, at the level of a bulb 7, the aforementioned metal outlet of the turbojet engine, which can be said internal annular ferrule 22a and the central element (marked generally 3) which will be assimilated, in the embodiment of the invention which follows, to the ejection cone 1, the bulb 7 being a zone, swollen radially outwards, which the central element 3.
    [013] Problems can thus arise in particular:
    - management of the inlet diameter of the central element for the passage of flexible supports,
    - complicated fixing,
    - and inclined connections (not parallel to the X axis), in the bulb.
    One solution proposed for at least part of these problems consists in that the connecting flange comprises:
    - an annular part, and,
    - circumferentially, flexible legs individually, axially:
    a first end to which the tab is connected to said annular part, and
    - a second free end towards which said tab is fixed with the central element.
    This allows in particular to resume the differential expansions between said central element and said annular part which may respectively belong to, or define the metallic exhaust casing and the ejection cone which is not metallic.
    In this regard, it is further proposed that, radially, the flexible tabs extend radially outwardly relative to the first end and / or relative to openings formed in the annular part.
    [017] This makes it possible to offset the fixing zones radially and to combine flexibility and ease of assembly. [018] In addition, and in particular in this case, two possibilities have been more precisely defined:
    - First, it is proposed that a said tab can be connected to said annular part, at a said first end, by means of tongues extending downstream and which would be in one piece upstream with said annular part;
    - Then, it is proposed as an alternative that a said tab can be connected in one piece to said annular part, at the location of a part of said annular part forming a downstream edge of a said opening.
    In the second case, by cutting locally, at the location of an area, for example rectangular, the annular part on three sides and folding the cut part to form a so-called flexible tab, we will avoid adding weight and make it easy both to manufacture and to achieve the desired flexible fixing.
    In the first case, if such tabs are provided, integrated in a slot shape of said annular part, we will also limit the weight, having in fact reduced this annular part in another way.
    [021] In the text, connected to for a fixed direction with by mechanical means (screwing, welding in particular) or integrated with. If this creates a one-piece connection, this is specified.
    [022] Preferably, said annular part will be coaxial with said central element.
    [023] Preferably, the second free end of a said (of each said) tab will be located axially upstream of the first end of this tab. This could be important.
    Indeed, by ensuring flexibility downstream upstream in the fasteners via said flexible tabs, we will be able to move upstream, so towards the connecting flange, the fixing of the central element / ejection cone, this favoring a fixing zone located axially outside a said bulb and an acoustic treatment zone which could be provided.
    In this regard, it is also proposed that said central element precisely has a peripheral wall:
    - locally provided with an acoustic attenuation structure with cellular core, and
    - Having, upstream of the acoustic attenuation structure, an upstream end portion where the central element will be fixed with said flexible tabs at their said second free ends.
    [026] It may even be possible for the acoustic attenuation structure to extend axially to the right of said legs.
    [027] Thus, we could have fixed said central element, including a central element in CMC (ceramic matrix composite, as known per se), without impacting the acoustic treatment and without being located in the bulb aerodynamic profile. The connecting flange can then be metallic, without difficulty. And, all the more so, we will maximize the acoustic treated surface of the central element.
    [028] The above will preferably be carried out:
    - with a said upstream end portion for fixing the central element extending parallel to said axis (X) (thus avoiding the aforementioned inclined connections),
    - likewise for said legs towards their said second ends, so that these legs and said end portion upstream of the central element / ejection cone are fixed together by screws passing through them.
    [029] We can also usefully provide that the aforementioned peripheral wall is extended:
    - axially upstream, and
    - radially outside relative to said upstream end portion which it covers except at places with radial passages for said screws.
    With said flexible legs ensuring flexibility from downstream to upstream in the bindings, we will be able to:
    - gain in compactness,
    - therefore limit the mass of the solution compared to other flexible supports,
    - integrate, including with metal connecting flanges, architectures of central elements / ejection cones (CMC or metal) provided with acoustic treatments related to a gas stream (see the primary stream 24 above) equipped with upstream stiffeners and downstream.
    The invention may be, if necessary, better understood and other details, characteristics and advantages of the invention may appear on reading the following description given by way of nonlimiting example with reference to the accompanying drawings in which :
    BRIEF DESCRIPTION OF THE FIGURES
    - Figure 1 is a schematic sectional profile of a turbomachine for aircraft;
    - Figure 2 corresponds to the local view in frame II of Figure 1, in a version according to the invention;
    - Figure 3 is a perspective view of the connecting flange (9 below), in a first embodiment;
    - Figure 4 is an enlargement of the area marked IV Figure 3;
    - Figure 5 is an enlargement of the area marked V in Figure 2, according to a second embodiment; and
    - Figure 6 is the same view as Figure 4, but according to the second embodiment.
    DETAILED DESCRIPTION In FIG. 2, there is found, by reference with FIG. 1 and therefore on a turbojet engine 10, a set 2 of the engine tail 12, comprising a central element 1 for gas ejection (or cone of ejection) and a connecting flange 9 interposed between, upstream, a metal outlet of a turbojet (here the internal annular shell 22a of the exhaust casing) and, downstream, said central element 1, for connect together via the axial fixings 5. The central element 1 is made of a ceramic matrix and annular composite around the axis (X). It is suitable for gas to be ejected by the turbojet engine around it, from upstream to downstream; see arrow F figures 1,2.
    [033] According to the invention and as illustrated in FIGS. 2,3, the connecting flange 9 comprises an annular part 9a, coaxial with the central element 1 and, circumferentially, flexible lugs 11.
    [034] The flexible tabs 11 succeed one another circumferentially, in a regular manner, around the axis X, on the annular part 9a. The tabs 11 are presented as blades which can be substantially rectangular. For their flexible articulation relative to the annular part 9a, they have individually, axially:
    a first end 11a at (the place of) which the tab is connected in a single piece to said annular part 9a, and
    - a second free end 11b, projecting radially (axis Z) outwards relative to the first end 11a and to which the tab 11 is fixed with the central element 1.
    Each can therefore flex at the first end 11a. They define as many flexible supports.
    [036] The central element / ejection cone 1, hereinafter systematically called central element, is made of ceramic matrix composite and the connecting flange 9 is metallic. It can be a titanium alloy or any other alloy with high temperature resistance.
    [037] In particular so as not to fix the tabs 11 to the central element 1 in the treated area for acoustic attenuation (see details below; area 13) or in the bulb 7, the second free end 11b of a said ( each) flexible tab 11, where there is attachment with the central element 1, is located axially upstream (AM) of the first end 11a of this tab; see in particular figure 5.
    [038] In particular in this case, the central element 1 may have a peripheral wall 15:
    - locally provided with a structure 17 for acoustic attenuation with a cellular core, and
    - Having, upstream of the acoustic attenuation structure 17, an upstream end portion 19 where the central element 1 is fixed with said flexible tabs 11, at their second free ends 11 b.
    [039] Thus, the structure 17 of acoustic attenuation will be well confined downstream of the part 19 by which the fixing with the legs 11 will take place.
    To make the binding more reliable, the upstream end portion 19 will favorably form a circumferentially closed ring extending in a single piece the peripheral wall 15 upstream relative to the structure 17 of acoustic attenuation, like an axial. This annular rim 19 is traversed by holes 21 through which pass fixing screws 23 which also pass through other holes 25 which have the flexible tabs 11 towards their respective second free ends 11b.
    [041] In addition, to promote a large radial clearance and the establishment of the fasteners (such as the screws 23; see Figures 2.5), it may be preferred that, radially, the flexible tabs 11 extend by relative to openings, here cutouts, 18 formed in the annular part 9; see figures 3,4,6.
    [042] In practice, provision may be made for the central element 1 to comprise, as indicated with reference to FIG. 1, an upstream part 1a (commonly therefore designated "front plug"), of substantially cylindrical shape and, fixed to it axially (for example by bolting), a downstream part 1b (commonly therefore called "rear plug"), of conical shape. It would then be this upstream part 1a which would be equipped with at least one said structure 17 of acoustic attenuation, and therefore of the wall 15 and of the part 19.
    [043] With an orientation of the upstream end part 19 extending parallel to said axis X, likewise for the tabs 11 towards their second ends 11b, it is possible to fix together the upstream part 1a of the central element 1 and the flange of link 9 parallel to the X axis, thus avoiding oblique stresses.
    [044] Screws 23 passing radially through coaxial holes 21 25 will then be able to provide reliable and effective fixing without excessive stresses.
    [045] In particular for the installation and / or maintenance of these screws, it is also proposed that the peripheral wall 15 be extended, by a wall section 27:
    - axially upstream,
    - And radially outside with respect to said upstream end portion 19 that this wall section 27 will then cover, except at places with radial passages 29, for the screws 23; see figures 2.5.
    [046] It will also be noted in FIGS. 2 and 5 that, by means of said lugs 11 therefore ensuring flexibility from downstream to upstream in the fasteners, the structure 17 of acoustic attenuation may extend axially, in upstream end, to the right of the legsl 1.
    Figure 6 shows schematically an alternative to the solution of Figures 2.5. In fact, the annular part 9a, coaxial with the central element 1, is no longer, circumferentially, upstream and downstream of the legs 11 (parts respectively 9a1 and 9a2b in FIG. 4), but only upstream of these legs: part 9a1 Figure 6. From the annular part 9a1, extend axially axial tongues 31 between which are reserved said openings 18, here each in the form of sectored slots 18a. The solution of FIG. 5 is also thus constituted. The connection to said annular part 9a then takes place via the tongues 31. And it is at the free downstream end 31a (see FIG. 6) of each tongue 31 that said first is connected (for example welded) end 11a. The second free end 11b, still projecting radially (axis Z) towards the outside with respect to the first end 11a and towards which the tab 11 is fixed with the central element 1, is also located in the mount of said first end 11a . In this case, the tabs 11 are located circumferentially between two successive openings 18 and, radially opposite the respective tongues 31.
    [047] Figures 4 and 6, we can also see the radial flange through axial holes 35 of which axial fasteners 5 (see Figure 2), such as screws, used to fix the connecting flange 9 to said metal outlet of the turbojet engine, here the internal annular shell 22a of the exhaust casing 22.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. An assembly for an aircraft turbojet engine, the assembly comprising:
    - a central gas ejection element (1), annular around an axis (X) and adapted so that gas is ejected by the turbojet engine around it, from upstream to downstream, and
    - a connecting flange (9) interposed between, upstream, a metal outlet (22a) of a turbojet engine and, downstream, the central element (1), to connect them together, characterized in that the connecting flange (9) comprises an annular part (9a), and, circumferentially, flexible tabs (11) having, individually, axially:
    - a first end (11a) where the tab is connected to said annular part, and
    - a second free end (11b) to which said tab is fixed with the central element (1), the second free end (11b) being located axially upstream of the first end (11a).
    [2" id="c-fr-0002]
    2. Assembly according to one of the preceding claims, in which, radially, the flexible tabs (11) extend radially outwards relative to the first end and / or relative to openings (18,18a) of the connecting flange (9).
    [3" id="c-fr-0003]
    3. Assembly according to one of the preceding claims, in which the central element (1) has a peripheral wall (15):
    - locally provided with a structure (17) for acoustic attenuation with a cellular core, and
    - Having, upstream of the acoustic attenuation structure, an upstream end portion (19) where the central element (1) is fixed with said flexible tabs (11) at their said second free ends (11b).
    [4" id="c-fr-0004]
    4. The assembly of claim 3, wherein the upstream end portion (19) of the central element (1) extends parallel to said axis (X), as well as said flexible legs (11), towards their said second ends (11b), so as to be fixed together by screws (23) passing through them.
    [5" id="c-fr-0005]
    5. Assembly according to claim 4, in which the peripheral wall (15) extends axially upstream (at 27), and radially outside with respect to said upstream end part (19) which it covers except radial passage locations (29) for the screws (23).
    [6" id="c-fr-0006]
    6. Assembly according to one of claims 3 to 5, wherein the acoustic attenuation structure (17) extends axially up to the right of said tabs (11).
    [7" id="c-fr-0007]
    7. Assembly according to one of the preceding claims, in which the central element (1) is made of ceramic matrix composite and the connecting flange (9) is metallic.
    [8" id="c-fr-0008]
    8. Assembly according to one of the preceding claims, in which a said tab (11) is connected to said annular part (9a), at a said first end (11a), by means of tongues (31) extending downstream and monobloc upstream with said annular part (9a).
    [9" id="c-fr-0009]
    9. The assembly of claim 2 alone or in combination with one of claims 3 to 7, wherein a said tab (11) is connected in one piece to said annular part (9a), at the location of a part of said annular part forming a downstream edge (18a) of a said opening (18).
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3084916A1|2020-02-14|FLEXIBLE FIXING EJECTION CONE
    CA2594259C|2014-10-21|Cooling system for a centrifugal compressor impeller
    EP1881179B1|2018-08-15|System for ventilating the wall of a combustion chamber in a turbomachine
    EP1811131B1|2017-05-17|Set of fixed sectorised diffuser inserts for a turbomachine compressor
    EP0546935A1|1993-06-16|Stator guiding the inlet of air into a turbomachine and procedure for mounting a blade of this stator
    EP1873385B1|2009-08-12|Exhaust cone for channeling a gas stream downstream of a turbine
    EP2658779B1|2014-10-22|Device for suspending a turbojet engine
    WO2002086291A1|2002-10-31|Blade for a turbine comprising a cooling air deflector
    EP1881180B1|2018-01-03|System for ventilating a wall of a combustion chamber
    FR2926791A1|2009-07-31|AIR INLET FOR AIRCRAFT NACELLE, AND PROPULSIVE ASSEMBLY COMPRISING SUCH AN AIR INTAKE
    FR2976974A1|2012-12-28|DEVICE FOR ASSEMBLING ACOUSTIC PANELS OF A TURBOMACHINE NACELLE
    FR3068072A1|2018-12-28|ASSEMBLY FOR THE FLEXIBLE CONNECTION BETWEEN A TURBINE HOUSING AND AN ANNULAR TURBOMACHINE ELEMENT
    WO2015049468A1|2015-04-09|Turbomachine combustion chamber provided with air deflection means for reducing the wake created by an ignition plug
    EP3325788B1|2019-08-28|Aircraft gas turbine engine exhaust casing with increased lifespan
    FR3030627A1|2016-06-24|SERVITUDE PASSAGE SYSTEM FOR TURBOMACHINE
    WO2019197743A1|2019-10-17|Cooling device for a turbine of a turbine engine
    WO2021044099A1|2021-03-11|Ejection cone having a flexible aerodynamic attachment
    FR3073581B1|2019-11-22|DEVICE FOR MAINTAINING A CENTRAL RADIAL RADIAL AIR COLLECTION DEVICE
    FR3074151B1|2019-11-22|DEVICE FOR LIFTING AND TRANSPORTING A PROPULSIVE ASSEMBLY OF AN AIRCRAFT
    FR3089544A1|2020-06-12|COOLING DEVICE FOR A TURBOMACHINE HOUSING
    WO2021048323A1|2021-03-18|Exterior nozzle member for a turbomachine
    EP3344879A1|2018-07-11|Dimensioning of the skeleton angle of the trailing edge of the arms crossing the bypass flow of a turbofan
    同族专利:
    公开号 | 公开日
    WO2020030858A9|2020-11-26|
    FR3084916B1|2020-07-17|
    US20210293201A1|2021-09-23|
    EP3833861A1|2021-06-16|
    CN112543843A|2021-03-23|
    WO2020030858A1|2020-02-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0316233A1|1987-11-12|1989-05-17|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Assembly method for two parts having different thermal expansion coefficients|
    US20110203255A1|2008-09-08|2011-08-25|Snecma Propulsion Solide|Flexible abutment links for attaching a part made of cmc|
    US20140158458A1|2011-08-12|2014-06-12|Aircelle|Exhaust cone for aircraft turbojet engine|
    FR3113094A1|2020-07-31|2022-02-04|Safran Ceramics|Connecting device comprising a sliding pivot type connection for connecting an exhaust casing and an exhaust gas ejection cone of an aircraft turbojet engine|
    CN112318090B|2020-10-28|2021-06-15|上海尚实能源科技有限公司|Gas turbine engine centerbody assembly system|
    CN112282963B|2020-10-28|2021-05-04|上海尚实能源科技有限公司|Gas turbine engine tail cone connecting piece|
    CN112355610B|2020-10-28|2021-06-29|上海尚实能源科技有限公司|Splicing equipment for assembling gas turbine engine|
    法律状态:
    2019-07-22| PLFP| Fee payment|Year of fee payment: 2 |
    2020-02-14| PLSC| Search report ready|Effective date: 20200214 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 3 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1857457A|FR3084916B1|2018-08-10|2018-08-10|FLEXIBLE FIXING EJECTION CONE|
    FR1857457|2018-08-10|FR1857457A| FR3084916B1|2018-08-10|2018-08-10|FLEXIBLE FIXING EJECTION CONE|
    CN201980049780.XA| CN112543843A|2018-08-10|2019-08-09|Exhaust cone with flexible fitting|
    US17/267,361| US20210293201A1|2018-08-10|2019-08-09|Exhaust cone with flexible attachment|
    EP19778567.8A| EP3833861A1|2018-08-10|2019-08-09|Exhaust cone with flexible attachment|
    PCT/FR2019/000127| WO2020030858A1|2018-08-10|2019-08-09|Exhaust cone with flexible attachment|
    [返回顶部]