• 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 proposes an assembly comprising: - an exhaust casing (110) of a turbomachine, comprising two respectively inner and outer rings extending one inside the other concentrically about an axis of turbomachine, and a plurality of arms extending radially between the ferrules, and - an annular piece (130) centered on the axis, attached to a ferrule of the exhaust casing, downstream of said casing with respect to a flow of air in the turbomachine, the assembly being characterized in that the annular piece and the shell of the housing on which it is attached each comprise a circumferential thread (131, 115), said threads cooperating to allow a screw connection of the annular piece on the shell of the housing.
    公开号:FR3037358A1
    申请号:FR1555331
    申请日:2015-06-11
    公开日:2016-12-16
    发明作者:Sousa Mario Cesar De；Benoit Argemiro Matthieu Debray；Dominique Michel Fouquet；Gregory Ghosarossian-Prillieux；Frederic Noel
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to a turbomachine assembly comprising an exhaust casing and an annular downstream part that can be a mixer or an exhaust nozzle, or an exhaust cone.
    [0002] STATE OF THE ART FIG. 1 shows an example of a known turbine engine assembly, comprising an exhaust casing 10, a mixer 20, and an exhaust cone 30.
    [0003] The exhaust casing is a piece of revolution about an axis (not shown) of the turbomachine located immediately downstream of a low pressure turbine Turbomachine TuBP, with respect to the direction of flow of air in the turbomachine. The exhaust casing 10 comprises an inner ferrule 11 and an outer ferrule 12, these two ferrules being cylindrical pieces of revolution extending one inside the other concentrically around the axis of the ferrule. turbine engine. The exhaust casing further comprises a plurality of radial arms 13 extending between the inner shell 11 and the outer shell 12.
    [0004] The mixer 20 is a piece composed of a circular fastening flange to which is welded a lobed annular sheet metal part. The mixer 20 is an annular piece centered on the axis of the turbomachine, attached to the outer ring of the housing, downstream thereof. In a double-flow turbomachine, the mixer 20 is the part at which the primary flow and the secondary flow are mixed. It has, to optimize this mixture, a section in a plane orthogonal to the axis of revolution having a generally circular shape and forming undulations. Alternatively, the mixer may be replaced by an exhaust nozzle devoid of lobes.
    [0005] The exhaust cone 30 is also an annular piece centered on the turbomachine axis, having a cone shape whose open end is attached to the inner ring of the exhaust casing, downstream thereof. The flow of air at the outlet of the exhaust casing 10 thus circulates between the exhaust cone 30 and the nozzle or the mixer 20.
    [0006] As can be seen in FIG. 1, the mixer and the exhaust cone are fixed on the respective ferrules of the exhaust casing by bolting. In this regard, each ferrule comprises a scalloped flange dedicated solely to this assembly.
    [0007] Figure 2a shows a view of the assembly of the mixer 20 on the exhaust casing. The outer shell of the housing comprises a scalloped flange 15 oriented substantially axially with respect to the axis of the turbomachine, the orientation of a flange being defined by the orientation of the bolts allowing its assembly. Each festoon includes a through hole for bolting the mixer. Likewise, the mixer 20 comprises a scalloped flange 21 corresponding to the flange 15 of the exhaust casing. Figure 2b shows a view of the assembly of the exhaust cone 30 on the exhaust casing 10. The inner ring of the housing also comprises a scallop flange 16 substantially radial. Each festoon also has a through hole for bolting the exhaust cone. Similarly, a circumferential section 31 of the exhaust cone includes orifices for bolting to the exhaust casing. In addition, this section includes an extra thickness comprising radial festonnages to drown the heads of the screws and to guarantee the mechanical strength of the link. The set of bolts and additions of materials (scallops, overthickness) induces a mass for all the parts that can be substantially optimized. DESCRIPTION OF THE INVENTION One of the objects of the invention is to propose an alternative to a bolted connection of an exhaust casing to an exhaust cone, a mixer, or an exhaust nozzle, allowing economy mass of these pieces. In this regard, the invention relates to an assembly comprising: a turbomachine exhaust casing, comprising two respectively internal and external shrouds extending one inside the other concentrically around a turbomachine axis, and a plurality of arms extending radially between the ferrules, and an annular piece centered on the axis, attached to a shell of the exhaust casing, downstream of said casing with respect to a flow of air in the turbomachine, the assembly being characterized in that the annular piece and the shell of the casing on which it is attached each comprise a circumferential thread, said threads cooperating to allow a screw mounting of the annular piece on the casing shell. Advantageously, but optionally, the assembly according to the invention may further comprise at least one of the following features: - The thread of the shell of the housing may be formed on a radially outer surface of the ferrule. - The assembly may further comprise a stop system in axial translation of the annular piece on the shell of the housing. The stop system in axial translation comprises at least one groove arranged in the shell of the exhaust casing being adjacent to the threading. - The groove may be circumferential. - The axial translation stop system comprises a plurality of threaded through holes 20 arranged on the annular part and adapted to be opposite the groove when the part is screwed on the exhaust casing, and a plurality of screws. adapted to be screwed into the orifices. - The annular part may be a mixer or exhaust nozzle 25 (e) on the outer shell of the exhaust casing. - The annular piece may be an exhaust cone attached to the inner shell of the exhaust casing. Each screw may furthermore be shaped so as to be entirely contained in a volume constituted by an orifice of the exhaust cone and the throat of the exhaust casing. The invention also relates to a turbomachine, comprising an assembly according to the foregoing description.
    [0008] The invention may also relate to an exhaust casing, a mixer, an exhaust nozzle or an exhaust cone forming part of the assembly described above.
    [0009] The proposed assembly allows a mass reduction of the order of 500 g compared to the prior art. Indeed, the festoons and bolts are removed and replaced by a thread. In the case where the part is an exhaust cone, the extra thickness necessary for the bolting of the exhaust cone is also eliminated.
    [0010] The threading is a solution well adapted for this type of connection vis-à-vis the mechanical stresses to which the connection is subjected. The thread also has the advantage of facilitating the manufacture and maintenance of the assembly, thus reducing its cost of production and maintenance.
    [0011] DESCRIPTION OF THE FIGURES Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings in which: FIG. described, represents a turbomachine assembly 20 comprising an exhaust casing according to the prior art, - Figures 2a and 2b, already described also, are views of the detail of the assembly of an exhaust casing respectively to a mixer and an exhaust cone according to the prior art. FIGS. 3a and 3b illustrate an exhaust casing according to two embodiments of the invention, FIGS. 4a and 4b illustrate a mixer of an assembly according to one embodiment of the invention, FIGS. and 5b illustrate an exhaust cone of an assembly according to one embodiment of the invention; FIG. 6a is a sectional view of the assembly of an exhaust cone on an exhaust casing, - Figure 6b is a sectional view of the assembly of a nozzle or a mixer on an exhaust casing.
    [0012] DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT OF THE INVENTION There will now be described at least one set 1 of a turbomachine according to one embodiment of the invention.
    [0013] The assembly 1 comprises an exhaust casing 110, the exhaust casing being a part of revolution about an X-X axis of the turbomachine. The assembly 1 further comprises at least one annular piece screwed on the exhaust casing of a downstream side of the exhaust casing with respect to an air flow in the turbomachine - the part being centered on the axis XX 10 when mounted on the exhaust housing. The annular piece may be either a nozzle or a mixer 120, in the case where the turbomachine is double-flow, or an exhaust cone 130. According to an advantageous variant, the assembly 1 comprises an exhaust casing 110, an exhaust cone 130, and a nozzle or mixer 120 screwed onto the housing 110. The various components of the assembly will be described in more detail. Exhaust Housing 110 The exhaust housing 110 includes an inner shell 111 and an outer shell 112, both of which are cylindrical pieces of revolution extending concentrically around each other. the axis XX of the turbomachine. The exhaust casing further comprises a plurality of radial arms 113 with respect to the axis XX of the turbomachine, extending between the inner shell 111 and the outer shell 112. The exhaust casing 110 further comprises at least one circumferential thread, 114, 115, respectively arranged in a surface of the inner shell 111 and / or the outer shell 112. Advantageously, the thread 114, 115 is formed in a radially outer surface 111 *, 112 * of the ferrule, near a downstream edge of said surface. Each circumferential thread allows the mounting by screwing of a respective annular piece. The thread thus extends over a plurality of turns of each ferrule, preferably between 2 and 10 turns, for example over 4, 5 or 6 turns.
    [0014] Thus, with reference to FIG. 3a, the exhaust casing 110 comprises, on an outer surface 112 * of the outer shell 112, a circumferential threading 114, this thread allowing the screw connection of an exhaust nozzle. or a mixer 120 on the outer shell 112 of the exhaust casing 110.
    [0015] With reference to FIG. 3b, the exhaust casing comprises, on the external surface 111 * of the inner ferrule 111, a circumferential thread 115, this thread allowing the screw mounting of an exhaust cone 130 on the ferrule internal 111 of the exhaust casing 110. Advantageously, the exhaust casing 110 comprises two threads 114, 115 made on the outer shell 112 and inner 111, so as to screw a mixer or an exhaust nozzle on the ferrule external and an exhaust cone on the inner shell. In this case, the exhaust cone 130 extends inside the exhaust nozzle or mixer 120 coaxially.
    [0016] If the exhaust casing 110 has a thread on an inner or outer shell, the scalloped flange previously used for mounting the corresponding downstream part by bolting is omitted. Exhaust nozzle or mixer With reference to FIGS. 4a and 4b, the annular piece that can be screwed onto the exhaust casing may be a mixer or an exhaust nozzle. To enable the nozzle or mixer to be screwed onto the outer shell 112 of the casing, the latter also comprises a circumferential thread 121. The thread 121 is adapted to cooperate with the thread 114 of the outer shell 112 25 of the exhaust casing. 110. In this regard, the circumferential threading of the mixer or the nozzle 120 is preferably provided on a radially inner surface 122 of the latter, to cooperate with a thread 114 arranged on a radially outer surface 112 * of the ferrule 112.
    [0017] Exhaust cone With reference to FIGS. 5a and 5b, the annular piece that can be screwed onto the exhaust casing may be an exhaust cone 130. To allow the exhaust cone 130 to be screwed onto the inner ferrule 111 of the exhaust cone 130. exhaust casing, it also comprises a circumferential thread 131. The thread 131 is adapted to cooperate with the thread 115 of the inner ring of the exhaust casing 110. In this respect, if the thread 115 is made on an outer surface 111 * of the shell of the housing, the thread 131 is formed on a radially inner surface 132 of the exhaust cone 130.
    [0018] Preferably, the threads 114, 115 of the exhaust casing 110 as well as the threads 121, 131 of the nozzle / mixer and 120 / or the exhaust cone 130 are adapted to allow good angular indexing of the nozzle. downstream part 120, 130 relative to the exhaust casing 110.
    [0019] For example, the nozzle, the mixer and the exhaust cone may have one or more drainage holes which must be located in the down position when the part is mounted on the housing, that is to say substantially at the vertical below the axis of the turbomachine ("at 6 o'clock"). The threads of the exhaust casing 110 and the downstream part to be angularly indexed must therefore be adapted to allow this positioning, by precisely choosing the angular position of the start of each thread on each part. To do this, each thread is preferably made by milling. Stop in translation Advantageously, the assembly 1 further comprises a stop system 140 in axial translation of the downstream part on the exhaust casing. In the case where the assembly 1 comprises a mixer or an exhaust nozzle 120 and an exhaust cone 130 screwed onto the exhaust casing, the stop system 140 is applicable both to the translation stop. the exhaust cone 130 relative to the housing 110 and the mixer or the nozzle 120 relative to the housing 110. The axial translation stop system is shown in FIG. 6a, in the case where the downstream part is a exhaust cone 130, and in FIG. 6b, in the case where it is an exhaust nozzle or a mixer 120. The translation stop system 140 advantageously comprises a groove 141 made of adjacent the thread 114 or 115 of the exhaust casing, that is to say on the outer surface respectively of the outer shell 112 and / or the inner ring 111 of the exhaust casing. The groove 141 is preferably circumferential. Alternatively, the groove 141 may comprise a plurality of circular sector sections. According to another alternative, nevertheless less advantageous for reasons of manufacturability, the groove 141 may be replaced by localized machining, arranged at the precise locations of the screws. In addition, the translational stop system 140 includes at least one through orifice 142 formed in the circumferential wall of the downstream part carrying the thread 131, 132. Each through orifice 142 is threaded. Preferably, each downstream part (mixer or nozzle 120 or exhaust cone 130) has a plurality of through orifices 142 arranged regularly around the circumference of the wall carrying the thread. For example, the downstream part may comprise three through orifices 142 distributed at a constant angular interval of 120 °. The locations of the orifices 142 are chosen so that the orifices are opposite the groove 141 of the exhaust casing when the annular piece is screwed onto the casing 110.
    [0020] Finally, the axial translation stop system 140 comprises a plurality of screws 143 adapted to be screwed into the orifices 142. Each screw is thus received in an orifice 142 until it emerges in the groove 141. The end of the screw housed in the groove abuts against the edges of the groove and prevents axial translation of the downstream part relative to the exhaust casing.
    [0021] Preferably, as shown in FIG. 6a, when the downstream part is an exhaust cone 130, each screw 143 is shaped so as to be completely contained in a volume consisting of an orifice 142 of the exhaust cone and the groove 141 the exhaust casing, so as not to protrude from the wall of the exhaust cone 130.
    [0022] Indeed, when the screw is disposed in an orifice, the head of the screw is at a radially outer surface of the exhaust cone. However, since the flow of air in the turbomachine takes place between the exhaust nozzle / mixer and the exhaust cone, the fact that the head of the screw is projecting relative to the exhaust cone would impact unfavorably the air flow 30 between the exhaust cone and the mixer or the nozzle. The screws used may be of the type with BTR or domed head.
    [0023] The replacement of a bolted connection by a screw connection makes it possible to reduce the mass of the assembly. Preferably, to reduce the mass more significantly, both the exhaust cone and the nozzle or mixer are shaped to be screwed on the exhaust casing. 5
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Assembly (1) comprising: - a turbomachine exhaust casing (110), comprising two respectively internal (111) and outer (112) ferrules extending one inside the other concentrically around each other; a turbomachine axis (XX), and a plurality of arms (113) extending radially between the ferrules, and - an annular piece (120, 130) centered on the axis, attached to a ferrule of the exhaust housing (110), downstream of said casing with respect to an air flow in the turbomachine, the assembly being characterized in that the annular piece (120), 130) and the shell (111, 112) of the casing on which it is reported each comprise a circumferential thread (121, 131, 114, 115), said threads cooperating to allow mounting by screwing the annular piece on the shell of the housing.
    [0002]
    2. The assembly of claim 1, wherein the thread (114, 115) of the ferrule (111, 112) of the housing is formed on a radially outer surface (111 *, 112 *) of the ferrule.
    [0003]
    3. An assembly according to one of claims 1 or 2, further comprising a stop system (140) in axial translation of the annular piece (120, 130) on the shell (111, 112) of the housing (110).
    [0004]
    4. The assembly of claim 3, wherein the axial translation stop system (140) comprises at least one groove (141) arranged in the shell of the exhaust casing being adjacent to the thread.
    [0005]
    5. The assembly of claim 4, wherein the groove (141) is circumferential.
    [0006]
    6. An assembly according to one of claims 3 or 4, wherein the axial translation stop system (140) comprises a plurality of threaded through holes (142) arranged on the annular piece (120, 130) and adapted to be opposite the groove (141) when the workpiece is screwed to the exhaust housing, and a plurality of suitable screws (143) to be screwed into the orifices (142).
    [0007]
    7. An assembly according to one of the preceding claims, wherein the annular member is a mixer or an exhaust nozzle (120) attached to the outer shell (112) of the exhaust casing (110).
    [0008]
    8. An assembly according to one of claims 1 to 6, wherein the annular part is an exhaust cone (130) attached to the inner shell (111) of the exhaust casing (110).
    [0009]
    An assembly according to claim 8 in combination with claim 6, wherein each screw (143) is further shaped to be integrally contained in a volume constituted by an orifice (142) of the exhaust cone and the groove ( 141) of the exhaust casing.
    [0010]
    10. Turbomachine, comprising an assembly (1) according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    US20180171932A1|2018-06-21|
    FR3037358B1|2017-05-19|
    EP3307991B1|2019-05-29|
    CN107709744B|2019-09-20|
    EP3307991A1|2018-04-18|
    WO2016198806A1|2016-12-15|
    CN107709744A|2018-02-16|
    US11053890B2|2021-07-06|
    引用文献:
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    FR2978989A1|2011-08-12|2013-02-15|Aircelle Sa|EJECTION CONE FOR AIRCRAFT TURBOJET ENGINE|
    WO2013163510A1|2012-04-27|2013-10-31|General Electric Company|Connecting gas turbine engine annular members|
    US20140053563A1|2012-08-27|2014-02-27|Snecma|Method for assembling a nozzle and an exhaust case of a turbomachine|
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    GB0221585D0|2002-09-17|2002-10-23|Weatherford Lamb|Tubing connection arrangement|
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    US9200537B2|2011-11-09|2015-12-01|Pratt & Whitney Canada Corp.|Gas turbine exhaust case with acoustic panels|
    US20140209291A1|2013-01-28|2014-07-31|Schlumberger Technology Corporation|Seals for electric submersible pump|
    CN203321652U|2013-05-21|2013-12-04|宁波奥格达汽配有限公司|Automobile air exhaust duct easy to clean|
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    US10519805B2|2015-04-13|2019-12-31|United Technologies Corporation|Turbine case coupling|
    US10082042B2|2015-06-22|2018-09-25|United Technologies Corporation|Case coupling and assembly|
    FR3053430B1|2016-06-30|2019-01-25|Snecma|TURBOMACHINE ASSEMBLY FOR A SEALED ASSEMBLY OF A FRONT CONE ON A FRONT VIROLE|
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    US10330009B2|2017-01-13|2019-06-25|United Technologies Corporation|Lock for threaded in place nosecone or spinner|
    US10393065B2|2017-11-09|2019-08-27|United Technologies Corporation|Variable nozzle apparatus|
    US10808613B2|2018-01-09|2020-10-20|Raytheon Technologies Corporation|Assembly for releasable locking of a spinner or nosecone to an engine structure|
    US10774685B2|2018-04-30|2020-09-15|Ratheon Technologies Corporation|Gas turbine engine exhaust component|
    FR3082238A1|2018-06-11|2019-12-13|Airbus Operations|PRIMARY NOZZLE OF A PRIMARY EJECTION DUCT OF A TURBOMACHINE|
    法律状态:
    2016-06-10| PLFP| Fee payment|Year of fee payment: 2 |
    2016-12-16| PLSC| Search report ready|Effective date: 20161216 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 4 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-10| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20200304 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1555331A|FR3037358B1|2015-06-11|2015-06-11|EXHAUST CASE ASSEMBLY AND END OF REVOLUTION PIECE|FR1555331A| FR3037358B1|2015-06-11|2015-06-11|EXHAUST CASE ASSEMBLY AND END OF REVOLUTION PIECE|
    PCT/FR2016/051415| WO2016198806A1|2015-06-11|2016-06-10|Assembly comprising an exhaust case and a downstream rotationally symmetrical part|
    EP16735912.4A| EP3307991B1|2015-06-11|2016-06-10|Assembly comprising an exhaust case and a downstream rotationally symmetrical part|
    US15/580,496| US11053890B2|2015-06-11|2016-06-10|Assembly comprising an exhaust case and a downstream rotationally symmetrical part|
    CN201680033063.4A| CN107709744B|2015-06-11|2016-06-10|Component including exhaust casing and downstream rotational symmetry component|
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