• 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 a turbomachine subassembly and a turbomachine comprising - an annular gas flow duct (16) which is radially delimited, with respect to the main axis of the turbomachine, by a radially inner shell (20) and a radially outer shell (18), - at least one radial arm (22) extending radially between the inner shell (20) and the outer shell (18), which delimits an isolated volume of the annular vein (16), and in which a section (38) of at least one duct extends radially, and - means for supplying ventilation air to an enclosure (28) delimited at least in part by the inner shell (20), via said at least one radial arm (22), characterized in that the interior volume of said at least one radial arm (22) is connected to the interior volume of said enclosure (28) and to an air supply source ventilation.
    公开号:FR3036442A1
    申请号:FR1554582
    申请日:2015-05-21
    公开日:2016-11-25
    发明作者:Augustin Marc Michel Curlier；Nicolas Aussedat
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD The invention provides an aircraft turbine engine comprising a ventilation system of a generator mounted downstream of the low pressure turbine. Because of its layout, the generator can be brought to heat up strongly, it must therefore be associated with additional means for cooling by a ventilation air, and integrate these ventilation means in spaces that do not affect the operation of the turbomachine. STATE OF THE PRIOR ART In the context of the development of the management of energy in an aircraft, it has been proposed to incorporate an electric current generator into the turbomachine, in order to supply, for example, an electric de-icing system. . In a turbofan-type conventional turbomachine, a generator is driven via the high-pressure unit (HP) of the turbomachine via a gearbox, within a set of equipment commonly called "accessory gear box". "or AGB. It has been proposed to add an additional generator driven by a low pressure shaft of the turbomachine, which is disposed in the extension of this low pressure shaft, inside an enclosure formed by an exhaust housing hub. This generator is supplied with lubricating liquid which also ensures its cooling. But this lubricating liquid does not completely cool the generator.
    [0002] It has therefore been proposed to add a ventilation circuit of the generator, which comprises an air supply circuit of the enclosure in which the generator is located.
    [0003] 3036442 2 The ventilation circuit comprises in particular an air flow section which passes through a radial arm of the exhaust casing. The radial arms are already traversed by a plurality of conduits, which limits the space available for one or more additional conduits for supplying the enclosure with sufficient ventilation air. It has also been proposed to supply the interior volume of the radial arms with ventilation air. For this purpose, a volume of pressurization of the ventilation air is formed around the exhaust casing. To achieve this volume, an additional shell is mounted around the exhaust casing.
    [0004] However, according to an embodiment of recent turbomachines, the exhaust casing is fixed to a support ring by means of suspension screeds. These screeds prevent the establishment of such an additional shell. The object of the invention is to propose a system for supplying the ventilation air chamber via the interior volume of the radial arms, which makes it possible to connect the interior volume of the radial arms to a source of ventilation air. . SUMMARY OF THE INVENTION The invention relates to a subset of a turbomachine comprising an annular gas flow vein which is radially delimited, with respect to the main axis of the turbomachine, by a radially inner shell and a ferrule radially external, at least one radial arm which extends radially between the inner ferrule and the outer ferrule, which delimits an isolated volume of the annular vein, and in which a portion of at least one duct extends radially, and means for supplying ventilation air to an enclosure delimited at least in part by the inner shell, via said at least one radial arm, characterized in that the internal volume of said at least one radial arm is connected to the internal volume of said enclosure and to a source of ventilation air supply.
    [0005] 3036442 3 Connecting the inside volume of one radial arm to both the enclosure and the connection box allows the ventilation air to circulate through the radial arm volume, without adding an additional duct to the arm. The connection box allows the connection of the internal volume of the arm, without being hampered by the presence of the support means of the exhaust casing. Preferably, the inner radial end of said arm opens directly into the chamber and the outer radial end of each arm carries means for connecting the internal volume of the arm to said air source. Preferably, each radial end of the arm carries a box for connecting the internal volume of the arm to the enclosure or to said air source and the end of the section of the duct which is associated with said axial end of the arm is connected to the rest. duct via said associated connection box. Preferably, one of the two connection boxes, in particular the connection box associated with the radially outer end of the arm, is mounted to slide radially relative to the radial end of the arm at which said housing is mounted. Preferably, the outer radial end of the arm carries a first connecting box which sealingly closes the radial outer end of the arm, which comprises means for connecting the section to the rest of the conduit which is associated with it and connection means. the internal volume of the arm to the source of ventilation air supply. Preferably, the subassembly comprises a second connection box which is mounted near the radially inner end of the arm and which is offset radially inward with respect to the radially inner end of the arm.
    [0006] Preferably, the second connection box comprises a first channel oriented mainly radially, to which the inner radial end of the section, which is associated with it, is connected, and a second channel oriented mainly parallel to the main axis of the turbomachine, which extends the first channel and is connected to the rest of the conduit 3036442 4 Preferably, the turbomachine comprises a support ring on which all the second connection boxes are mounted. Preferably, the casing which is slidably mounted relative to the associated radial end of the arm has a cylindrical outer face located opposite a cylindrical face of said associated radial end of the arm and carries means making contact sliding waterproof between the two walls vis-à-vis. - cf. Previous comment Preferably, the cylindrical outer face of the housing carries an annular bead having an outer surface in a sphere portion which is in contact with the cylindrical face of said associated radial end of the arm. The invention also relates to an aircraft turbomachine (10), which comprises such a subassembly. Preferably, the exhaust casing is connected to a support member by means of a suspension mesh which is connected to the outer shell of the casing.
    [0007] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended figures in which: FIG. 1 is a schematic representation in perspective of The downstream portion of the turbomachine of a turbomachine comprising a generator and ventilation means of the enclosure receiving this generator; Figure 2 is a schematic perspective and exploded view of downstream portion of the turbomachine shown in Figure 1; Figure 3 is a section along an axial plant of an exhaust casing arm made according to the invention; Figure 4 is a detail on a larger scale of the outer radial end of the arm shown in Figure 3; Figure 5 is a detail on a larger scale of the inner radial end of the arm shown in Figure 3; FIG. 6 is a perspective detail of the connection box shown in FIG. 5. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS For the description of the invention, the axial orientation of the invention will be adopted without implied limitation. upstream downstream as being the axial direction from left to right with reference to FIG. 2. FIGS. 1 and 2 show a downstream part of a turbomachine 10, for example an aircraft turbomachine. The turbomachine 10 comprises in particular a low-pressure shaft 12 which is driven by the low-pressure turbine of the turbomachine 10 and an exhaust casing 14 delimiting the downstream portion of an annular gas flow stream 16. The exhaust casing 14 comprises a radially outer shell 18, a radially inner shell 20 coaxial with the main axis of the turbomachine 10 and radial arms 22 which connect the rings 18, 20 to one another.
    [0008] The radial arms 22 are hollow and allow ducts and cables to pass through the annular duct 16 by protecting them from the flow of gas in the annular duct 16. The turbomachine also comprises a set of beams or connecting rods (not shown ), forming a suspension lattice, through which the exhaust casing 14 is attached to a supporting peripheral component such as a support ring. This lattice is located outside the outer shell 18 and surrounds it. For the connection of the exhaust casing 14 to this lattice, the outer shell 18 18 has yokes 70 projecting radially outwardly, which are connected to the beams or rods. The turbomachine 10 also comprises an electric current generator 24 which is mounted coaxially with the low-pressure shaft 12, downstream thereof.
    [0009] The rotor (not shown) of the generator 24 is connected and is driven by the low pressure shaft 12. The turbomachine 10 comprises a downstream collar 26 which extends downstream of the inner shell 20 of the exhaust casing 14. These two rings 20, 26 define an enclosure 28 in which the generator 24 is received. The generator 24 is supplied with lubricating liquid by a lubricating circuit 30 comprising in particular two conduits 32 (a supply duct for lubricating liquid and a discharge duct) which pass through a radial arm 22. The generator 24 is brought to the s During the operation of the turbomachine 10, the heating circuit 30 is used to cool the internal components of the generator 24 such as bearings, coils, for example. However, the heat extraction exerted by this lubrication is insufficient and must therefore be assisted by the ventilation of the enclosure 28 in which is housed the generator 24. - 15 turbomachine 10 for this purpose comprises a ventilation device of the generator 24 which consists in supplying the chamber 28 with fresh air taken from a primary vein (not shown) of the turbomachine 10. This ventilation air is then discharged downstream through orifices 34 formed in the downstream ferrule 26. The feed The ventilation air chamber 28 is made by circulating the ventilation air directly through the interior of each radial arm 22. That is, the ventilation air circulates around the ducts 32. and cables arranged in the various radial arms 22. This makes it possible not to add one or more ventilation ducts through the radial arms 22, since the space available is already limited.
    [0010] Each radial arm 22 thus delimits a radial duct which is traversed by one or more ducts and which is also traversed directly by a flow of ventilation air. The radial duct delimited by each arm 22 is directly connected to the internal volume of the enclosure 28 receiving the generator 24, that is to say that the inner radial end of the arm 22 opens into the enclosure 28.
    [0011] On the other hand, the internal volume of each arm 22 is isolated from the volume surrounding the outer shell 18 of the exhaust casing 14. For this purpose, the outer radial end of the arm 22 is closed hermetically in the air by a external box 36 of connection.
    [0012] The outer casing 36 is traversed by the conduits 32 and cables passing through the arm 22 associated therewith. Preferably, each duct 32 comprises a section 38 which is situated in the associated arm 22 and which is connected to the remainder of the duct 32 via the external casing 36 and to an internal connection box 40, which is located at the level of the duct 32. the radially inner end of the arm 22. This facilitates the mounting of a duct 32 by mounting each section 38 in the associated arm 22 by fixing it to the two housings 36, 40, and then connecting the other two parts of the leads 32 to the two housings 36, 40, thus connecting them to the ends of the section 38.
    [0013] As previously mentioned, the internal volume of the arm 22 opens directly into the chamber 28. Therefore, and preferably, the internal connection box 40 is offset radially inward with respect to the radial end 22. As can be seen in more detail in FIG. 4, the external connection box 36 has an internal volume 42 which communicates with the internal volume of the arm 22 and which is able to be connected to the source of the power supply. Ventilation air by known means (not shown). The external connection box 36 comprises flanges 44 for supporting the sections 38 of the ducts 32 and connectors 46 arranged at the ends 25 of the sections 38, for the connection of each section to a portion of the duct 32 associated. Each connector 46 is made in known manner, it consists here of a connector of the nipple and nozzle type which is locked by a nut 48.
    [0014] As can be seen in more detail in FIGS. 5 and 6, the internal connection box 40 has an internal pipe 50 associated with each pipe 32 which is associated with the arm 22. Each pipe 50 comprises a channel 52 oriented mainly radially 5. , and a channel 54 oriented parallel to the main axis of the turbomachine. The radial channel 52 opens radially outwards and is adapted to be connected to the inner radial end of the associated section 38. Here, the radial channel 52 is extended radially outwards by a threaded sleeve 56 which is adapted to cooperate with a nut 58 for clamping the inner radial end of the associated section 38 in the radial channel 52. The axial channel 54 is intended to be connected to a portion of the conduit 32 associated with the section 38. According to the embodiment shown, the two radial channels 52 are aligned axially. The axial channels 54 are preferably offset laterally with respect to each other, so as not to impede the flow of fluid or their connection to the associated conduit 32. Each internal connection box 40 is located radially at a distance from the inner radial end of the associated arm 22, and consequently it is located radially at a distance from the inner shell 20. The support of the internal connection boxes 40 is made by 20 through a support ring 60 which is located inside the enclosure 28 and which is connected to a mechanical interface of the exhaust casing, which is here a support flange of a bearing. All the internal connection boxes 40 are fixed to the support ring 60. By way of non-limiting examples, the fixing of the internal connection boxes 40 on the support ring 60 is carried out by bolting, by welding, or well realizing the boxes 40 and the support ring 60 in one piece. During operation of the turbomachine 10, the variations in operating conditions and temperature therein result in dimensional variations of its components by expansion.
    [0015] Also, the dimensional variations of the components of the turbomachine take place during a transition between a cold state of the turbomachine, that is to say before it starts, in which all the components of the turbomachine are cold and an operating state in which some components are very hot and other components such as coolant circulation ducts are still cold. Thus, in particular, the length of the sections 38 may vary, or the relative distance between the external connection box 36 and the internal connection box 40 may also vary.
    [0016] To allow such dimensional variations, one of the two connection boxes 36, 40 is mounted to slide radially relative to the radial end of the arm 22 associated therewith, while the other connection box 40, 36 is stationary radially relative to the radial end of the arm 22 associated therewith.
    [0017] According to a preferred embodiment which is shown in the figures, it is the external connection box 36 which is mounted to slide radially relative to the outer radial end of the arm 22. Therefore, the internal connection box 40 is stationary relative to the radially inner end of the arm 22.
    [0018] According to another embodiment allowing the dimensional variations of the sections 38 with respect to the arm 22, the means of hydraulic connection of the inner radial ends of the sections 38 with the internal box 40 are formed to allow radial sliding of the inner radial ends of the sections. 38 with respect to the arm 22, and more particularly with respect to the support ring 60 and the internal casing 40. For example, the connection means do not comprise a clamping nut 58 and the external connection box 36 is fixed in relation to the outer end of the arm 22. FIG. 3 shows an external connection box which is made according to the embodiment in which the dimensional variations of the ducts 32 are made possible by a radial sliding of the duct 32. outer casing 36 relative to the outer radial end of the arm 22. According to this embodiment, the housing outer tier 36 has an outer cylindrical wall 62 which is received within and away from an inner cylindrical wall 64 of the outer radial end of the arm 22. The outer cylindrical wall 62 has at its radial end internal, an annular bead 66 which bears in airtight manner against the inner wall 64 of the radial end of the arm 22. The airtightness of this support is completed by an annular seal not shown.
    [0019] The outer face of this bead 66 is a sphere portion, so that the support between the inner wall 64 of the radial end of the arm 22 and the bead 66 can be maintained even if the orientation of the outer casing 36 becomes more radial, because of the different expansions of the two sections 38. Thus, this bead 66 makes it possible to maintain a sealed sliding contact 15 between the inner wall 64 of the radial end of the arm 22 and the outer cylindrical 62 of the outer casing 36. Connection boxes 36 located on the outer shell 18 are generally installed between the yokes 70 and their dimensions make it possible not to hinder the installation of the suspension mesh of the exhaust casing 14.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Subassembly of a turbomachine (10) comprising - an annular gas flow vein (16) which is delimited radially, with respect to the main axis of the turbomachine, by a radially inner shell (20) and a radially ferrule external device (18), - at least one radial arm (22) extending radially between the inner shell (20) and the outer shell (18), which delimits an isolated volume of the annular vein (16), and wherein a section (38) of at least one duct extends radially, and - means for supplying ventilation air to an enclosure (28) delimited at least in part by the inner shell (20), by the intermediate of said at least one radial arm (22), characterized in that the internal volume of said at least one radial arm (22) is connected to the interior volume of said enclosure (28) and to a source of ventilation air supply.
    [0002]
    2. Subassembly according to the preceding claim, characterized in that the inner radial end of said arm (22) opens directly into the chamber (28) and the outer radial end of each arm carries means for connecting the internal volume of the arm to the said air source.
    [0003]
    3. Subassembly according to any one of the preceding claims, characterized in that each radial end of the arm (22) carries a connecting box (36, 40) of the internal volume of the arm to the enclosure or to said air source. and in that the end of the section (38) of the duct (32) which is associated with said axial end of the arm (22) is connected to the remainder of the duct via said associated connection box.
    [0004]
    4. Subassembly according to the preceding claim, characterized in that one of the two connection boxes (36, 40), in particular the housing 3036442 12 connection (36) associated with the outer radial end of the arm (22), is slidably mounted radially relative to the radial end of the arm (22) at which said housing (36, 40) is mounted. 5
    [0005]
    5. Subassembly according to the preceding claim, characterized in that the outer radial end of the arm (22) carries a first connection box (36) sealingly closing the radial outer end of the arm (22), which comprises means (46, 48) for connecting the section (38) to the remainder of the duct (32) associated therewith and means for connecting the interior volume of the arm (22) to the source 10 for supplying ventilation air.
    [0006]
    6. Subassembly according to claim 4 or 5, characterized in that it comprises a second connection box (40) which is mounted near the radial inner end of the arm (22) and which is offset radially towards the interior relative to the inner radial end of the arm (22).
    [0007]
    7. Subassembly according to claim 6, characterized in that it comprises a support ring (60) on which all the second connection boxes (40) are mounted. 20
    [0008]
    8. Subassembly according to any one of claims 4 to 7, characterized in that the second connection box (40) comprises a first channel (52) oriented mainly radially, to which the inner radial end of the section (38), associated therewith is connected, and a second channel (54) oriented substantially parallel to the main axis of the turbomachine (10), which extends the first channel (52) and which is connected to the remainder of the duct (32)
    [0009]
    9. Turbine engine (10), characterized in that it comprises a subassembly according to any one of the preceding claims. 3036442 13
    [0010]
    10. A turbomachine (10) according to the preceding claim, characterized in that the exhaust casing (14) is connected to a support member via a suspension mesh which is connected to the outer shell (18). of the housing (14). 5
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    同族专利:
    公开号 | 公开日
    US10364691B2|2019-07-30|
    GB2539096B|2020-06-17|
    US20160340053A1|2016-11-24|
    GB201608601D0|2016-06-29|
    FR3036442B1|2021-07-16|
    GB2539096A|2016-12-07|
    引用文献:
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    法律状态:
    2016-05-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-25| PLSC| Search report ready|Effective date: 20161125 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1554582A|FR3036442B1|2015-05-21|2015-05-21|TURBOMACHINE WITH A VENTILATION SYSTEM|FR1554582A| FR3036442B1|2015-05-21|2015-05-21|TURBOMACHINE WITH A VENTILATION SYSTEM|
    GB1608601.9A| GB2539096B|2015-05-21|2016-05-16|Turbomachine comprising a ventilation system|
    US15/156,660| US10364691B2|2015-05-21|2016-05-17|Turbomachine comprising a ventilation system|
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