• 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 the passage of an electrical harness through a wall (28) comprising a tubular metal ferrule (34) extending across the wall (28) and housing the electrical harness, a sleeve of heat-shrinkable material (38, 64, 66) extending around an end portion (40, 50) of the tubular tip (34) and the electrical harness. The assembly comprises heat extraction means (42, 44, 46, 76) of the tubular nozzle which are arranged on the side of the tip (34) surrounded by the heat-shrinkable sleeve (38, 64, 66). .
    公开号:FR3034580A1
    申请号:FR1552763
    申请日:2015-03-31
    公开日:2016-10-07
    发明作者:George Kwakye；Benoit Marie Bernard Kieffer；Antonio Matias
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to an assembly for the passage of an electrical harness through a wall, in particular, in an intermediate casing of a turbomachine. BACKGROUND OF THE INVENTION It also relates to a housing and a turbomachine comprising such a housing or such an assembly. In a known manner, a turbomachine comprises an intermediate casing arranged between an upstream low pressure compressor and high downstream pressure. The intermediate casing comprises a plurality of radial arms joining concentric walls of revolution intended to form surfaces delimiting internally and externally the flow of primary and secondary flow air. The radial arms allow the passage of servitudes such as electrical harnesses in particular, which walk from inside the turbomachine to an accessory box carried by the nacelle of the turbomachine and arranged radially outside the flow of secondary air. An electrical harness usually comprises electrical cables comprising an electrically insulating outer layer, these cables being covered in particular with a textile sheath making it possible to limit the wear of the insulating layers and then, outside the textile sheath, a metal sheath intended to protect the electrical signals of the surrounding electromagnetic disturbances. This metal sheath is usually covered with a heat-shrink sleeve to reduce wear on the metal sheath.
    [0002] To achieve the passage of electrical cables through the walls of revolution, the electrical harness is inserted into a metal tip engaged in a hole of a wall of revolution of the intermediate casing. A sleeve of heat-shrinkable material is used on both sides of the wall. A first sleeve covers one end of the metal tip and part of the axial length of the metallic sheath. Similarly, on the other side of the wall a second sleeve covers one end of the metal tip and part of the axial length of the metal sheath. In operation, the temperature of the air in the casing arms 5 located in the secondary air duct is lower than the air temperature in the inter-vein space (between the primary annular vein and the secondary annular vein ), so that it is possible to use a sleeve heat shrinkable material whose temperature resistance is lower than the temperature resistance of the heat-shrinkable material used in the inter-vein space. However, it has been found that thermal conduction phenomena in the metal tip can lead to a significant increase in the temperature of the heat-shrink sleeve used in the crankcase of the secondary vein, which can lead to its self-ignition. . The invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above. For this purpose, it proposes an assembly for the passage of an electrical harness 20 through a wall comprising a tubular metal ferrule passing through both sides of the wall and housing the electrical harness, a sleeve of heat-shrinkable material s' extending around an end portion of the tubular tip and the electrical harness, characterized in that it comprises means for extracting heat from the tubular tip which are arranged on the side of the tip surrounded by by the heat-shrink sleeve. The invention proposes to integrate heat extraction means at the tip so as to limit the heat transfer to the heat-shrinkable sheath and thus prevent its self-ignition in operation.
    [0003] Preferably, the tubular nozzle comprises an annular flange applied to the wall and disposed between the wall and said heat extraction means. The flange ensures positioning of the tip in the wall opening by abutting the wall.
    [0004] According to another characteristic of the invention, the heat extraction means comprise a metal covering sheath integrally surrounding the heat-shrinkable sleeve and fixed at a first end located on the side of the wall by clamping on the tubular endpiece.
    [0005] The use of a metal sheath allows conduction of heat to the metal sheath surrounding the heat-shrinkable sheath rather than to the heat-shrinkable sleeve. In addition, the metal sheath provides confinement of the heat-shrinkable sleeve by limiting the amount of oxygen in contact with the sleeve, which further reduces the risk of self-ignition of the sleeve. According to another characteristic of the invention, said first end of the metal covering sheath is folded on itself radially inwards and clamped by a first member interposed radially between the first curved end and the remainder of the metallic sheath. recovery. A second clamping member may be applied to a second end of the metal covering sheath opposite the first end that is in contact with the heat-shrinkable sleeve. According to yet another characteristic of the invention, said metallic sheath 25 is made of a material whose thermal conductivity is greater than that of the tubular tip. The metal sheath may be a metal braid. The invention also relates to a housing, in particular an intermediate housing for a turbomachine, comprising an assembly of the type described above, in which said wall is a substantially cylindrical wall delimiting the radially internal surface of a flow of gas. The invention also relates to a turbomachine such as a turbojet, characterized in that it comprises an assembly as described above or a housing as described in the previous paragraph. The invention will be better understood and other details, advantages and characteristics of the invention will become apparent on reading the following description given by way of non-limiting example, with reference to the accompanying drawings, in which: FIG. schematic view in axial section of a turbomachine with a double flow according to the known technique; Figure 2 is a schematic view of an arm of an intermediate casing of a turbomachine; Figure 3 is a schematic sectional view of an assembly according to a first embodiment of the invention; Figure 4 is a schematic axial sectional view according to a second embodiment of the invention; Figures 5 and 6 are schematic views of two embodiments of the second embodiment.
    [0006] Referring first to FIG. 1, which shows a turbomachine comprising, upstream to downstream, a fan 12, a low-pressure compressor 14, an intermediate casing 16, a high-pressure compressor 18, a combustion chamber 20 , a high pressure turbine 21 and a low pressure turbine 22. The air entering the turbomachine is divided into a primary air flow (arrow A) which circulates inside the low and high pressure compressors 14, 18 to the combustion chamber 20 then through the high and low pressure turbines 21, 22, and a secondary air flow (arrows B) which bypasses the compressor 14, 18, the combustion chamber 20 and the turbine 21, 22.
    [0007] The intermediate casing 16 includes structural arms 24 extending radially outwardly. The intermediate casing 16 comprises a wall of internal revolution 26 delimiting externally the flow vein of the primary air flow and an outer wall of revolution 28 delimiting internally the flow vein of the secondary air flow.
    [0008] Some of the radial arms 24 such as for example the one arranged angularly at three o'clock with respect to the dial of a watch, when looking at the turbomachine from the upstream, comprise electrical harnesses of electrical cable passages (FIG. ). These harnesses 30 travel from a device to an accessory box 32 10 as shown in FIG. 1. Each electrical harness 30 comprises a set of electrical cables which are covered with a textile sheath itself covered with a metallic sheath. internal then a sleeve. The electric cables run through an orifice of the outer revolution wall 28 in a tubular tip 34, preferably made of metal, for example made of stainless steel, with an axis 35. The wall 28 is made in two half-pieces, preferably in aluminum alloy, which block the tip 34 longitudinally in the direction of the axis 35. For this purpose, the two half-pieces may comprise a shape of cut complementary 20 to a narrowed cross section of the tip. In such an embodiment, it is not necessary to make an end 34 externally threaded and fix the end piece 34 relative to the wall 28 by means of a nut screwed onto the thread of the endpiece. According to the invention, means for extracting heat are provided.
    [0009] Thus, in a first embodiment of the invention shown in FIG. 3, the tubular endpiece 34 comprises an annular flange 36 applied to the external face of the outer wall of revolution 28. The electrical harness 30 engaged in the endpiece tubular 34 is covered by a sleeve 38 of heat-shrinkable material, preferably of fluoroelastomer material, which also covers a first end portion 40 of the tip 34 located on the side of the flange 36 relative to the wall 3034580 6 28. The tip 34 further comprises a second end 41 located on the opposite side of the flange 36 relative to the wall 28. The end portions 40 and 41 are interconnected. The end piece 34 is locked at least in translation relative to the wall 28 along the axis 35. It can be welded to the wall 28 or mounted free to rotate relative to the wall 28 about the axis 35. heat extraction means are arranged along the axis of the sleeve between the annular flange 36 and the end of the sleeve covering the end portion 40 of the nozzle 34. These heat extraction means 10 comprise annular grooves 42 and annular ribs 44 of the tip. The grooves 42 are alternately disposed along the axis 35 of the nozzle 34 with the annular ribs 44 so as to form a heat exchange means. The ribs 44 are preferably integral with the first end portion 40.
    [0010] Advantageously, the flange 36 is disposed between the wall and the ribs 44. Thus, in operation, when heat circulates by thermal conduction in the tip 34, preferably metal, the grooves 42 and ribs 44 provide heat exchange with the external ambient air limiting the amount of heat flowing to the heat-shrinkable sleeve 38. According to a second embodiment shown in FIG. 4, the heat extraction means comprise an outer metallic covering sheath 46, for example made of nickel-plated copper which covers the heat-shrinkable sleeve 38 and which is fixed at its end located on the side of the wall 28 by clamping to the tubular metal endpiece by means of a collar 48. More particularly, FIGS. 5 and 6 show two variants of the second embodiment.
    [0011] Similarly to what has been described previously, the tip 34 comprises an annular collar 36. The end portion 50 of the tip 34, disposed on the side of the collar 36 with respect to the wall 28, comprises a cylindrical end portion 52 and two annular ribs 54, 56, arranged radially outwardly from the end portion 50 and spaced axially from each other along the axis 35 and arranged between the cylindrical portion 52 and the annular flange 36. As indicated above, the electrical cables are surrounded externally by a textile sheath 58 which is inserted into the tubular nozzle 34. An inner metal sheath 60 surrounds the textile sheath 58 to limit its wear and provides protection electromagnetic electric cables. The end of the inner metal sheath 60 surrounds the cylindrical end portion 52 of the ferrule 34 and is clamped on the cylindrical portion 52 by a clamp 62, for example. A heat-shrinkable sleeve 64, 66 is adhesively secured to a first end 68, 70 on the end portion 50 of the tubular tip 34 between the two annular grooves 54, 56 and for a second end 72 opposite on a free end. a sheath 74 of thermal protection surrounding the inner metal sheath 60 externally. The sheath 74 may be, for example, made of nickel-plated copper. In both variants of the invention shown in FIGS. 20 and 6, the heat extraction means comprise a covering metal sheath 76 disposed on the side of the collar 36 with respect to the wall 28 and completely surrounding the sleeve 64, 66. Said metal covering sheath 76 comprises a first end 78 located near the annular flange 36 and a second end 80 situated opposite, that is to say remote from the flange. The first end 78 of the covering sheath 76 is folded or curved on itself radially at 180 ° inwards and is fixed by a first clamping member 82 such as a collar on the first end 68, 70 of the sleeve. 64, 66. Said first clamping member 82 is thus interposed between the first end 78 folded and the remainder of the sheath 76. The second end 80 of the covering sheath 76, which is not folded down, is fixed by clamping by means of a collar 84, for example on the second free end 80 of the thermal protection sheath 74 surrounding the inner metallic sheath 60. Thus, according to the invention, the metal covering sheath 76 ensures a confinement of the heat-shrinkable sleeve 64, 66 limiting the supply of oxygen necessary for self-ignition of the heat-shrinkable sleeve 64, 66. The outer metallic covering sheath 76 also allows effective diffusion radially outwardly, which limits the heat concentration of the tubular metallic tip, preferably metal, at the sleeve 64, 66 and also at the wall 28. Although it does not there is no contact between the end portion 50 of the tubular nozzle 34 and the metal sheath 76, the sleeve 64, 66 ensures the diffusion of heat to the sheath 76 which radiates the heat outwards.
    [0012] Alternatively, it would be possible to attach the metal cover sheath 76 directly to the end portion 50 of the tip 34 to achieve better heat transfer. The embodiments of FIGS. 5 and 6 differ essentially in that the sleeve 64 bears externally on the clamping collar 20 in the case of the embodiment of FIG. 5 while the sleeve 66 is located at a distance from the collar 62 in FIG. the case of the embodiment of Figure 6, which avoids the wear of the sleeve 66 on the collar 62. The sleeve 64 of the embodiment of Figure 5 thus comprises an annular projection 86 which is not present in 6. The stacking of the 25 layers of the harness is simpler to achieve with the embodiment of FIG. 5 than with the embodiment of FIG. 6. In FIG. 6, the end of the first end 70 of the sleeve 66 extends radially inwards in the case of the embodiment of Figure 6 and extends cylindrically in the case of Figure 5. In addition, in the latter embodiment, the clamp 62 is not in contact with the mancho No. 66, which limits the friction of the sleeve on the collar 62 and consequently the wear of the sleeve 66. In the foregoing description, the choice of the materials of the metal covering sheath 76 and the endpiece tubular 34 is such that said metal covering sheath is made of a material whose thermal conductivity is greater than that of said tip. Preferably, the metal covering sheath 76 is made of a nickel-plated copper or copper-based alloy wire braid material, while the tubular ferrule is made of stainless steel.
    [0013] Thus, in operation, when heat is circulated by thermal conduction in the nozzle 34, the extraction of heat from the nozzle to the metal covering sheath 76 is facilitated. By heat exchange with the outside ambient air, the amount of heat flowing to the heat-shrinkable sleeve 64, 66 is substantially limited.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Assembly for the passage of an electrical harness through a wall (28) comprising a tubular metal ferrule (34) extending across the wall (28) and housing the electrical harness, a sleeve of heat-shrinkable material ( 38, 64, 66) extending around an end portion (40, 50) of the tubular nozzle (34) and the electrical harness, characterized in that it comprises means for extracting heat (42, 44, 46, 76) of the tubular tip which are arranged on the side of the tip (34) surrounded by the heat-shrinkable sleeve (38, 64, 66).
    [0002]
    2. Assembly according to one of the preceding claims, characterized in that the tubular nozzle (34) comprises an annular flange (36) applied on the wall (28) and disposed between the wall (28) and said extraction means heat.
    [0003]
    3. An assembly according to claim 1 or 2, characterized in that the heat extraction means comprise an outer metal sheath (46, 76) covering completely surrounding the heat-shrinkable sleeve (38, 64, 66) and fixed to a first end (78) located on the side of the wall by clamping on the tubular end (34).
    [0004]
    4. The assembly of claim 3, characterized in that said first end (78) of the covering metal sheath (76) is folded on itself radially inward and clamped by a first member (82) interposed radially between the first curved end (78) and the remainder of the covering metal sheath (76).
    [0005]
    5. An assembly according to claim 4, characterized in that a second member (84) clamping is applied to a second end (80) of the metal sheath (76) facing the opposite end to the first end (78) which is in contact with the heat-shrinkable sleeve (64, 66).
    [0006]
    6. An assembly according to one of claims 3 to 5, characterized in that said metal covering sheath (76) is made of a material whose thermal conductivity is greater than that of the tubular nozzle. 3034580 11
    [0007]
    7. Assembly according to one of claims 3 to 6, characterized in that the metal sheath (76) is a metal braid.
    [0008]
    8. Carter, in particular an intermediate casing for a turbomachine, comprising an assembly according to one of claims 1 to 7, wherein said wall is a substantially cylindrical wall (28) defining the radially internal flow surface of a gas flow.
    [0009]
    9. Turbomachine, such as a turbojet, characterized in that it comprises an assembly according to one of claims 1 to 7 or a housing according to claim 8.
    [0010]
    10
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3277542B1|2019-01-09|Passage assembly for a wire harness in a jet engine
    EP1857657B1|2012-09-19|Turbine accessory drive gearbox assembly in an airplane engine such as a jet engine
    CA2594146C|2014-11-25|Ventilation system for combustion chamber wall
    FR3020865A1|2015-11-13|ANNULAR CHAMBER OF COMBUSTION
    CA2891076C|2021-03-09|Air exhaust tube holder in a turbomachine
    FR3036442A1|2016-11-25|TURBOMACHINE COMPRISING A VENTILATION SYSTEM
    EP1607818B1|2007-01-10|Thermostatic valve for a cooling circuit
    CA2646976A1|2009-06-14|Bearing bracket sealed fitting in a turbine engine
    FR2943718A1|2010-10-01|FLUID HEATING DEVICE, ASSEMBLY METHOD AND CONNECTION SYSTEM FOR INCORPORATING AIR INTAKE PIPE OF GAS LEAKING PIPE.
    FR3053387B1|2019-07-05|TURBOMACHINE HOUSING
    FR3026572A1|2016-04-01|ASSEMBLING A SET OF ELECTRIC CABLES IN A TURBOMACHINE
    FR2903151A1|2008-01-04|Exhaust case ventilation device for e.g. aircraft`s jet engine, has slits delimiting blades that are supported on stiffener and freely deformable in radial direction under effect of differential thermal dilatation between case and trim
    FR3044704A1|2017-06-09|TURBOMACHINE HOUSING
    FR3047544A1|2017-08-11|TURBOMACHINE COMBUSTION CHAMBER
    EP3759319B1|2022-01-12|Assembly for a turbomachine
    EP3647636A1|2020-05-06|Control valve of a stream of fluid provided with an electrical actuator and system comprising such a valve
    FR3085188A1|2020-02-28|A TURBOCHARGER WITH AN AXIAL BEARING COOLING ARRANGEMENT
    WO2020065220A1|2020-04-02|Annular assembly for turbine engine
    FR3081623A1|2019-11-29|ELECTRICAL HARNESS FOR A TURBOMACHINE
    FR3076860A1|2019-07-19|SERVITUDE PASSAGE ARM FOR TURBOMACHINE
    WO2016198811A1|2016-12-15|Assembly for supporting an electric motor
    FR3113419A1|2022-02-18|DISTRIBUTOR OF A TURBOMACHINE TURBINE
    FR3092449A1|2020-08-07|Device for compressing a fluid driven by an electric machine with a compression shaft passing through the rotor
    FR3084141A1|2020-01-24|SET FOR A TURBOMACHINE
    FR3111666A1|2021-12-24|RECOVERED CYCLE AIRCRAFT TURBOMACHINE
    同族专利:
    公开号 | 公开日
    RU2696620C2|2019-08-05|
    RU2017131830A|2019-05-06|
    JP6784693B2|2020-11-11|
    US20180080385A1|2018-03-22|
    BR112017020187A2|2018-06-12|
    EP3277542B1|2019-01-09|
    EP3277542A1|2018-02-07|
    FR3034580B1|2018-11-09|
    US10436119B2|2019-10-08|
    CA2979476A1|2016-10-06|
    CN107408803A|2017-11-28|
    RU2017131830A3|2019-06-25|
    WO2016156706A1|2016-10-06|
    JP2018517087A|2018-06-28|
    CN107408803B|2020-04-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2000019082A2|1998-08-17|2000-04-06|Ramgen Power Systems, Inc.|Ramjet engine with axial air supply fan|
    US6359223B1|1999-08-11|2002-03-19|Avaya Technology Corp.|Method and apparatus for making a high-pressure seal using cold shrink tubing|
    FR2958373A1|2010-03-31|2011-10-07|Snecma|Combustion chamber for turbine engine e.g. turbo propeller, of airplane, has air passage openings inclined with respect to axis of chimney in axial direction and circumferential direction so as to form local stream of air on specific level|
    FR2990745A1|2012-05-21|2013-11-22|Snecma|Holding fixture for holding electric cables of turboshaft engine of aircraft, has fixing units fixed on fixed support, where fixing units maintain sleeves in position when fixing units are attached on fixed support|
    FR2990805A1|2012-05-21|2013-11-22|Snecma|Device for fixing electromagnetic protection shielding electric cable in opening connecting wall surfaces, has retainer body provided to be opened to receive sleeve in its passage and closed on sleeve to retain sleeve by geometrical locking|
    FR2996070A1|2012-09-21|2014-03-28|Snecma|Guidance system for electric cable in turbojet of aircraft, has arm extending approximately through seam and crossing opening associated with internal revolution casing and another opening associated with external casing|CN106051317A|2016-07-19|2016-10-26|郭舒珂|Plugging device|
    EP3483398A1|2017-11-08|2019-05-15|United Technologies Corporation|Jem igniter cable conduit and assembly method|
    US11230995B2|2017-11-08|2022-01-25|Raytheon Technologies Corporation|Cable conduit for turbine engine bypass|US3068315A|1960-01-25|1962-12-11|Gen Cable Corp|Joint for aluminum sheathed cables|
    US5906576A|1998-03-27|1999-05-25|Mercury Enterprises, Inc.|Light coupling assembly for use in a medical instrument, system and method|
    FR2891954B1|2005-10-12|2008-01-04|Hispano Suiza Sa|ELBOW FITTING FOR MULTIFIL ELECTRIC CABLE|
    JP4791251B2|2006-05-19|2011-10-12|矢崎総業株式会社|Harness wiring structure of swinging part|FR3076105B1|2017-12-21|2020-10-30|Latelec|HARNESS OUTLET ADAPTER OF A WIRING PATH AND METHOD FOR INSTALLING SUCH ADAPTER|
    CN112576409A|2020-12-03|2021-03-30|上海新力动力设备研究所|Combustion chamber shell of solid rocket engine|
    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-10-07| PLSC| Publication of the preliminary search report|Effective date: 20161007 |
    2017-03-14| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2019-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552763|2015-03-31|
    FR1552763A|FR3034580B1|2015-03-31|2015-03-31|ASSEMBLY FOR PASSING AN ELECTRIC HARNESS IN A TURBOMACHINE|FR1552763A| FR3034580B1|2015-03-31|2015-03-31|ASSEMBLY FOR PASSING AN ELECTRIC HARNESS IN A TURBOMACHINE|
    BR112017020187-9A| BR112017020187A2|2015-03-31|2016-03-24|? assembly for passing a harness through a wall, housing and turbine engine?|
    PCT/FR2016/050661| WO2016156706A1|2015-03-31|2016-03-24|Assembly for passing an electrical harness into a turbine engine|
    CN201680019292.0A| CN107408803B|2015-03-31|2016-03-24|Assembly for transferring a wire bundle into a turbine engine|
    JP2017551210A| JP6784693B2|2015-03-31|2016-03-24|Assembly for passing electrical harnesses inside the turbine engine|
    RU2017131830A| RU2696620C2|2015-03-31|2016-03-24|Device for passing electric bundle into gas turbine engine|
    EP16717674.2A| EP3277542B1|2015-03-31|2016-03-24|Passage assembly for a wire harness in a jet engine|
    CA2979476A| CA2979476A1|2015-03-31|2016-03-24|Assembly for passing an electrical harness into a turbine engine|
    US15/561,156| US10436119B2|2015-03-31|2016-03-24|Assembly for passing an electrical harness into a turbine engine|
    [返回顶部]