• 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 (10) comprising: - at least one hollow guide arm (44) extending radially from a hub (38) to an annular casing (42), and having a radially outer end which opens on an opening (60) of said annular housing, - a radial deflection shaft (48) located in said guide arm (44) and intended to drive in rotation at least one equipment arranged at the periphery of said annular housing (42), invention, a transfer case (50) is arranged facing the opening (60) of the annular housing, and the turbomachine comprises means (78, 52) for transferring power between the radial return shaft ( 48) and the equipment, the guide arm (44) being provided, at its outer end, with an enlarged portion (56) through which it opens onto the opening (60) of the annular housing and in which is housed a part of the transfer case (50).
    公开号:FR3022301A1
    申请号:FR1455346
    申请日:2014-06-12
    公开日:2015-12-18
    发明作者:Jean-Baptiste Etienne Bernard Lepretre
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a turbomachine comprising a drive system of an equipment such as an accessory box of the turbomachine. Conventionally, an accessory box is an equipment used to support and mechanically drive other equipment called accessories, such as electric generators, oil or fuel pumps, or other, necessary for the operation of the turbine engine or to that of the aircraft on which the turbomachine is mounted. In order to ensure this drive, the required power is taken from a main shaft of the turbomachine, generally by means of a radial gear shaft meshing with the main shaft, to mechanically transmit this power to the accessory box.
    [0002] A double-body turbojet engine comprises two coaxial shafts, one said to be low pressure or LP, connecting the low pressure compressor to the low pressure turbine and forming the BP body together, the other, said high pressure or HP, connecting the compressor high pressure to the high pressure turbine and together forming the HP body. In the case of such a motor, the radial return shaft is generally housed in a structural support arm of an annular casing through which the secondary flow flows, this annular casing being generally called an intermediate casing. A radially inner end of the radial return shaft generally comprises a conical pinion cooperating with a pinion integral with the main shaft formed by the high-pressure body. The other end is mechanically connected to the accessory box comprising a plurality of gears ensuring the drive of other equipment, that is to say the accessories. When the engine is double-flow, the radial return shaft passes through the two primary flow and secondary flow veins respectively because the accessory gearbox, also called AGB for "Accessory Gear Box", is generally mounted externally on the crankcase. of the fan generating the secondary flow. The aircraft manufacturer may specify to mount the accessory box in the angular sector of six hours, or about eight hours of the turbomachine. In order to allow the training of ancillary equipment that constitutes accessories, it is common, as illustrated by publication FR2971816A1 and in particular with reference to FIG. 2 of this publication, to form a first structural arm at six o'clock, having a role intermediate casing support and connecting the hub of the turbomachine to the intermediate casing, a second structural arm similar to twelve hours, and a third structural arm directed within eight hours or four hours, the third arm being dedicated to the passage of a return shaft to an accessory box arranged in the extension of the shaft. The structural arms also serve to guide pipes and harnesses between a central compartment and a fan compartment of the turbomachine. However, this case involves therefore forming at least three radial arms through at least the secondary vein of the turbomachine, without the need for a particular positioning symmetry, such as for example the arms 44 shown in FIG. the current. However, it has been shown that the presence of at least three arms, as in the case above, destabilizes the flow flow and creates disturbances, which reduces the aerodynamic performance of the turbomachine. In order to optimize the flow of at least the secondary flow, the applicant has sought to retain only two structural support arms of the intermediate casing, one to twelve hours, the other to six hours. These two arms are positioned symmetrically in the flow flow veins, and are less disruptive than mounting involving three or more arms, which ultimately improves the aerodynamic performance of the turbomachine. For reasons of vertical size of the turbomachine, the accessory box is arranged in a direction relatively angularly distant arm of six hours and twelve hours, for example about eight hours of the turbomachine. In this case, the arm at six o'clock accommodates not only pipes and harnesses but also the radial shaft used to drive equipment such as an accessory box and thus ultimately equipment training. auxiliaries formed by accessories. A major difficulty, however, hinders the realization of a configuration as described above. Indeed, such an embodiment necessarily involves the establishment of power transfer means outside the intermediate casing, between the radially outer end of the radial shaft formed at six hours of the turbomachine and the casing 'accessories formed about eight hours from the turbomachine. These means necessarily involve the presence of bulky parts, used in particular to resume the rotation of the radial deflection shaft to transfer it, along another axis, for example substantially tangential to the intermediate casing of the turbomachine, to the accessory box. These parts will take the form of a conical pinion, for example, in engagement with the radial deflection shaft, and capable of being connected to a tangential transfer shaft, and will also have to be in a lubricated fixed enclosure allowing precise positioning of the bearings. pieces between them. In the case concerned here, the nacelle which surrounds, maintains and protects the turbomachine, and whose dimensions are imposed by the aircraft manufacturer, leaves only a very small radial space within six hours of the turbomachine between the intermediate casing. and a bonnet of the nacelle, to limit the vertical size of the nacelle. The implementation of the means of transfer is not obvious and requires a thorough reflection on their integration. The present invention thus provides a simple, effective and economical solution for integrating the aforementioned transfer means.
    [0003] To this end, it proposes a turbomachine, such as a turbojet engine or a turboprop engine, extending along an engine axis and comprising: at least one hollow guide arm extending radially with respect to the engine axis from a hub up to an annular casing of the turbomachine, and having a radially outer end which opens on an opening of said annular casing, - a radial return shaft located in said guide arm and intended to drive in rotation at least one equipment arranged at the periphery said annular casing, characterized in that it further comprises a transfer case arranged opposite the opening of the annular casing and comprising means for transferring power in rotation between the radial return shaft and the equipment, and in that the guide arm is provided at its radially outer end with an enlarged portion through which it opens on the opening of the annular housing and in which e is housed a part of the transfer case. In the present case, a guide arm of an intermediate casing is a structural arm for supporting the intermediate casing that can be used for the passage of electrical harnesses and ducts, or even for the passage of a radial deflection shaft.
    [0004] The invention thus makes it possible to adapt a guide arm of an intermediate casing so that it can receive at its radially outer end at least a portion of the transfer casing. While the section of a guide arm is usually only dimensioned to accommodate at most a deflection shaft as well as harnesses and pipes, the guide arm here has a radially outer hollow portion of larger section, so widened, arranged inside the intermediate casing, and which has the space necessary to accommodate a part of the transfer case. The transfer case is thus positioned partially radially inside the intermediate casing, which allows the housing to be installed in the small radial space left outside the casing to a hood of the nacelle, and therefore responds to the integration problems mentioned above. In addition, the invention makes it possible to shorten the length of the return shaft, since the latter is then connected to the transfer means at a shorter radial distance with respect to the central axis of the turbomachine.
    [0005] This aspect is particularly advantageous because it makes it possible to make the following modifications to the turbomachine: either the increase in the critical speed of rotation of the return shaft, as a result of the reduction in length of the shaft and without increasing the diameter of the shaft, which improves the margins of safety of the operation of the turbomachine, or to increase the operating speed of the turbomachine without the shaft rotation exceeds the critical speed and therefore without risking any particular damage to the tree; or reducing the diameter of the countershaft, while maintaining its original rotational speed of rotation, which makes it possible to reduce the size of the section of the guide arm along its length, except for the enlarged portion, and then improves the aerodynamic performance of the turbomachine. Preferably, the turbomachine is double flow, and the guide arm passes through a secondary flow stream of the turbomachine. Preferably, the rotational power transfer means of the transfer case comprise a hollow shaft comprising: internal splines at a radially inner end of the hollow shaft, said splines being engaged between outer splines formed at a radially outer end; of the countershaft, and a conical pinion coaxial with the hollow shaft, the hollow shaft of the transfer case being held by bearings disposed inside an enclosure of the transfer case, said enclosure being positioned partly in the enlarged portion of the guide arm radially inside the annular housing.
    [0006] In a particular embodiment, the enclosure of the transfer case comprises a main part and a connecting part sealingly connected to the main part, and at least one of said bearings is positioned at an opening of the main part. on which the connecting part connects. According to another feature, at least one of said bearings is partly radially at the opening of the annular housing. The entire structure of the transfer case has thus been brought closer to the central axis of the turbomachine, taking advantage of the space available in the enlarged portion of the guide arm. Advantageously, the enclosure of the transfer case comprises an opening through which the hollow shaft of the transfer case extends, said opening being sealingly connected to the enlarged portion of the guide arm, so as to form a single sealed cavity. comprising the interior of the guide arm and the interior of the enclosure. Sealing means connecting the chamber to the guide arm may advantageously be arranged inside the annular casing of the turbomachine. This sealing between the guide arm and the housing of the transfer case allows in particular the establishment of a common lubrication circuit between the guide arm and the transfer case, in which shafts are rotated from solidarity way. According to another characteristic of the invention, the radially outer end of the radial return shaft is located radially inside the casing of the turbomachine. The countershaft is therefore shorter than in the prior art, where it extends radially beyond the casing of the turbomachine. From this follows the advantages already mentioned above. Advantageously, the enlarged portion of the guide arm may comprise at least one flange fixed to the casing of the turbomachine from the inside. This flange makes it possible to position and fix the guide arm relative to the casing of the turbomachine, which ensures its structural maintenance in the turbomachine. Advantageously, the turbomachine further comprises an oil draining circuit of the transfer case, in which at least two oil recovery pumps are connected respectively to two oil discharge orifices, each passing through a bottom wall of the engine. transfer case. These two oil discharge orifices are preferably spaced apart from each other in a transverse direction of the turbomachine. These pumps allow the oil to be drained from the oil circuit, regardless of the position and inclination of the turbomachine in operation. Indeed, when the turbomachine is embarked on an aircraft, depending on the flight phase, the turbomachine may be inclined to one side or the other relative to the horizontal. Depending on its flight phase, the pumps can either drain oil simultaneously or alternately.
    [0007] The turbomachine will comprise in a preferred case two guide arms extending substantially radially from two opposite sides of the hub to the annular casing of the turbomachine, the transfer case being disposed radially outwardly with respect to one of the arms guidance.
    [0008] Preferably, the two opposite guide arms are respectively an upper guide arm and a lower guide arm extending substantially vertically, the transfer case being disposed under the lower guide arm. A transfer shaft may connect in rotation the transfer case to an accessory box of the turbomachine disposed at the periphery of the annular casing of the turbomachine in an angular sector different from the angular sectors where the two opposite guide arms are located, namely the upper guide arm and the lower guide arm. This ensures the training of equipment connected to the accessory box, while the latter is not located with respect to the radial shaft. Advantageously, the accessory box can carry an electrical generator driven by the radial shaft, in particular via the transfer means and the tangential transfer shaft. This generator makes it possible to convert the kinetic energy produced by the turbomachine into electrical energy, available for example for an airplane carrying the turbomachine. The electric generator is for example driven directly by a rotary accessory arm of the accessory box. According to a particular embodiment, an annular space is formed between the casing and a nacelle inside which the turbomachine is arranged, said annular space being radially smaller in size at the angular sector where the transfer case is located than at the level of the angular sector in which is located said at least one rotated equipment, this equipment may for example be auxiliary equipment such as an electric generator and mounted on an accessory box so that the assembly has a radial size much larger than that of the transfer case. Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is, in axial section, a general view of a turbomachine with double flow and double body according to a known prior art; Figure 2 is a view downstream of an intermediate casing used in the turbomachine of Figure 1; FIG. 3 is a diagram, from the upstream, of a propulsive overall architecture, with the turbomachine; FIG. 4 is a more detailed view of the transfer case of FIG. 3, and of the outer end of the guide arm, in which the drive return arm extends from the equipment of the accessory box, in axial section. . A known dual flow turbomachine 10 with its various main components is illustrated schematically in FIG. 1. It comprises a first shaft 12 connecting, upstream, a fan rotor 14 and the first stages 16 of the compressor to the low-pressure turbine 18; the whole forms the body low pressure, or BP. Coaxial with the first shaft, a second shaft 20 in the form of a drum connects the high pressure stages 22 of the compressor to the high pressure turbine 24; the assembly forms the high pressure body, or HP, with the combustion chamber (not shown). The shaft 12 is supported, upstream, by the bearings 26 and 26 'mounted on the casing 28 which is designated as an intermediate casing and, downstream, by the bearing 30 mounted on the exhaust casing 32. HP shaft is supported here by the bearing 34 of the intermediate casing 28 and downstream of the shaft 12 via the inter-shaft bearing 36. As illustrated in Figures 1 and 2, the intermediate casing 28 comprises a ferrule outside 40 in the extension of the fan casing 42. Radial guide arms 44 connect the ferrule 40 to a hub 38 supporting the bearings 26, 26 'and 30, This intermediate casing 28 consists at least in part of a part of foundry on which the radial arms were eventually reported. Auxiliary equipment, such as electric generators and fuel or oil pumps, is mounted on an accessory housing 46, as is known, which is referred to in the art as AGB. The accessory box 46 is mounted outside on the fan casing 42 at a location which allows access for maintenance, in an angular sector of the turbomachine 10 corresponding to about eight hours of the latter. The turbomachine is indeed intended to be mounted in a particular orientation, with a high part corresponding to twelve hours, and a lower part corresponding to six hours. The equipment is mechanically connected to a central shaft 12, 20 of the turbomachine by means of a radial return shaft 48, which is housed in a radial guide arm 44 of the intermediate casing 28 extending in the angular sector of the approximately eight hours, directly in the direction of the accessory box 46. Two other guide arms 44 of the intermediate casing 28 extend in the sectors of twelve hours and six hours, and serve for example to guide electrical harnesses and pipes fuel, oil, etc. Such a structure comprising more than two guide arms 44 on the intermediate casing 28 has the drawbacks mentioned above.
    [0009] The invention thus proposes a solution illustrated by FIGS. 3 and 4. It can be seen in FIG. 3 that only two guide arms 44 of the intermediate casing 28 have been kept at twelve o'clock and at six o'clock, which improves the flow of the flow at least in the secondary vein of the turbomachine, and thus improves the aerodynamic performance. The turbomachine is here with double flow, and each guide arm passes through a vein of secondary flow of the turbomachine. In order to mechanically connect a central shaft of the turbomachine to at least one piece of equipment, in this example to a set of equipment mounted on an accessory box 46 which is in the eight hour sector, the shaft of radial return 48 in the guide arm 44 six hours. The outer end of this deflection shaft 48 is connected to a transfer case 50, the function of which is to transfer the rotational movement of the deflection shaft 48 in the direction of the accessory box 46, via of a transfer shaft 52, for example substantially tangential to the fan casing 42, and connecting the transfer case 50 to the accessory box 46. Note that the radial return shaft 48 is not necessarily perpendicular to the central shaft of the turbomachine, and can form an angle relative to a strictly radial direction that is to say perpendicular to the central shaft, as can be seen in Figure 4. At least one equipment, not shown on the figure and comprising for example an electric generator, is mounted on the accessory box 46, so that the assembly constituted by the accessory box and the equipment has a radial size much larger than that of ui transfer case. These differences in radial dimensions of the members around the annular fan casing 42 lead to the fact that a nacelle 54 accommodating the turbomachine 10 will preferably have a non-axisymmetric shape, as can be seen in FIG. 3 and detailed below. Furthermore, it is understood that instead of an accessory box, it is possible to have an isolated equipment, for example an electric generator. It is also conceivable that the isolated equipment is constituted by another transfer case, remote from the transfer case 50 and which leaves at least one transfer shaft to drive more distant equipment.
    [0010] In the present case, the casing 42 is considered as an annular casing which comprises the fan casing and the outer casing of the intermediate casing. This annular casing 42 is not necessarily cylindrical, and may therefore have a diameter that varies as a function of the longitudinal position considered in the direction of the central axis of the turbomachine. Furthermore, as can be seen in FIG. 3, dimensional constraints are imposed by the nacelle 54 accommodating the turbomachine 10. In particular, the nacelle 54 has a distance to the central axis of the turbomachine which varies in the peripheral direction . More particularly, the nacelle surrounds the annular housing 42 of the turbomachine so as to leave an annular space of variable radial dimension all around this annular housing. In order to reduce the overall height of the nacelle, the radial space available at six hours from the turbomachine, for the transfer case, is relatively small, and therefore made it necessary to develop a particular solution for producing the case. 50, shown in detail in Figure 4. It is seen in Figure 4 that the six-hour guide arm 44, which is hollow, and in which extends the radial deflection shaft 48, has at its end radially outer an enlarged portion 56 by which it is connected to the fan casing 42 of the turbomachine from the inside. This enlarged portion 56, also hollow, thus forms a cavity, or a housing 58, in the outer end of the guide arm. More particularly, the wall defining the guide arm 44, away from the axis A of the deflection shaft 48 at its outer end relative to the central axis of the turbomachine, before connecting to the housing blower 42 all around an opening 60 of the annular housing 42 formed for the passage of the deflection shaft 48. In this way, the enlarged portion 56 opens on the opening 60 of the annular housing. A flange 62 is formed on the wall of the guide arm 44 and bears against the fan casing 42 from the inside, to allow attachment therein. The outer end 64 of the deflection shaft 48 is formed at the widening 56, at a radial distance from the central axis of the turbomachine shorter than the radius of the fan casing 42. The outer end 64 the deflection shaft 48 includes longitudinal grooves 66 formed on its outer surface.
    [0011] The transfer case 50 is arranged partly in the opening 60 of the fan casing 42 and in the cavity 58 of the guide arm 44 formed by the widened portion 56. The transfer case 50 comprises a fixed external enclosure 68 which comprises a main portion 68A and a connecting portion 68B sealingly connected to the main portion 68A. This junction portion 68B serves to connect the enclosure 68 to the widened portion 56 of the guide arm, and has an opening for example circular delimited by a cylindrical wall 70 surrounded by an annular seal 72. This opening is arranged inside. a coaxial cylindrical wall 74 formed projecting on the widened portion 56 of the guide arm, so as to seal the seal 72 between the two cylindrical walls 70, 74. Thus, the cavity inside the guide arm 44, where the deflection shaft 48 extends, and the cavity inside the enclosure communicate to seal. Inside the enclosure 68 is maintained, by a series of bearings 76, a hollow shaft 78 of the same axis A as the axis of the deflection shaft 48. The end 80 of the hollow shaft 78 directed towards the central axis of the turbomachine is formed around the splined end 64 of the deflection shaft 48, in the guide arm 44. More particularly, longitudinal grooves 82 are formed on the inner wall of the hollow shaft 78 and engage between the splines 66 of the deflection shaft 48, to secure the two shafts 48, 78 in rotation. At the other end of the hollow shaft 78, away from the central axis of the turbomachine, is formed a conical pinion 84. On assembly, the connecting portion 68B is connected to the main portion 68A of the enclosure 68 a once the aforementioned elements of the transfer case 50 have been put in place in the enclosure 68.
    [0012] The bearings 76 are ball or roller, and serve to guide the hollow shaft 78 in rotation in the enclosure 68 of the transfer case 50. A roller bearing and a ball bearing are formed around the hollow shaft 78 between the flutes 82 and the bevel gear 84, and a roller bearing surrounds an end portion 86 of the hollow shaft 78 which extends radially more radially than the bevel gear 84. It will be noted that the bearing 76 located closest to the central axis of the turbomachine is located in part at the opening 60 of the fan casing 42. More particularly, this bearing 76 can be positioned at an opening of the main portion 68A of the enclosure 68 on which the connecting portion 68B connects. Two orifices 88 are each formed in a bottom wall 680 of the enclosure 68 of the transfer case 50, and are spaced from each other in a transverse direction of the turbomachine. In this way, in almost all the attitudes of the flight range of the aircraft equipped with the turbomachine, and especially in the event of a turn even with a large angle, at least one of the two orifices 88 constitutes a low point of the enclosure 68 These two orifices 88 serve to drain the oil circulating in the enclosure and the guide arm 44 to lubricate and cool the bearings. At least two oil recovery pumps 90 are respectively connected to the two oil discharge orifices 88 to produce an oil draining circuit of the transfer case 50, thus allowing the oil to be drained in all the attitudes of the engine. flight domain. The pumps 90 drain oil either simultaneously or alternately according to the attitudes of the flight area. It is conceivable to provide at least one other orifice 88 associated with an additional dedicated recovery pump. In the figure, the two orifices 88 being located one behind the other, a single orifice is shown. The tangential transfer shaft 52 can easily be engaged with the conical pinion 84 of the hollow shaft 78 of the transfer case 50, through an opening of the transfer case that is not visible in the figure, because oriented perpendicularly to the plane of section of Figure 4, so as to achieve the assembly of Figure 3.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Turbomachine (10), such as a turbojet engine or a turboprop engine, extending along a motor axis and comprising: - at least one hollow guide arm (44) extending radially with respect to the motor shaft from a hub ( 38) to an annular housing (42) of the turbomachine, and having a radially outer end which opens out an opening (60) of said annular housing, - a radial deflection shaft (48) located in said guide arm (44). ) and intended to drive in rotation at least one equipment arranged at the periphery of said annular housing (42), characterized in that it further comprises a transfer housing (50) arranged opposite the opening (60) of the annular housing and comprising rotational power transfer means (78, 52) between the radial return shaft (48) and the equipment, and in that the guide arm (44) is provided at its radially outer end with of an enlarged portion (56) by which it opens onto the opening (60) of the annular housing and wherein is housed a portion of the transfer housing (50).
    [0002]
    2. A turbomachine according to claim 1, wherein the means (76, 78) for transferring power of the transfer case (50) comprises a hollow shaft (78) comprising: - internal grooves (82) at one end radially. interior (80) of the hollow shaft, said splines being engaged between outer splines (66) formed at a radially outer end (64) of the countershaft (48), and a conical gear (84) coaxial with the hollow shaft, the hollow shaft (78) of the transfer housing being held by bearings (76) disposed within a housing (68) of the transfer housing, said enclosure being positioned partly in the enlarged portion (56) of the guide arm (44) radially inside the annular housing (42).
    [0003]
    The turbomachine according to claim 2, wherein the housing (68) of the transfer case comprises a main portion (68A) and a joint portion (68B) sealingly connected to the main portion (68A), and at least one one of said bearings (76) is positioned at an opening of the main portion (68A) on which the joining portion (68B) connects.
    [0004]
    4. A turbomachine according to one of claims 2 or 3, wherein at least one of said bearings (76) is located partly radially at the opening (60) of the annular housing (42).
    [0005]
    5. Turbomachine according to one of claims 2 to 4, wherein the housing (68) of the transfer housing comprises an opening (70) through which extends the hollow shaft (78) of the transfer case (50). ), said opening being sealingly connected to the enlarged portion (56) of the guide arm, so as to form a single sealed cavity comprising the interior of the guide arm (44) and the inside of the enclosure, means sealing device (72) connecting the enclosure to the guide arm being disposed inside the annular housing (42) of the turbomachine.
    [0006]
    6. Turbomachine according to one of the preceding claims, wherein the radially outer end (64) of the radial return shaft (48) is located radially inside the annular housing (42) of the turbomachine.
    [0007]
    7. A turbomachine according to one of the preceding claims, comprising an oil draining circuit of the transfer case (50), wherein at least two oil recovery pumps (90) are respectively connected to two orifices (88). ) of oil discharge each passing through a bottom wall (680) of the transfer housing and spaced apart from each other in a transverse direction of the turbomachine.
    [0008]
    8. A turbomachine according to one of the preceding claims, comprising an upper guide arm and a lower guide arm (44) extending substantially vertically from two opposite sides of the hub (38) to the annular housing (42) of the turbomachine, the transfer case (50) being arranged under the lower guide arm (44), in which a transfer shaft (52) rotatably connects the transfer case (50) to an accessory box (46) of the turbomachine disposed at the periphery of the annular casing (42) of the turbomachine in an angular sector different from the angular sectors where are located the upper guide arm and the lower guide arm (44).
    [0009]
    9. A turbomachine according to claim 8, wherein the accessory box (46) carries an electric generator driven by the radial return shaft (48), via the transfer means (76, 78) and the transfer shaft (52).
    [0010]
    10. Propulsion unit comprising a turbomachine (10) according to one of the preceding claims, which is arranged inside a nacelle (54), an annular space being formed between the housing (42) of the turbine engine and the nacelle , said annular space being radially smaller in dimension at the angular sector where the transfer housing (50) is located than at the angular sector in which is located at least one equipment driven in rotation.
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    同族专利:
    公开号 | 公开日
    US9982556B2|2018-05-29|
    CA2951196A1|2015-12-17|
    CN106662018B|2019-05-31|
    BR112016028953A8|2021-06-22|
    RU2681391C2|2019-03-06|
    EP3155234A1|2017-04-19|
    RU2016147732A3|2019-01-09|
    BR112016028953A2|2017-08-22|
    CN106662018A|2017-05-10|
    RU2016147732A|2018-07-12|
    FR3022301B1|2016-07-29|
    EP3155234B1|2018-05-23|
    US20170122122A1|2017-05-04|
    WO2015189522A1|2015-12-17|
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    法律状态:
    2015-06-12| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-18| PLSC| Search report ready|Effective date: 20151218 |
    2016-06-08| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-06-05| PLFP| Fee payment|Year of fee payment: 5 |
    2019-05-22| PLFP| Fee payment|Year of fee payment: 6 |
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    2021-05-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1455346A|FR3022301B1|2014-06-12|2014-06-12|TURBOMACHINE COMPRISING A DRIVE SYSTEM OF AN EQUIPMENT SUCH AS AN ACCESSORY HOUSING|FR1455346A| FR3022301B1|2014-06-12|2014-06-12|TURBOMACHINE COMPRISING A DRIVE SYSTEM OF AN EQUIPMENT SUCH AS AN ACCESSORY HOUSING|
    RU2016147732A| RU2681391C2|2014-06-12|2015-06-11|Turbine engine containing system of drives for such device as accessory-gear box|
    US15/317,335| US9982556B2|2014-06-12|2015-06-11|Turbine engine comprising a drive system for a device such as an accessories case|
    BR112016028953A| BR112016028953A8|2014-06-12|2015-06-11|turbomachine and powertrain|
    EP15732861.8A| EP3155234B1|2014-06-12|2015-06-11|A turbine engine comprising a drive system for a device such as an accessories case|
    CN201580031234.5A| CN106662018B|2014-06-12|2015-06-11|A kind of includes the turbogenerator for the drive system of the devices such as accessory case|
    PCT/FR2015/051547| WO2015189522A1|2014-06-12|2015-06-11|A turbine engine comprising a drive system for a device such as an accessories case|
    CA2951196A| CA2951196A1|2014-06-12|2015-06-11|A turbine engine comprising a drive system for a device such as an accessories case|
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