• 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 radial control shaft (48) for a device for controlling the orientation of the fan blades of a non-ducted fan turbomachine, the shaft comprising an external part (52) which is intended to be mounted in the control device from outside thereof and to be coupled to at least one fan blade (26) for adjusting its orientation, and an inner portion (50), independent of the outer portion, which is intended to to be mounted from the inside of the control device, to be connected to a motion transfer bearing (40) to rotate the shaft about a radial axis (ZZ), and to provide enclosure closure oil in which is housed said bearing, the outer and inner portions of the shaft being coupled to each other. The invention also relates to a method of mounting such a shaft and a control device comprising such a shaft.
    公开号:FR3036141A1
    申请号:FR1554280
    申请日:2015-05-12
    公开日:2016-11-18
    发明作者:Olivier Belmonte；Van Thomas Julien Nguyen；Emmanuel Pierre Dimitri Patsouris
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of turbomachines equipped with one or two non-ducted fan (s), and more particularly to the control of the orientation of the fan blades (s). ) of these turbomachines. A preferred field of application of the invention relates to jet engines with counter-rotating propellers, called "Open Rotors" in English, which comprise two counter-rotating propellers placed downstream ("pusher" version in English) or upstream ("puller" version in English). English) of the gas generator. However, the invention also applies to turboprop engines with one or more propulsive propellers. In a turbojet engine with contra-rotating propellers, it is known that the orientation (or wedging) of the blades that form these propellers is one of the parameters for managing the thrust of the turbojet, in particular by operating the propeller always in the best conditions possible. Indeed, the speed of the propellers is almost constant on all phases of operation, and it is the pitch of the propeller blades that varies the thrust. This setting allows in particular to operate the propeller in the best possible conditions. Thus, in the cruising flight phase, it is sought to obtain the lowest power possible on the turbine shaft which is necessary for a given traction at a given speed of the airplane, so as to obtain the best efficiency ( that is, the efficiency to minimize fuel consumption and increase the range. Conversely, on takeoff, the strongest possible traction is sought to accelerate and then take off the plane. The control mechanism of the orientation of the propeller blades of the turbojet engine is generally integrated inside the hub carrying the propellers. More specifically, the orientation of each blade constituting the propellers is typically controlled by a radial control shaft which passes through a housing arm coinciding with a blade axis and which comprises at its inner end a lever arm for controlling its rotation along this axis of wedging. A cylinder, fixed relative to the engine structures and centered on the longitudinal axis thereof, drives in translation the inner ring of a motion transfer bearing (called LTB for "Load Transfer Bearing") positioned in 3036141 2 the extension of the cylinder. This bearing makes it possible to transmit the translational movement of the fixed reference linked to the cylinder to a rotating reference linked to the blades. In addition, for each drive shaft, a pitch lock connecting rod connects the end of each lever arm to the outer ring of the motion transfer bearing 5. In particular, reference may be made to the document WO 2013/050704 which describes an example of implementation of such a command. This type of mechanism requires access to the hubs of the engine propellers for the assembly of the various elements that constitute it. However, for some turbojet engine architectures, in particular for jet engines with counter-rotating propellers in "pusher" version, this access is limited because the hubs are masked by the rotating housings which reconstitute the vein. Indeed, with this turbojet architecture, the radial control shafts must be engaged by the inside of the hub carrying the propeller through the casing arms and then coupled through splines with the blade roots. To achieve this, it is necessary that the space available inside the hub carrying the propeller has a diameter at least equivalent to the length of the control shafts.
    [0002] With the desired reduction of the diameter of the hubs of the turbojet propellers which improves the propulsive performance of the propellers, however, it becomes more and more difficult to introduce the control shafts from the inside of the hubs.
    [0003] OBJECT AND SUMMARY OF THE INVENTION The main object of the present invention is therefore to propose a control shaft for a device for controlling the orientation of the blades which does not have the abovementioned disadvantages. This object is achieved by means of a radial control shaft for controlling the orientation of the fan blades of a non-ducted fan turbomachine, said shaft comprising an external part which is intended to be mounted in the control device. from outside thereof and to be coupled to at least one blower blade for adjusting its orientation, and an inner portion, independent of the outer portion, which is to be mounted from within the device control, to be connected to a transfer transfer bearing 3036141 3 for pivoting said control shaft about a radial axis, and to ensure closure of an oil chamber in which is housed said motion transfer bearing, the outer and inner portions of the control shaft being coupled to each other.
    [0004] The use of a control shaft made in two parts independent of one another solves the problems associated with its introduction into the hub of the turbojet bearing the propeller. Indeed, the inner part of the control shaft (which carries the lever arm) can be engaged by the inside of the hub, even if it is of small diameter, while the outer part of the shaft can be introduced from outside the vein. The control shaft is thus perfectly compatible with the reduction of hub diameters of turbojet propellers. In addition, the inner portion of the control shaft remains in place in the hub carrying the helix, and thus acts as a stopper to the oil chamber in which is housed the motion transfer bearing and the cylinder of actuation of the control shafts, which reduces the risk of oil leakage from this enclosure. This oil chamber is in particular a critical point since it contains the elements of the device for controlling the orientation of the blades which require a high degree of lubrication and high oil flow rates (for the cylinder, the bearing bearings in rotation of the propellers with respect to the housing, the motion transfer bearing, etc.). Finally, since the outer portion of the control shaft is accessible from outside the vein, it is possible to remove it without having to first remove the rotating housings. Maintenance operations are simplified because it is not necessary to disassemble a complex set of mechanisms located in an oil chamber to disassemble the rotating ring on which the blade pivots are mounted. Thanks to this two-part control shaft, it is possible to separate the control device from the orientation of the blades of the fan blade assembly by dismantling the outer parts of the control shafts without having to disassemble the fan blades. or the rotating ring that drives them in rotation.
    [0005] The two independent parts of the shaft can be coupled to each other by splines of complementary shapes.
    [0006] Preferably, the inner portion of the shaft comprises a lever arm to be coupled to an outer ring of the motion transfer bearing and the outer portion of the shaft comprises a coupling system to at least one blade. blower.
    [0007] The inner part of the shaft is advantageously intended to be mounted through a hub casing with the interposition of a rolling bearing. Similarly, the outer portion of the shaft is preferably intended to be mounted on a rotating ring and held thereon by a nut. The nut being manipulable from the outside, it is possible to easily dismantle the outer part of the shaft from the outside. The invention also relates to a method of mounting a radial control shaft as defined above, comprising mounting the outer portion of the shaft in a control device from the outside thereof, the mounting the inner portion of the shaft in the control device from the inside thereof, and the coupling of the inner and outer portions of the shaft therebetween. The invention further relates to a device for controlling the orientation of the fan blades of a non-ducted fan-shaped turbomachine, comprising at least one set of adjustable-orientation fan blades, said assembly being rotationally secured to each other. a rotary ring, the fan blades being coupled, for adjusting their orientation, to at least one radial control shaft as defined above, the outer portion of each control shaft being coupled to at least one fan blade and the inner portion of each control shaft being mechanically connected to a motion transfer bearing for pivoting said drive shaft about its radial axis. Preferably, the rotating ring provides radial retention and free rotation of the outer portion of the control shaft. Also preferably, the device further comprises a hub housing which provides radial retention and free rotation of the inner portion of the drive shaft. BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate an exemplary embodiment without any limiting character. In the figures: - Figure 1 is a schematic longitudinal sectional view of a jet engine with contra-rotating propellers to which the invention applies; FIGS. 2 and 3 are views in longitudinal section of a control device in two different setting positions equipped with control shafts according to the invention; and - Figure 4 is a partial view of a control shaft of Figures 2 and 3 showing the coupling between the two parts thereof.
    [0008] DETAILED DESCRIPTION OF THE INVENTION The invention is applicable to any turbomachine equipped with at least one non-ducted fan, in particular turboprop engines with one or more propulsive propellers, as well as jet engines with counter-rotating propellers (called "Open" propellers). Rotor ") which comprise two counter-rotating propellers placed upstream (in" puller "version in English) or downstream (in" pusher "version in English) of the gas generator, such as the turbojet 2 of the" pusher "type represented by schematically in Figure 1.
    [0009] In known manner, the turbojet engine 2 comprises, from upstream to downstream in the direction of flow of the gas flow inside a nacelle 4 of the turbojet, one or two compressors 6 (according to the architecture of the gas generator single or double body), a combustion chamber 8, a high pressure turbine 10 (or a high pressure turbine and an intermediate pressure turbine according to said architecture), and a low pressure turbine 12 which drives contrarotatively by means of a gearbox or epicyclic gearbox 14, an upstream propeller 16 and a downstream propeller 18 which are aligned coaxially along the longitudinal axis XX of the turbojet and which are arranged downstream of the combustion chamber. For this purpose, the upstream propeller 16 is integral with a rotary ring 20 centered on the longitudinal axis XX of the turbojet and rotatably coupled to an output of the gearbox 14 to rotate in one direction, while the downstream propeller 18 is secured to another rotating ring 22 also centered on the axis XX and rotatably coupled to another output of the gearbox 14 to rotate in an opposite direction. The coupling between the gearbox outputs and the rotary rings of the propellers is known and is therefore not detailed here. Furthermore, the blades 26 of the upstream propeller 16 and the blades 28 of the downstream propeller 18 each have a foot which is mounted on a blade foot support 30, respectively 30, 32, these blade foot supports being as for them pivotally mounted on the rotary ring 20, 22 corresponding. Thus, a rotation of the blade foot supports around the axis of setting of the blades that they carry makes it possible to regulate the orientation of the latter (one also speaks of pitch change of the blades). The turbojet engine 2 also comprises a device for controlling the orientation of the blades of each propeller 16, 18. Such a device 16 for controlling the orientation of the blades 26 of the upstream propeller is shown schematically in FIGS. and 3. Of course, this device is equally applicable to the orientation of the blades of the downstream propeller of the turbojet engine. In known manner, the control device comprises in particular an annular jack 34 centered on the longitudinal axis X-X of the turbojet engine and a connecting mechanism connecting the cylinder to the bottom supports 30 of the blades 26 of the upstream propeller. The jack 34 surrounds a fixed annular casing 36 of the turbojet engine by being secured to it so that its static part (namely its rod) is immobilized in rotation and in translation relative thereto. As for the chamber 38 of the jack, it is able to move axially (that is to say along the longitudinal axis X-X) and is connected to the connecting mechanism. The link mechanism comprises in particular a motion transfer bearing 40 (called LTB for "Load Transfer Bearing") provided with an inner ring 42 mounted on the chamber 38 of the jack 34 and an outer ring 44, the inner and outer rings. external defining rolling tracks for bearings (here two rows of balls 46). In this way, an axial displacement of the chamber 38 of the cylinder causes a same translation of the motion transfer bearing along the longitudinal axis X-X. The jack 34 and the motion transfer bearing 40 are housed in an oil enclosure 47 delimited radially between the casing 36 3036141 7 and a casing hub 49 spaced radially outwardly relative to the casing. The linkage mechanism also comprises radial control shafts 48 (ie which are arranged radially with respect to the longitudinal axis XX of the turbojet), each control shaft being provided for adjusting the orientation (ie the step pitch) of at least one blade 26 of the upstream propeller. More precisely, the control shafts 48 may each extend along a radial axis ZZ which is offset axially and / or tangentially from the blade root (s) controlled by the shaft (see FIGS. 3 where the radial axis ZZ of the shaft is offset axially relative to the wedge axis 26 'of the blade 26). These control shafts 48 are able to be pivoted about their radial axis Z-Z while being integral in rotation with the rotary ring 20 driving the upstream propeller 15 in rotation. According to the invention, each control shaft 48 is composed of two parts independent of one another and coupled together, namely an inner portion 50 intended to be mounted by the inside of the hub casing 49, and an outer portion 52 to be mounted externally of the vein (i.e., on the rotating ring 20 side). More specifically, at their outer radial end, each control shaft 48 is coupled by its outer portion 52 to at least one blade root support 30 by any coupling means known per se. For example, reference may be made to the French patent application filed by the Applicant on May 12, 2015 with the title "Radial shaft device for controlling the orientation of the fan blades of a non-ducted fan turbomachine" which describes an example of such coupling kinematics between the control shafts 48 and the blade foot supports 30. Briefly, this patent application 30 describes a coupling in which each control shaft makes it possible to control the setting of at least two consecutive blades via eccentric led and leading. In this way, a pivoting of the control shafts 48 about their radial axis Z-Z causes a change in the pitch of the blades 26 of the upstream propeller.
    [0010] In addition, at their inner radial end, the inner portion 50 of each control shaft 48 includes a lever arm 54 which pivots with the drive shaft about its radial axis Z-Z. This lever arm 54 may be integral with or independent of the inner portion of the control shaft. The lever arms 54 are also coupled to the outer ring 44 of the motion transfer bearing 40, for example by means of a finger 56 carried by the lever arms and cooperating with a sliding ball 58 carried by the ring external 44 of the bearing. Reference may be made to the French patent application filed by the Applicant on May 12, 2015 with the title "Lever arm device for controlling the orientation of the fan blades of a non-ducted fan turbomachine" which describes an example of such a coupling between the lever arm and the outer ring of the transfer transfer bearing. Thus, as represented by the kinematics of FIGS. 2 and 3, when the actuator 34 is actuated, its chamber 38 will axially move the outer ring 44 of the motion transfer bearing, causing pivoting of the lever arms 54 and a corresponding pivoting of the 20 control shafts 48 about their radial axis ZZ, and subsequently a rotation of the blade root supports 30 in the rotary ring 20 which carries them. Of course, the linkage mechanism between the control shafts 48 and the motion transfer bearing 40 with the resulting kinematics could be different. For example, one could imagine resorting rods pitch pitch between the lever arm and the outer ring of the bearing as described in patent application WO 2013/050704. The inner portion 50 and the outer portion 52 of each control shaft 48 according to the invention are parts independent of each other. In particular, given its small size, the inner portion 50 can be mounted by the inside of the hub housing 49, even if it has a small diameter. In addition, when this inner portion is mounted on the hub housing, it acts as a plug to limit the risk of oil leakage from the oil enclosure 47.
    [0011] It will be noted that to allow retention and free rotation of the inner portion 50 of the control shafts with respect to the hub casing 49, a rolling bearing 60 can be inserted between these two elements.
    [0012] As for the outer portion 52 of the control shaft, it can be mounted by the outside of the vein, that is to say on the side of the rotary ring 20 by passing through a hole provided for this purpose in this, which avoids having to disassemble all the mechanisms of the oil chamber 47 when it comes to intervene for maintenance operations 10 only on the blade feet on the rotating ring. Maintaining the outer portion of the control shaft on the rotary ring 20 is effected for example by means of a nut 62 centered on the radial axis ZZ of the control shaft and clamped on the outer end of it.
    [0013] As for their internal part, it will be noted that in order to allow retention and free rotation of the outer part 50 of the control shafts with respect to the rotary ring 20, a rolling bearing 64 can be inserted between these two elements. bearing being held by clamping another nut 66 on the rotating ring. This nut 66 being advantageously accessible from the outside, it is thus easy to handle it from the outside to mount / dismount the outer portion of the control shaft. Furthermore, the retaining and free rotation system of the outer portion of the control shaft is advantageously positioned at a distance from the blade root supports 30 so that this external part can be mountable and dismountable independently of the blades. The inner portion 50 and the outer portion 52 of each control shaft 48 according to the invention are coupled together by any known mechanical coupling means.
    [0014] For example, as shown in more detail in FIG. 4, the outer portion 52 of the control shaft may carry on its outer periphery external splines 68 extending along the radial axis ZZ and co-operating with internal splines. 70 of complementary shapes carried by the inner portion 50 of the control shaft 35 so as to provide such a coupling.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Radial control shaft (48) for a device for controlling the orientation of the fan blades of a non-ducted fan turbomachine, said shaft comprising an external part (52) which is intended to be mounted in the control device by means of outside thereof and to be coupled to at least one blower blade (26, 28) for adjusting its orientation, and an inner portion (50), independent of the outer portion, which is to be mounted by inside the control device, to be connected to a motion transfer bearing (40) for pivoting said control shaft about a radial axis (ZZ), and to ensure a closure of an oil chamber in which is housed said motion transfer bearing, the outer and inner portions of the control shaft being coupled to each other.
    [0002]
    2. Shaft according to claim 1, wherein the two independent parts (50, 52) of the shaft are coupled to each other by splines (68, 70) of complementary shapes.
    [0003]
    3. Shaft according to one of claims 1 and 2, wherein the inner portion (50) of the shaft comprises a lever arm (54) intended to be coupled to an outer ring (44) of the transfer transfer bearing (40).
    [0004]
    4. Shaft according to any one of claims 1 to 3, wherein the outer portion (52) of the shaft comprises a coupling system to at least one fan blade.
    [0005]
    Shaft according to any one of claims 1 to 4, wherein the inner portion (50) of the shaft is intended to be mounted through a hub casing (49) with the interposition of a rolling bearing. (60).
    [0006]
    6. Shaft according to any one of claims 1 to 5, wherein the outer portion (52) of the shaft is intended to be mounted on a rotary ring (20) and held thereon by a nut (62). . 3036141 11
    [0007]
    A method of mounting a radial control shaft (48) according to any one of claims 1 to 6, comprising mounting the outer shaft portion (52) in an external control device. of the latter, mounting the inner portion (50) of the shaft in the control device by the interior thereof, and the coupling of the inner and outer portions therebetween.
    [0008]
    8. Device for controlling the orientation of the fan blades of a fanless turbomachine, comprising at least one set (16, 18) of fan blades (26, 28) with adjustable orientation, said assembly being secured to each other. rotating a rotary ring (20, 22), the fan blades being coupled, for adjustment of their orientation, to at least one radial control shaft (48) according to any one of claims 1 to 6, the outer portion (52) of each drive shaft being coupled to at least one fan blade and the inner portion of each drive shaft being mechanically connected to a motion transfer bearing (40) for pivoting said drive shaft around its radial axis (ZZ). 20
    [0009]
    9. Device according to claim 8, wherein the rotary ring (20, 22) provides radial retention and free rotation of the outer portion (52) of the control shaft. 25
    [0010]
    10. Device according to one of claims 8 and 9, further comprising a hub housing (49) which provides radial retention and free rotation of the inner portion (50) of the control shaft. 30
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    同族专利:
    公开号 | 公开日
    GB201607834D0|2016-06-22|
    GB2540246B|2020-04-08|
    FR3036141B1|2019-08-09|
    US10408069B2|2019-09-10|
    GB2540246A|2017-01-11|
    US20160333709A1|2016-11-17|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20130017087A1|2011-07-13|2013-01-17|Snecma|Device for controlling the pitch of turboprop fan blades|
    US20130052016A1|2011-08-26|2013-02-28|Aleksander Krzysztof Szymandera|Pitch control of contra-rotating airfoil blades|
    WO2013050704A1|2011-10-03|2013-04-11|Snecma|Turbo engine with propeller for an aircraft with a system for changing the pitch of the propeller|
    US3994128A|1975-05-21|1976-11-30|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Dual output variable pitch turbofan actuation system|
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    US5431539A|1993-10-28|1995-07-11|United Technologies Corporation|Propeller pitch change mechanism|
    US5533825A|1994-11-14|1996-07-09|General Electric Company|Parabolically helical spline shaft coupling|
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    FR2946011B1|2009-05-29|2013-01-11|Snecma|MOBILE ROLLER DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR|
    FR2946010B1|2009-05-29|2011-06-24|Snecma|FIXED CYLINDER DEVICE FOR CONTROLLING BLOWER BLADES OF A TURBOPROPULSER|
    FR2946012B1|2009-05-29|2011-06-24|Snecma|DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR|
    FR2956377B1|2010-02-12|2012-09-14|Snecma|DEVICE FOR CREMALLER CONTROL OF THE ANGULAR POSITION OF TURBOMACHINE SWIVELING BLADES|
    US8336290B2|2010-09-30|2012-12-25|General Electric Company|Pitch change apparatus for counter-rotating propellers|
    FR2977367A1|2011-06-30|2013-01-04|St Microelectronics Crolles 2|TRANSISTORS INCLUDING THE GRID COMPRISING A TITANIUM NITRIDE LAYER AND METHOD FOR DEPOSITING THE SAME|
    US20140029458A1|2012-07-24|2014-01-30|Acer Incorporated|Apparatuses and methods for signaling coordinated multi-point measurement configuration|
    FR3001264B1|2013-01-18|2017-03-17|Snecma|SYSTEM FOR CHANGING THE PITCH OF THE BLADES OF A PROPELLER.|FR2980770B1|2011-10-03|2014-06-27|Snecma|AIRBORNE TURBINE ENGINEFOR AIRCRAFT WITH SYSTEM FOR CHANGING THE PROPELLER STEP.|
    FR3055310B1|2016-08-26|2018-08-17|Safran Aircraft Engines|TURBOMACHINE WITH OIL GUIDING DEVICE AND METHOD OF DISASSEMBLING THE TURBOMACHINE|
    FR3074476B1|2017-12-06|2020-12-25|Safran Aircraft Engines|AIRCRAFT TURBOPROPELLER CONTAINING A NON-FAIRED PROPELLER|
    法律状态:
    2016-05-25| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-18| PLSC| Search report ready|Effective date: 20161118 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    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
    FR1554280|2015-05-12|
    FR1554280A|FR3036141B1|2015-05-12|2015-05-12|RADIAL CONTROL SHAFT FOR DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A NON - CARBENE BLOWER TURBOMACHINE AND METHOD FOR MOUNTING SUCH A SHAFT.|FR1554280A| FR3036141B1|2015-05-12|2015-05-12|RADIAL CONTROL SHAFT FOR DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A NON - CARBENE BLOWER TURBOMACHINE AND METHOD FOR MOUNTING SUCH A SHAFT.|
    GB1607834.7A| GB2540246B|2015-05-12|2016-05-05|A radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, and a method of mounting such a shaft|
    US15/150,832| US10408069B2|2015-05-12|2016-05-10|Radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, and a method of mounting such a shaft|
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