• 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 steerable blade pivot (16) for a turbomachine fan hub (18), comprising a stud (22) having coupling means (26) for transmitting a torque and a external thread (28), a force decoupling piece (30) positioned around the stud, provided with an external thread (34), in transverse support (F2) against the stud at its outer radial end, a bearing external bearing (38) having an inner ring (42) mounted in transverse support against the force decoupling part, an inner rolling bearing (40) mounted around and held by the force decoupling member, a ring stall transmission (52) provided with coupling means (54) cooperating with the coupling means of the stud, a first clamping nut (36) screwed onto the external thread of the decoupling piece of forces to ensure a clamping rolling bearings outside and i ntérieur around the fan hub, and a second clamping nut (56) screwed on the external thread of the stud to ensure a clamping between them of the stud, the decoupling piece of the forces and the ring of stall transmission.
    公开号:FR3046403A1
    申请号:FR1650040
    申请日:2016-01-05
    公开日:2017-07-07
    发明作者:Olivier Belmonte；Christophe Paul Jacquemard；Clementine Charlotte Marie Mouton；Emmanuel Pierre Dimitri Patsouris
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to the general field of turbomachines equipped with one or two fan (s) ducted (s) or not careened (s), and more particularly to the control of the orientation of the fan blades (s) of these turbomachinery.
    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 propeller-driven turbojet engine, it is known that the orientation (or wedging) of the blades that form these propellers constitutes one of the parameters making it possible to manage the thrust of the turbojet engine, in particular by still operating the propeller in the propellers. 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. 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.
    Typically, each propeller comprises several fan blades which are each composed of an aerodynamic profile and a pivot. The pivots fulfill several functions: by means of rolling bearings, they ensure the retention of the fan blades in operation and the guiding of these for the setting of their pitch.
    Moreover, for "Open Rotor" turbojet engine architectures in the "puller" version, the turbojet engine constitutes in itself an oil enclosure which it is necessary to seal (or to control leaks). However, on the known systems of fan blade pivots, the structure located below the propeller is not an enclosure, this sealing function is not ensured.
    In addition, with the known systems of pivots, it is necessary to open the casing located upstream of the propeller to be able to disassemble the pivots and perform maintenance on the blades. However, when it is a turbojet type "Open Rotor" version "puller", this maintenance operation is particularly tedious since it is necessary to redo the entire installation of the oil enclosure, and its pressurization. In addition, the presence of two propellers, equipped with their rotating drive shafts and their control systems of the blade orientation, greatly limits access to the pivots of the fan blades. Also, when it is necessary to perform a maintenance operation on a single aerodynamic profile of the downstream fan blade, the engine removal becomes mandatory and the entire upstream propeller must be dismantled with its systems, as well as the control systems of the downstream propeller.
    Document US Pat. No. 8,057,184 discloses a pivot for a fan blade in which all the parts forming the pivot have all the forces (centrifugal and aerodynamic), which requires oversizing these parts to enable the pivot to withstand the stresses in torsion, compression and extension. Moreover, this pivot generates several concurrent stress paths, which is undesirable and makes the pivot difficult to dismantle.
    Document FR 2,953,195 also discloses a pivot for a fan blade in which the balls of the lower bearing must be positioned after the mounting of the pivot, which makes the replacement of this bearing complex. In addition, all parts of the pivot see all efforts (centrifugal and aerodynamic), which requires over-size these parts to allow the pivot to withstand stress in torsion, compression and extension.
    Object and summary of the invention
    The present invention therefore has the main purpose of providing an adjustable pivot blade pivot which does not have the aforementioned drawbacks.
    According to the invention, this object is achieved by means of an adjustable-orientation blade pivot for a turbomachine fan hub, comprising: a stud having, at an inner radial end, coupling means for transmitting a torsion torque and an external thread; an annular force decoupling piece positioned around the stud and provided at an outer radial end with an external thread, said force decoupling piece being in transverse support against the stud at its outer radial end and free from contact with said stud at an inner radial end; an outer rolling bearing having an inner ring mounted as a transverse support against the outer radial end of the force decoupling piece; an inner rolling bearing mounted around and held by the radially inner end of the force decoupling member; a timing transmission ring positioned around the radially inner end of the stud and provided with coupling means cooperating with the coupling means of the stud; a first tightening nut screwed onto the external thread of the force decoupling member to ensure a clamping of the outer and inner rolling bearings around the fan hub; and a second tightening nut screwed onto the external thread of the stud to ensure a clamping between them of the stud, the force decoupling piece and the timing transmission ring.
    The pivot according to the invention is remarkable in that, through the various separate elements that constitute it, it allows to separate the stress paths. Thus, the centrifugal force undergone by the fan blade transits directly through the stud of the pivot to be resumed radially at the inner rolling bearing. The transverse forces (relative to the axis of the pivot) are in turn taken up by the upper rolling bearing passing through the outer radial end of the decoupling piece efforts. In addition, the direct contact between the inner ring of the outer rolling bearing and the force decoupling part makes it possible to take up the majority of the bending forces undergone by the blade. Finally, the particular arrangement of the pivot according to the invention limits the bending forces (due to aerodynamic forces experienced by the blade) in the pivot.
    The pivot according to the invention also has the advantage of dissociating the various functions it provides. In particular, if it is necessary to perform maintenance on the pivot, it is not necessary to disassemble all the elements thereof (including the inner and outer bearings and the decoupling piece forces). In addition, the change of the rolling bearings of the pivot according to the invention is relatively easy since it makes it possible to have a unitary assembly comprising the two rings and the balls of the bearings (or the two separate rings and a set of balls trapped in a cage). By separating the functions provided by the pivot, it is also not necessary to perform a motor removal and disassemble the entire propeller to operate on a single fan blade.
    Finally, it should be noted that the pivot according to the invention also has the advantage of being able to be assembled on the fan hub without having to make rolling tracks on the hub, which allows it to be made of an alloy of titanium type.
    The outer rolling bearing may further comprise an outer ring intended to be housed inside an orifice made in the fan hub and traversed by the pivot, the inner and outer rings defining raceways for a plurality of balls. In this case, the first clamping nut is preferably screwed radially against the inner ring of the outer rolling bearing.
    The inner rolling bearing may comprise an outer ring mounted around the inner radial end of the force decoupling member and defining with an outer surface thereof rolling tracks for a plurality of balls.
    As for the coupling means of the stud, they may be external splines and the coupling means of the timing transmission ring are internal splines cooperating with the external splines of said stud.
    According to one embodiment, the stud the stud comprises two separate parts interconnected: a radial portion comprising the coupling means for transmitting a torque and the external tightening thread, and a fastening portion comprising a radial bore traversed by the radial portion. This embodiment makes it possible to have a titanium-type alloy on the part that does not have threads (namely the attachment part).
    In this embodiment, the attachment portion may further comprise a countersink formed around the bore and intended to receive a flange of the radial portion to provide a connection between the two parts of the pivot. The subject of the invention is also a blade with a variable pitch angle for a turbomachine fan hub, comprising an aerodynamic profile and a pivot as defined above. The invention further relates to a turbomachine comprising at least a fan hub and at least one set of these blades variable pitch angle.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate embodiments having no limiting character. In the figures: FIG. 1 is a sectional view showing an example of implantation of an adjustable orientation fan blade pivot according to one embodiment of the invention; - Figure 2 is a magnifying glass of Figure 1 showing more precisely the blade pivot; and - Figure 3 is a sectional view showing a pivot according to another embodiment of the invention.
    DETAILED DESCRIPTION OF THE INVENTION The invention applies to any turbomachine equipped with at least one ducted or non-ducted fan, and whose propeller blades (in the case of a non-ducted fan) or the fan blades. (in the case of a streamlined fan) are equipped with a change of pitch system. The invention applies in particular to turboprop engines with one or more propeller propellers, as well as propeller (s) (known as "Open Rotor") turbofan engines that comprise a propeller (and a variable-pitch stator for the propeller). USF - "Unducted Single Fan", or "single fan unsheathed") or two contra-rotating propellers placed upstream (in "puller" version in English) or downstream (in "pusher" version in English) of the gas generator. The invention is still applicable to streamlined fan turbomachines. The architecture of these types of turbomachines is well known to those skilled in the art and will not be described here in detail. Briefly, these turbomachines comprise one or more propellers (in the case of a non-ducted fan turbomachine) or a fan (in the case of a fan-cooled turbomachine) each consisting of a set of blades (or blades ) blowers variable pitch angle, that is to say that their orientation can be changed by means of a control system of the orientation of the blades described below.
    In the remainder of the description, reference will be made to propeller and propeller blades regardless of whether the invention applies to a non-ducted fan turbomachine or to a ducted fan turbomachine (in which case the propeller corresponds to the fan of the turbomachine and the propeller blades correspond to the fan blades).
    A turbomachine propeller is constituted by a set of fan blades with variable pitch angle, independent or not, that is to say that their orientation can be modified by means of a control system of the orientation of the blades .
    As shown in FIG. 1, this control system may comprise an axial jack 2 centered on the axis of rotation X-X of the helix and fixed with respect to the structures of the engine. This jack 2 comprises a chamber 4 and rods 6 which can move axially synchronously when the cylinder is actuated. At their free end, the rods 6 are connected to the inner ring 8 of a rolling motion transfer bearing 10 whose outer ring 12 is coupled, by means of lever arms 14, to pivots 16 of the blades. blower of the propeller. Thus, when the cylinder 2 is actuated, the rods 6 translate to move the rolling motion transfer bearing 10, which causes a pivoting of the pivots 16 of the fan blades about their radial axis Z-Z.
    Note that it is possible to have a reverse configuration in which the cylinder rods are secured to the casing of the turbomachine and the cylinder body is movable relative to the cylinder rods.
    More specifically, the pivot 16 serves to ensure the retention of the fan blade on a rotary hub 18 of the fan and the guide thereof for the setting of its pitch. For this purpose, the pivot 16 of the fan blade is mounted radially in an orifice 20 of the hub 18 of the propeller through which it passes through, the hub being centered on the longitudinal axis X-X of the turbomachine.
    According to the invention, as shown in Figure 2, the pivot 16 of the fan blade comprises a plurality of separate elements which are assembled together so as to facilitate assembly / disassembly of the hub of the propeller.
    Thus, the pivot 16 comprises in particular a stud 22 which extends along the radial axis ZZ of the pivot through the orifice 20 of the fan hub 18 and which has, at an outer radial end (ie say at its end farthest from the axis XX), a tooth 24 which is intended to receive a foot of the fan blade (not shown in the figures). It should be noted that the fan blade could be unitary with the stud.
    At its radially inner end (that is to say at its end closest to the axis XX), the stud 22 comprises external splines 26 for transmitting a torque and an external thread Clamping 28.
    The pivot 16 according to the invention further comprises an annular piece of decoupling forces 30 which is positioned around the stud 22. This force decoupling part is centered on the radial axis ZZ of the stud 22, is in transverse support against the stud at its radially outer end and at an annular flange 32, and free of contact therewith at an inner radial end. The transverse support between the collar 32 of the stud and the force decoupling part is shown schematically in FIG. 2 by the arrows F1.
    At its outer radial end, the force decoupling part 30 is provided with an external thread 34 on which is tightened a first nut 36 also centered on the radial axis Z-Z of the stud.
    The pivot 16 according to the invention further comprises an outer rolling bearing 38 (that is to say located on the outside of the pivot) and an inner rolling bearing 40 (that is to say located on the inner side of the pivot) mounted around the stress decoupling member, respectively at the outer radial end and an inner radial end thereof.
    More specifically, the outer rolling bearing 38 is of the angular contact type and comprises an inner ring 42 and an outer ring 44 which define rolling tracks for a plurality of balls 46. The outer ring 44 bears radially against the inside of the orifice 20 made in the rotary hub 18.
    As for the inner ring 42 of this rolling bearing outside, it comes in transverse support against the outer radial end of the decoupling piece forces (this support is shown schematically by the arrows F2 in Figure 2). The tightening of the first clamping nut 36 on the force decoupling part thus makes it possible to stress this outer rolling bearing 38.
    The inner rolling bearing 40 is of the angular contact type and comprises an outer ring 47 also intended to bear radially inside the orifice 20 formed in the hub 18 of the fan. In addition, this outer ring defines with an outer surface 48 of the inner radial end of the decoupling member the forces 30 of the raceways for a plurality of balls 50.
    The pivot 16 according to the invention also comprises a timing transmission ring 52 also forming an annular sealing cover for an oil chamber located inside the control system. This timing transmission ring 52 is positioned around the inner radial end of the stud 22 being centered on the radial axis Z-Z thereof. This timing transmission ring is provided with internal splines 54 cooperating with the external splines 26 of said stud. It should be noted that other means of coupling that splines could be envisaged between the wedge transmission ring and the stud.
    A second clamping nut 56 is screwed onto the external thread 28 formed at the inner radial end of the stud 22 to provide radial clamping between the stud 22, the decoupling member 30, and the stall transmission ring 52. This clamping also makes it possible to stress the inner rolling bearing 40.
    Figure 3 shows an alternative embodiment of the pivot according to the invention. In this Figure 3, the elements of the pivot 16 'which are identical to those of the pivot of the embodiment of Figure 2 bear the same reference.
    Here, the stud 22 'of the pivot 16' consists of two distinct parts interconnected, namely a radial portion 22'a comprising the external splines 26 for transmitting a torsion torque and the external clamping thread 34, and an attachment portion 22'b comprising the tooth 24 and a radial bore 58 traversed by the radial portion 22'a.
    In this case, the attachment portion 22'b further comprises a countersink 59 formed around the bore 58 and intended to receive a flange 60 of the radial portion 22'a to provide a connection between the two parts of the pivot. The advantage of separating the stud into two distinct parts is that it is possible to use two different materials to make these two parts of the stud and thus gain mass.
    Whatever the embodiment, the mounting of the pivot according to the invention is thus relatively easy and is performed by first unscrewing the clamping nut 56, then removing the timing transmission ring 52 and the stud 22, the outer bearings 38 and inner 40 remaining still in place. This makes it easy to change or inspect the removed parts. Then, simply unscrew the clamping nut 36 to change the rolling bearings 38,40.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Pivot (16; 160) of adjustable-angle blade for turbomachine blower hub (18), comprising: a pad (22; 220 having at one radially inner end coupling means (26) for transmitting a torque and an external thread (28); an annular force decoupling member (30) positioned around the stud and provided at an outer radial end with an external thread (34), said force decoupling piece being in abutment transverse end (F2) against the stud at its outer radial end and free from contact with said stud at an inner radial end; an outer rolling bearing (38) having an inner ring (42) mounted transversely against the outer radial end of the force decoupling member, an inner rolling bearing (40) mounted around and held by the inner radial end of the force decoupling member; e timing transmission ring (52) positioned around the inner radial end of the stud and provided with coupling means (54) cooperating with the coupling means (26) of the stud; a first clamping nut (36) screwed onto the outer thread (34) of the force decoupling member (30) for clamping the outer and inner rolling bearings around the fan hub (18); and a second clamping nut (56) screwed onto the external thread (28) of the stud to ensure a clamping between them of the stud, the force decoupling piece and the timing transmission ring.
    [2" id="c-fr-0002]
    2. Pivot according to claim 1, wherein the outer rolling bearing (38) further comprises an outer ring (44) intended to be housed inside an orifice (20) formed in the hub (18) of blower and traversed by the pivot (16), the inner ring (42) and outer (44) defining raceways for a plurality of balls (46).
    [3" id="c-fr-0003]
    3. Pivot according to claim 2, wherein the first clamping nut (36) is screwed radially against the inner ring of the outer rolling bearing.
    [4" id="c-fr-0004]
    4. Pivot according to any one of claims 1 to 3, wherein the inner rolling bearing (40) comprises an outer ring (47) mounted around the inner radial end of the force decoupling piece and defining with a outer surface (48) thereof rolling tracks for a plurality of balls (50).
    [5" id="c-fr-0005]
    5. Pivot according to any one of claims 1 to 4, wherein the coupling means of the pad (22) are external splines (26) and the coupling means of the shim ring (52) are internal splines (54) cooperating with the outer splines (26) of said pad.
    [6" id="c-fr-0006]
    6. Pivot (16 ') according to any one of claims 1 to 5, wherein the stud (220 comprises two separate parts interconnected: a radial portion (22'a) comprising the coupling means for the transmission of a torsion torque and the external clamping thread, and an attachment portion (22'b) comprising a radial bore (58) traversed by the radial portion.
    [7" id="c-fr-0007]
    7. Pivot according to claim 6, wherein the attachment portion (22'b) further comprises a countersink (59) formed around the bore (58) and intended to receive a flange (60) of the radial portion (22). a) to provide a connection between the two parts of the pivot.
    [8" id="c-fr-0008]
    8. Variable pitch angle blade for a turbomachine fan hub (18) comprising an airfoil and a pivot (16; 160 according to any one of claims 1 to 7.
    [9" id="c-fr-0009]
    9. Turbomachine comprising at least one fan hub (18) and at least one set of variable pitch angle blades according to claim 8.
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    同族专利:
    公开号 | 公开日
    EP3400168A1|2018-11-14|
    WO2017118808A1|2017-07-13|
    CN108473193B|2021-09-21|
    CN108473193A|2018-08-31|
    FR3046403B1|2018-02-09|
    US20190010957A1|2019-01-10|
    US10730608B2|2020-08-04|
    EP3400168B1|2019-11-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2017505A|1933-02-15|1935-10-15|Meon Engineering Corp|Propeller blade mounting for variable pitch propellers|
    GB546621A|1940-12-19|1942-07-22|Leonard Gaskell Fairhurst|Improvements in or relating to variable-pitch airscrews|WO2020169896A1|2019-02-22|2020-08-27|Safran Aircraft Engines|Blade pivot of adjustable orientation and of reduced bulk for a turbomachine fan hub|
    WO2021116566A1|2019-12-11|2021-06-17|Safran Aircraft Engines|Improvement in the radial locking of a blade pivot with adjustable orientation for a turbomachine fan hub|
    WO2021214399A1|2020-04-23|2021-10-28|Safran Aircraft Engines|Blade pivot with adjustable orientation and protected integrity for a turbomachine fan hub|GB485982A|1937-01-06|1938-05-27|Ver Deutsche Metallwerke Ag|Improvements in or relating to mountings for the blade roots of variable pitch propellers|
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    法律状态:
    2017-01-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-07| PLSC| Publication of the preliminary search report|Effective date: 20170707 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650040A|FR3046403B1|2016-01-05|2016-01-05|ADJUSTABLE ORIENTATION BLADE PIVOT FOR TURBOMACHINE BLOWER HUB|
    FR1650040|2016-01-05|FR1650040A| FR3046403B1|2016-01-05|2016-01-05|ADJUSTABLE ORIENTATION BLADE PIVOT FOR TURBOMACHINE BLOWER HUB|
    CN201780005867.8A| CN108473193B|2016-01-05|2017-01-04|Pivot for variable orientation blades of a turbine engine fan hub|
    EP17702672.1A| EP3400168B1|2016-01-05|2017-01-04|Pivot blade with variable pitch for a turbofan engine|
    PCT/FR2017/050010| WO2017118808A1|2016-01-05|2017-01-04|Pivot for blade with adjustable orientation for hub of a turbomachine fan|
    US16/067,981| US10730608B2|2016-01-05|2017-01-04|Variable pitch blade pivot for a turbine engine fan hub|
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