• 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 propeller (2) for an aircraft engine (1) comprising: - a blade support (10) associated with each blade, pivotally mounted on the hub (8) along an incidence bearing axis (14) ; a pivoting connection (20) between each blade support (10) and the foot (6a), allowing pivoting of the blade (6) relative to its blade support (10) along a blade folding axis (22) ; - Associated with at least one of the blades (6), a blade folding / unfolding control member (24) configured to pivot the foot (6a) relative to the blade support (10) along the axis of folding (22); a passive device (40) for synchronizing the folding / unfolding of the blades, comprising a central synchronization element (42) rotatably mounted relative to the hub (8) along the axis of rotation of the helix (4), and a connecting element (44) associated with each blade (6), having a first end mounted on the blade root (6a) and a second end mounted on the central synchronization element (42).
    公开号:FR3048953A1
    申请号:FR1652398
    申请日:2016-03-21
    公开日:2017-09-22
    发明作者:Christophe Heranger；Marco Prampolini
    申请人:Airbus Defence and Space SAS；
    IPC主号:
    专利说明:

    AIRCRAFT PROPELLER COMPRISING PLATFORMED AND VARIABLE SHAFT BLADES
    DESCRIPTION
    TECHNICAL FIELD The invention relates to the field of aircraft engine propellers, in particular propellers controlled in rotation at a substantially constant speed.
    They apply to all types of aircraft, such as drones.
    STATE OF THE PRIOR ART
    From the prior art, it is known aircraft engine propellers whose blades have a foldable character, so as to be moved from an active position deployed to a retracted position, and vice versa. This type of system is mainly used on small-size passenger aircraft, in order to be able to bend the propeller once the aircraft is on the ground. This reduces the size of the aircraft and protect its propeller. Another feature may lie in the folding of the propeller during the flight, in order to reduce the induced drag.
    In addition, on larger aircraft, it is known to provide propeller blades pivotally mounted on the hub to allow their wedging incidence. Indeed, the variation of the angle of incidence of the blades during a flight makes it possible to adapt at any moment to the thrust requirements without modifying the parameters of this flight, and while maintaining a substantially constant speed of rotation. of the propeller. Nevertheless, no technical solution has yet been proposed to combine the two aforementioned functionalities within the same propeller, namely to offer a variable pitch of the blades while making them collapsible. There is therefore a need in this direction.
    DISCLOSURE OF THE INVENTION The invention therefore aims to at least partially meet the need identified above.
    To do this, the subject of the invention is a propeller for an aircraft engine intended to be rotated about an axis of propeller rotation, the propeller comprising a hub and a plurality of blades distributed circumferentially around the hub. and further comprising: - a blade support associated with each blade, said blade support being pivotally mounted on said hub according to an incidence timing axis; control means in incidence of the blades configured to rotate said blade support relative to the hub, according to said incidence timing axis; a pivoting connection between each blade support and the foot of its associated blade, the pivoting connection allowing pivoting of the blade relative to its blade support along a blade folding axis; associated with at least one of the blades, a blade folding / unfolding control member configured to pivot said blade root relative to the blade support according to said folding axis, said folding / unfolding control member comprising a first element and a second element movable in translation relative to each other, the first element being mounted on said hub with a first pivot connection and the second element being mounted on a transmission device to the first using a second pivot connection, the transmission device being connected to said blade root; a passive device for synchronizing the folding / unfolding of the blades, comprising a central synchronization element rotatably mounted relative to the hub according to said axis of propeller rotation, and a coupling element associated with each blade, said coupling element comprising a first end mounted on said blade root according to a first ball joint connection, and a second end mounted on said central synchronization element by means of a second ball joint. The invention is remarkable in that it makes it possible to respond to the need identified above in a clever, simple and efficient manner. In particular, the implementation of the pivot / ball joints makes it possible to introduce degrees of freedom of movement that are useful for supporting the pivoting of the blades when they are wedged in incidence. Similarly, these pivot / ball joints are useful for the kinematics of folding / unfolding of the blades, a movement during which the central synchronizing element rotates freely around the hub along the axis of rotation of the helix. In this regard, it is noted that the passive synchronization device not only makes it possible to avoid the occurrence of imbalances during the folding / unfolding movements, but also makes it possible to provide a number of folding / unfolding control members that are smaller than number of blades of the propeller. The invention is also remarkable in that it has a design that can be implemented on existing propellers with variable pitch of the blades, without causing significant changes.
    In addition, it allows to consider an unfolding of the blades with the propeller already in rotation, or with the propeller stopped.
    Finally, it adapts to both propellers mounted in push configuration (called "pusher"), in which the blades are bent backwards, and propellers mounted in traction configuration (called "puller") in which the blades bend forward. The invention furthermore exhibits at least one of the following optional features, singly or in combination. The propeller comprises at least two blades folding / unfolding control members, respectively associated with two blades. As mentioned above, the number of these control members may be less than the number of blades, but may be alternately identical to the latter. By way of example, the number of control members is half that of the blades of the propeller. Also by way of example, it is noted that a single folding / unfolding control member could be associated with all the blades of the propeller.
    Preferably, said blade folding / unfolding control member is a controlled cylinder, preferably a hydraulic cylinder. The cylinder can be controlled in "pusher" or "puller" modes, depending on the design of the propeller. In addition, it is noted that in "puller" mode, the jack can fulfill the function of damper.
    Preferably, each connecting element is a connecting rod.
    Preferably, said central synchronization element is a ring. Preferably, said transmission device comprises two links articlés one on the other.
    Preferably, the blade folding axis and the incidence pinning axis are substantially orthogonal.
    Preferably, the number of blades is between one and four, even if a greater number could be provided, without departing from the scope of the invention.
    Preferably, the folding / unfolding control member is oriented substantially parallel to the axis of propeller rotation when the blades are in an extended active position. The invention also relates to an aircraft engine comprising a helix as described above, preferably configured so that the propeller rotates at a substantially constant speed along its axis of rotation. Nevertheless, it is conventionally indicated that the rotational speed of the propeller can be controlled at a slightly lower speed by the pilot, for purposes of thrust optimization or fuel consumption, depending on the mission. Other advantages and features of the invention will become apparent in the detailed non-limiting description below.
    BRIEF DESCRIPTION OF THE DRAWINGS
    This description will be made with reference to the appended drawings among which; - Figure la shows a schematic perspective view of a helix according to the invention, in an active position deployed; - Figure lb is a schematic side view of the propeller shown in Figure la; - Figure 2a is a view similar to that of Figure la, with the propeller shown in a position close to the retracted position; - Figure 2b is a view similar to that of Figure lb, with the propeller shown in a position close to the retracted position; and - Figure 3 is a partial perspective view of the helix shown in Figure la, and shown in more detail.
    DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
    Referring firstly to Figures 1a and 1b, there is shown a propeller 2 for an aircraft engine 1, for example a drone engine. It is preferably a motor adapted for a vehicle with a mass of the order of five tons, and whose propeller 2 is intended to be rotated at a substantially constant speed along its axis of rotation. propeller 4, for example at a maximum speed of the order of 2000 rev / min. To do this, the engine 1 is conventionally equipped with a control system (not shown), making it possible to order a variation in the incidence of the blades of the propeller in order to maintain its constant speed of rotation, whatever the power requirements. The propeller 2 comprises a plurality of blades 6, here present four in number regularly distributed circumferentially around the axis of rotation 4. These blades 6 are carried externally by a propeller hub 8, rotatably mounted according to the invention. axis 4 relative to a fixed part of the engine. The invention has the particularity of offering a design allowing not only the wedging in incidence of its blades 6, but also the pounding / unfolding of its blades between an active deployed position as shown in Figures la and lb, and a position withdrawal or folded position, close to that shown in Figures 2a and 2b.
    Still with reference to Figures 1a and 1b, the propeller 2 comprises a blade support 10 associated with each blade. This support 10 is arranged radially in relation to the axis of rotation 4, and passes through an opening 12 of the hub 8. The blade support 10 is pivotally mounted in this opening 12 of the hub, according to an axis of incidence timing 14 which is substantially oriented radially. As has been shown schematically in FIG. 1b, each blade support 10 cooperates in known manner with means 16 for controlling the blades, housed inside the hub 8. These means 16 are configured to rotate simultaneously each blade support 10 in its opening 12, according to its bearing timing axis 14. This pivoting is performed in response to an order of the engine control system, to change the pitch angle of the blades 6 of the propeller.
    In addition, each blade 6 comprises an aerodynamic portion and a base forming a blade root 6a. This takes the form of a clevis articulated on its associated blade support 10, thanks to a pivotal connection 20. This connection defines a blade pusher axis 22, substantially circumferential orientation relative to the axis of rotation 4 Consequently, the pivoting connection 20 allows a pivoting of the blade 6 relative to its blade support 10, according to the blade folding axis 22 substantially orthogonal to the bearing pinning axis 14. In this respect, it is noted that the folding of the blades is here provided for them to swing forward, since the engine has a traction configuration (called "puller") in which the propeller is mounted at the front of the gas generator. Nevertheless, an inverted configuration (called "pusher") could be adopted without departing from the scope of the invention. In this case, the blades are designed to bend backwards.
    To realize the folding / unfolding of the helix, there is provided at least one blade folding / unfolding control member 24 associated with a blade 6. For example, only two of the four blades 6 are equipped with such a blade member. 24 command, even if the number of these bodies could be lower or higher, without departing from the scope of the invention. The blade folding / unfolding control member 24 is configured to pivot the blade root 6a relative to the blade support 10, along the axis of folding 22. It is preferably a hydraulic cylinder controlled, comprising a cylinder body 28 and a cylinder rod 30 movable in translation relative to each other. In the deployed active position as shown in Figures la and lb, the control member 24 is oriented substantially parallel to the axis of rotation 4 of the helix.
    The cylinder body 28 is mounted on a rear part of the hub 8 by means of a first pivot connection 32a, while the cylinder rod 30 is mounted on a transmission device 34 by means of a second link pivot 32b. More specifically, the transmission device 34 comprises two links 37 articulated to one another, and one of which is also articulated on the blade root 6a, and the other of which is articulated on a fitting 38 integral in rotation of the blade support 10. The three hinge axes are here parallel to each other, and also parallel to the blade bending axis 22.
    The two links 37 follow one another in the radial direction, being arranged externally to the hub 8. The link located radially inwardly has an eyelet (referenced 50 in FIG. 3) for connection to the piston rod 30, at the level of which the second pivot link 32b is made. As an indication, it is noted that the axes supporting the first and second pivot links 32a, 32b are preferably parallel to the blade bending axis 22.
    Finally, the propeller 2 comprises a passive device 40 for synchronizing folding / unfolding of the blades 6. This device 40 firstly comprising a central synchronization element 42 in the form of a ring, arranged around the front part of the hub 8 This ring 42 is locked in translation along the axis of rotation of the helix 4, and is only rotatable along the same axis 4 relative to the hub 8. It also comprises a coupling element 44 associated with each blade 6, preferably rod-shaped. Its first end is mounted on the blade root 6a according to a first ball joint 32c, and its second end is mounted on the central synchronization ring 42 by means of a second ball joint 32d. Each connecting rod 44 extends substantially forward, and has an angle in the radial direction when viewed in front view. As can be seen in Figure 3 more detailed but on which the control members have been removed for clarity, the axes supporting the first and second ball joints 32c, 32d are preferably orthogonal to each other. Indeed, the axis supporting the first ball joint 32c, whose orientation is symbolized by the dotted line 52, is parallel to the blade bending axis 22, while the axis supporting the second ball joint 32d, of which the orientation is symbolized by the dotted line 54, is parallel to the axis of rotation 4 of the helix.
    With the design described above, in case of variation of incidence controlled by the means 16, each blade support 10 pivots about its axis 14 relative to the hub 8. This pivoting is accompanied by a movement of the cylinders 24 and rods 44 , thanks to the pivot links / ball joints 32a-32d. In addition, during the movement of the rods 44, it may be accompanied by a small rotation of the ring 42 around the hub 8, along the axis 4.
    When a folding of the propeller is controlled, the control members 24 are actuated accordingly until the blades 6 reach their withdrawal position close to that shown in Figures 2a and 2b. Here, it is a deployment of the cylinder 24, the piston rod 30 leads the radially lower link to pivot forward, taking with it the other link which in turn pushes the blade foot 6 to pivot forwardly along the axis 22. The two links 37 and pass from a configuration where they are substantially aligned radially to a configuration in which they form a V open rearward. It is noted that the retained design can be such that in the unfolded position, the two links 37 can adopt a position in which they are slightly inclined with respect to each other, so as to form a very flared V and especially in the opposite direction to the aforementioned V, open towards the rear. This prevents the accidental return of the blades in the folded position.
    The pivoting of the blades 6 is performed at an angle close to 90 °, so that their initially radial orientation gradually tilts to become substantially axial. During this pivoting of the blades 6, the first end of each connecting rod 44 is driven forward, while this displacement is compensated by the rotation of the ring 42 around the hub 8, caused by the induced displacement of the second end of each connecting rod 44. In this respect, it is indicated that it is preferentially provided a functional clearance on each connecting rod to avoid any hyperstatic loop between the synchronization device and the control means in incidence of the blades located inside the rotor. The spacing of the second ends of the rods 44 on the ring 42 being regular, the folding of the propeller 2 is advantageously performed in a synchronized manner. Of course, the folding of the propeller 2 forward must oppose the aerodynamic force applying to the blades 6 in flight, the propeller turns or it is stopped.
    For the unfolding of the propeller 2, the principles described above are realized in the opposite direction. In this regard, it is noted that the unfolding / deployment can be performed while the propeller rotates, or with the propeller stopped. In the first case, the centrifugal force advantageously helps the deployment.
    Of course, various modifications may be made by those skilled in the art to the invention which has just been described, solely by way of non-limiting examples.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    A propeller (2) for an aircraft engine (1) intended to be rotated about an axis of propeller rotation (4), the propeller comprising a hub (8) and a plurality of blades (6). ) distributed circumferentially around the hub, characterized in that it further comprises: - a blade support (10) associated with each blade, said blade support being pivotally mounted on said hub (8) according to a bearing axis in incidence (14); - Incident control means (16) for the blades configured to pivot said blade support (10) relative to the hub (8), according to said incidence timing axis (14); - A pivoting connection (20) between each blade support (10) and the foot (6a) of its associated blade, the pivoting connection allowing pivoting of the blade (6) relative to its blade support (10) along an axis folding blade (22); - Associated with at least one of the blades (6), a blade folding / unfolding control member (24) configured to pivot said blade root (6a) relative to the blade support (10) along said axis of rotation. folding (22), said folding / unfolding control member (24) comprising a first member (28) and a second member (30) translatable relative to each other, the first member (28) being mounted on said hub (8) with a first pivot link (32a) and the second member (30) mounted on a transmission device (36) with a second pivot link (36b) the transmission device being connected to said blade root (6a); a passive device (40) for folding / unfolding the blades, comprising a central synchronization element (42) rotatably mounted relative to the hub (8) along said axis of rotation of the propeller (4), and an element connector (44) associated with each blade (6), said connecting member (44) having a first end mounted on said blade root (6a) in a first ball joint (32c), and a second end mounted on said central synchronization element (42) using a second ball joint (32d).
    [2" id="c-fr-0002]
    2. Propeller according to claim 1, characterized in that it comprises at least two blade folding / unfolding control members (24) respectively associated with two payrolls (6).
    [3" id="c-fr-0003]
    3. Propeller according to any one of the preceding claims, characterized in that said blade folding / unfolding control member (24) is a controlled cylinder.
    [4" id="c-fr-0004]
    4. Propeller according to any one of the preceding claims, characterized in that each connecting element (44) is a connecting rod.
    [5" id="c-fr-0005]
    5. Propeller according to any one of the preceding claims, characterized in that said central synchronization element (42) is a ring.
    [6" id="c-fr-0006]
    6. Propeller according to any one of the preceding claims, characterized in that said transmission device comprises two links (36) articulated to one another.
    [7" id="c-fr-0007]
    7. Propeller according to any one of the preceding claims, characterized in that said blade bending axis (22) and said incidence timing axis (14) are substantially orthogonal.
    [8" id="c-fr-0008]
    8. Propeller according to any one of the preceding claims, characterized in that the number of blades (6) is between one and four.
    [9" id="c-fr-0009]
    9. Propeller according to any one of the preceding claims, characterized in that the folding / unfolding control member (24) is oriented substantially parallel to the axis of rotation of the propeller (4) when the blades (6) are in an active deployed position.
    [10" id="c-fr-0010]
    10. Aircraft engine (1) comprising a propeller (2) according to any one of the preceding claims.
    [11" id="c-fr-0011]
    11. Motor according to claim 10, characterized in that it is configured so that its helix (2) rotates at a substantially constant speed along its axis of rotation (4).
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    同族专利:
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    FR3048953B1|2018-04-06|
    CN108778926B|2021-12-31|
    CN108778926A|2018-11-09|
    JP2019509214A|2019-04-04|
    US20190061914A1|2019-02-28|
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    JP6921848B2|2021-08-18|
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    法律状态:
    2017-03-31| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-22| PLSC| Publication of the preliminary search report|Effective date: 20170922 |
    2018-03-29| PLFP| Fee payment|Year of fee payment: 3 |
    2018-06-01| CA| Change of address|Effective date: 20180424 |
    2018-06-01| CD| Change of name or company name|Owner name: ARIANEGROUP SAS, FR Effective date: 20180424 |
    2018-06-01| TP| Transmission of property|Owner name: ARIANEGROUP SAS, FR Effective date: 20180426 |
    2020-03-31| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652398|2016-03-21|
    FR1652398A|FR3048953B1|2016-03-21|2016-03-21|AIRCRAFT PROPELLER COMPRISING FOLDING BLADES AND VARIABLE SHAFT|FR1652398A| FR3048953B1|2016-03-21|2016-03-21|AIRCRAFT PROPELLER COMPRISING FOLDING BLADES AND VARIABLE SHAFT|
    CN201780017854.2A| CN108778926B|2016-03-21|2017-03-20|Aircraft propeller comprising foldable variable pitch blades|
    US16/086,817| US10683081B2|2016-03-21|2017-03-20|Aircraft propeller comprising collapsible variable pitch blades|
    PCT/EP2017/056512| WO2017162561A1|2016-03-21|2017-03-20|Aircraft propeller comprising collapsible, variable-pitch blades|
    JP2018549216A| JP6921848B2|2016-03-21|2017-03-20|Aircraft propeller with foldable variable pitch blade|
    EP17711221.6A| EP3433169B1|2016-03-21|2017-03-20|Aircraft rotor comprising foldable blades with variable pitch|
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