• 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:

    公开号:FR3017566A1
    申请号:FR1400444
    申请日:2014-02-19
    公开日:2015-08-21
    发明作者:Christian Mercier
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a power plant of an aircraft, and an aircraft equipped with this power plant. More particularly, the invention relates to a power plant comprising a connecting device for connecting a power transmission box and a motor. In particular, the invention lies in the field of rotorcraft powered installations equipped with a piston engine, a diesel engine more particularly. Rotorcraft are generally equipped with at least one rotor which is rotated by a power plant. This power plant is provided with at least one motor and a power transmission gearbox, said power transmission gear being interposed between the motor and the rotor. This engine may be a turbine engine connected by a power transmission chain to the power transmission gearbox.
    [0002] Such a power transmission chain comprises a transmission shaft extending between an output shaft of the engine and an input shaft of the power transmission gearbox. The transmission shaft may comprise one or more sections.
    [0003] During the operation of the installation, the engine and / or the power transmission may be subject to slight movement.
    [0004] Indeed, the power transmission can be suspended from the structure of an aircraft by a conventional suspension system. This suspension system may comprise for example suspension bars and suspension means.
    [0005] Reference will be made to literature to get a lesson on this subject. Similarly, an engine can be attached to this structure of the aircraft by feet, and if necessary by means of energy absorption and / or displacement such as means known under the name "silent block". Consequently, the power transmission gearbox and / or the motor can be subjected to relative movements in operation, for example oscillations. The movements can be caused by the operation of the power transmission and / or the engine, or by the deformation of the structures supporting them. As a result, the organs of the power transmission chain may then be misaligned with respect to each other which can cause their deterioration.
    [0006] To limit such misalignments, the power plant may include a connecting trumpet surrounding the drive train. This connecting trumpet is then rigidly attached to the power transmission and the engine. The trumpet link has the function of tending to maintain constant spacing between the power transmission and the engine, and ensure proper alignment of the various members of the power transmission chain. For example, a link trumpet may have the function of aligning a power transmission shaft with an input shaft of the power transmission gearbox and an output shaft of the engine.
    [0007] Nevertheless, the risk of misalignment remains. To allow possible misalignment between the drive shaft, the motor output shaft and the input shaft of the power transmission gearbox, the power transmission chain may comprise at least one elastic coupling means . A flexible coupling means may be of the type known by the name "flector" for example. Other coupling means are conceivable, for example of the type described in document US Pat. No. 795,9512.
    [0008] Each flexible coupling means makes it possible to transmit the motor torque generated by the motor to the power transmission gearbox. In addition, each flexible coupling means deforms in case of axial or angular misalignment to allow this misalignment and limit the impact of misalignment on the drive shaft. Therefore, a flexible coupling means may be the seat of significant effort and may deteriorate gradually. These coupling means are then regularly monitored. In addition, the drive shaft can also be designed to have sufficient flexibility to allow predetermined misalignment. Therefore, a power plant may include a connecting trumpet to limit the presence of misalignments, and flexible coupling means for possible misalignment to have a limited effect on the power plant. This system is interesting but can be difficult to size. It may require testing to assess the misalignments that the power transmission system will experience. In particular, the inertial movements of an engine in flight can be difficult to grasp without complex tests. For ecological or economic reasons for example, it may furthermore be envisaged to use not a turbine engine, but a piston engine and for example a diesel engine. Nevertheless, a piston engine is subjected to different movements due to the presence of moving parts during start-up, acceleration in engine speed, operation even in steady state, or engine torque setting 10 . These movements are then likely to degrade the physical integrity of the drive shaft. These movements seem difficult to grasp in the absence of tests, compared to the more linear movement of a turbine engine. JP 2000065265 is not part of the technical field of the invention with respect to a device for limiting the shear and torsional forces of a bellows. The object of the present invention is therefore to propose a power plant intended to limit any damage to a transmission shaft, particularly in the context of implementing a piston engine. The invention relates to a power plant comprising a heat engine and a power transmission box. This power plant has a power transmission chain extending in a longitudinal direction to connect the motor to the power transmission gearbox. As a result, the power transmission chain is rotated by the engine and then sets the power transmission gear in motion. This power transmission chain comprises at least one power transmission shaft and an elastic coupling means. This power plant then comprises two connecting bars extending respectively in a first direction and a second non-parallel direction and intersecting a common axis of rotation. Each link bar is hinged by a ball joint to the power transmission gearbox and the motor to eliminate relative movement in the longitudinal direction between the power transmission gearbox and the motor, and to allow limited rotation of the gearbox. of power transmission and the motor with respect to the geometric axis. This geometric axis may extend in a direction in elevation which is orthogonal to the longitudinal direction or to a direction parallel to this longitudinal direction. Therefore, the connecting rods limit by nature, via a suitable geometry, the possible movements of the engine relative to the power transmission. Since these connection bars are articulated by ball joints to the motor and to the power transmission gearbox, the connecting bars tend to limit the relative movement of the motor and the power transmission gearbox to a rotation with respect to their geometric axis of rotation. convergence. This relative movement then tends to be limited to one rotation with respect to the common geometric axis through which the two connecting bars pass together. The two connecting bars may therefore be rigid rods each capable of transmitting forces in their axis of extension in compression and traction. These connecting bars thus introduce a kinematic stress to the relative movements of the motor and the power transmission gearbox. Therefore, the invention includes connecting bars whose function is to reduce the movements of the power transmission shaft to movements that tend to be predictable. As a result, a manufacturer can evaluate the relative movements of the power transmission gearbox and the engine, and thus can adequately size the power transmission chain. The invention is all the more interesting when the heat engine is a piston engine and / or when the power transmission gear drives a rotorcraft rotor. Indeed, the implementation of the connecting bars makes more predictable modes of movement of the power transmission and the engine. However, these displacements are generally difficult to provide in the case of a piston engine whose movements and torsor forces transmitted to adjacent structures are complex and highly variable during a flight, unlike a turbine with more permanent operation. Therefore, the invention proposes a solution to this problem by limiting these movements to an identifiable rotation. The transmission shaft can then be positioned at a location resulting from the positions of the power transmission gearbox and the engine as well as the displacements allowed by the connecting rods. These movements are controlled and kinematically calculable. Indeed, the connecting bars remove degrees of freedom between the engine and the power transmission, and therefore allow a better knowledge of the movement of the power transmission chain. The dimensioning of the particular transmission shaft can thus be refined. In addition, the engine may comprise an engine block and feet. For example, the engine is carried by four feet which support it on a structure of an aircraft and also ensure the recovery of the engine torque. Therefore, at least one connecting bar can be articulated to a foot and / or at least one connecting bar can be articulated to the engine block. Furthermore, the power plant may comprise at least one elastic suspension system for connecting the power transmission box to a supporting structure. The suspension system may be a state-of-the-art system for, for example, filtering vibrations resulting from the rotational movement of a rotor driven by the power transmission gearbox. Reference will be made to the literature for the description of such a suspension system. The suspension system is therefore technically attractive but may provide freedom of movement to the power transmission gearbox. This freedom of movement is nevertheless constrained by the connecting bars. Furthermore, the power plant may include at least one energy absorbing means for connecting the motor to a carrier structure. The energy absorbing means may be a system of the state of the art, such as a device known under the name "silent bloc". Reference will be made to the literature for the description of such an energy absorbing means. The energy absorbing means can provide freedom of movement to the motor. This freedom of movement is nevertheless constrained by the connecting bars.
    [0009] Moreover, the connecting bars can cross one above the other between the power transmission gearbox and the motor, the geometric axis being arranged between the power transmission gearbox and the engine. Therefore, the geometric axis can pass through the elastic coupling means. The connecting bars converge towards a geometric axis that can be located at an elastic coupling means. This elastic coupling means may be a system of the state of the art, such as a device known by the name "flector" for example but not exclusively. Reference will be made to the literature for the description of such an elastic coupling means. Thus, the elastic coupling means is biased essentially in flexion. Indeed, the elastic coupling means is located at an instantaneous center of rotation of the motor and the power transmission gearbox. Therefore, the coupling means is biased in bending, and not in shear, tension or compression. The life of this elastic coupling means can then be improved over a conventional device for which the elastic coupling means is the seat of multiple efforts. As a result, the power transmission chain may comprise a transmission shaft connected to an output shaft of the motor by a first elastic coupling means and an input shaft of the power transmission gearbox by a second transmission means. elastic coupling. The geometric axis then passes through the second elastic coupling means. Optionally, a first minimum distance separating the geometric axis of the power transmission box is less than a second minimum distance separating the geometric axis of the engine. This characteristic makes it possible to optimize the positioning of the transmission shaft and in particular of the second elastic coupling means 10 in the context of the embodiment described above, as well as the distribution of the deformation work rate of the elastic coupling means in varying at will the positioning of the geometric axis. In addition to a power plant, the invention is directed to an aircraft provided with such a power plant. For example, the power transmission gear drives a levitation rotor and / or propulsion and / or control of yaw movement of the aircraft. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a view of a driving installation of a FIG. 2 is a diagram showing two connecting bars 25 converging towards a geometrical axis located at a power transmission box; FIG. 3 is a diagram showing two connecting bars converging towards a geometrical axis located at a power transmission box; FIG. a geometric axis located between a power transmission gearbox and a motor, and - Figures 4 and 5, two diagrams showing the rotational movement authorized by the connecting bars. The elements present in several separate figures are assigned a single reference. Note that three directions X, Y and Z orthogonal to each other are shown in some figures.
    [0010] The first direction X is called longitudinal. The term "longitudinal" is relative to any direction parallel to the first direction X. The second direction Y is said to be transverse. The term "transverse" is relative to any direction parallel to the second direction Y. Finally, the third direction Z is said to be in elevation. The expression "in elevation" relates to any direction parallel to the third direction Z. FIG. 1 shows an aircraft 1. This aircraft 1 is provided with a powerplant 10 for, for example, rotating a rotor 5. The aircraft may be a rotorcraft, the rotor 5 then being, for example, a rotor providing at least partially the lift of this rotorcraft and / or its propulsion. The powerplant 10 comprises a motor 15 resting on a structure 2 of the aircraft. This engine 15 is a heat engine, and possibly a piston engine.
    [0011] Regardless of the nature of the motor, the motor 15 is provided with a motor block 16 and feet 17, 18. The motor part as such of the motor 15 is referred to as the "motor block" and the fixing means are "feet". from engine to structure 2.
    [0012] For example, the engine block is based on the structure 2 by means of four feet, including a pair of feet called "front foot 17" and a pair of feet called "back foot 18". In addition, the motor 15 can be connected to the supporting structure directly by its feet, or indirectly by at least one energy absorbing means 70. For example, a power absorbing means 70 is interposed between each foot 17, 18 and structure 2. At least one foot may also include such energy absorbing means. The motor 15 has the particular function of setting in motion a power transmission box 20 of the power plant 10. This power transmission box 20 may then comprise a mast 20 'rotating the rotor 5. the power transmission gearbox 20 is connected to the carrier structure either directly or indirectly by an elastic suspension system 60. This elastic suspension system is optionally provided with connecting bars 61, with pendulum devices 62, or with means 63 interposed between the bottom of the power transmission box 25 and the structure 2 of the aircraft. The power plant is then provided with a power transmission chain 30 extending in a longitudinal direction 100 from the engine 15 to the power transmission box 20. The longitudinal direction 100 may be an axis of symmetry of the shaft of transmission. This power transmission chain may comprise a transmission shaft 31 and two elastic coupling means 32, 33. The transmission shaft 31 may be provided with one or more sections connected to each other. However, the variant of Figure 1 has a transmission shaft comprising a single section. Therefore, the power transmission shaft 31 is optionally connected by a first elastic coupling means 32 to an output shaft 19 of the motor 15. In addition, the transmission shaft 31 can be connected by a second transmission means. resilient coupling 33 to an input shaft 21 of the power transmission gearbox 20.
    [0013] In addition, the power plant has two connecting bars 41, 42 connecting the motor 15 to the power transmission box 20. This installation can then be devoid of trumpets. Each connecting bar 41, 42 is articulated by a ball joint 50 to the gearbox 20 and the motor 15. Each connecting bar 41, 42 is then articulated by a ball joint to the engine block 16 or to a foot 17 of the engine 15. A first connecting bar 41 extends in a first direction 101 which is not parallel to the longitudinal direction 100. In addition, a second connecting bar 42 extends in a second direction 102 which is not parallel neither in the longitudinal direction 100 nor in the first direction 101. As a result, the first direction 101 and the second direction 102 converge from the motor 15 to the same geometric axis 103 extending in elevation. For example, the first direction 101 and the second direction 102 are symmetrical relative to the longitudinal direction 100. According to the inclination of the first direction 101 and the second direction 102 relative to the longitudinal direction 100, a connecting bar can possibly pass over the other link bar. The connecting bars can also be coplanar, a connecting bar crossing an orifice of the other connecting bar.
    [0014] According to the variant of Figure 2, this inclination is low. As a result, the connecting bars 41, 42 converge towards a geometrical axis 103 located at the level of the power transmission box 20. As a result, the connecting bars 41, 42 do not intersect.
    [0015] On the other hand, this inclination is greater according to the variant of FIG. 3. Therefore, the connecting bars 41, 42 converge towards a geometrical axis 103 located between the power transmission box 20 and the motor 15. As a result, the connecting bars 41, 42 can intersect by passing one above the other at their intersection with the geometric axis 103. The geometric axis 103 can then be closer to the power transmission box 20 than Thus, a first minimum distance D1 separating the geometrical axis 103 from the power transmission box 20 is less than a second minimum distance D2 separating the geometrical axis 103 from the motor 15. The first distance is said to be "minimum Representing the smallest distance between the geometrical axis 103 and a casing of the power transmission gearbox 20. Similarly, the second distance is said to be "minimal" by representing the highest p This distance between the geometrical axis 103 and a casing of the motor unit 16 can therefore be separated by a geometrical axis 103 from an elastic coupling means of the power transmission chain, and in particular by the second means of transmission. Elastic coupling 33. The geometric axis may be located longitudinally between the first elastic coupling means 32 and the second elastic coupling means 33. This arrangement makes it possible to share the deformations at will between these two elastic coupling means. Independently of the variant, the geometric axis 103 may intersect in the longitudinal direction 100. In addition, the geometric axis 103 represents an instantaneous axis of rotation of the power transmission gearbox 20 with respect to the motor 15, and conversely . Indeed, when the engine is operating, the connecting bars 41, 42 allow antagonistic rotations of the power transmission box 20 and the motor 15 relative to the geometric axis 103, and tend to prevent relative movement according to the longitudinal direction 100 between the power transmission box 20 and the engine 15. Figures 4 and 5 explain this operation. With reference to FIG. 4, the power transmission gearbox 20 and the motor 15 are arranged in a theoretical position when the engine 15 is stopped.
    [0016] On the other hand, when the motor 15 is running, the gearbox 20 and / or the motor 15 tend to move relative to their theoretical positions. With reference to FIG. 5, these displacements are constrained by the connecting bars 41, 42. Indeed, the connecting bars tend to induce antagonistic rotations of the gearbox 20 and the motor 15 according to the arrows F with respect to FIG. the geometric axis 103. These displacements are therefore well identified. The manufacturer 10 can then take into consideration predictable movements in flight to size the power transmission chain in particular. Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention. 20
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. A power plant (10) comprising a thermal engine (15) and a power transmission gear (20), said power plant (10) having a power transmission chain (30) extending in a longitudinal direction (100) for connecting said motor (15) to said power transmission box (20), said power transmission chain (30) being rotated by said motor (15) and moving said power transmission gear (20), said power transmission chain (30) comprising at least one transmission shaft (31) and an elastic coupling means (32, 33), characterized in that said power plant (10) comprises two connecting bars (41, 42) extending respectively in a non-parallel first and second direction (101) and intersecting a common rotational geometrical axis (103), each connecting bar (41, 42) being hinged by a hinge (5). 0) to the power transmission gearbox (20) and the motor (15) to eliminate relative movement in said longitudinal direction (100) between the power transmission gearbox (20) and the motor (15) and for allow limited rotation of said power transmission gearbox (20) and said motor (15) with respect to said geometric axis (103).
    [0002]
    2. Powerplant according to claim 1, characterized in that said motor (15) is a piston engine, said power transmission box (20) driving a rotor (5) rotorcraft.
    [0003]
    3. Powerplant according to any one of claims 1 to 2, characterized in that said motor (15) comprising an engine block (16) and feet (17, 18), at least one connecting bar (41, 42). ) is articulated to a foot (17).
    [0004]
    4. Powerplant according to any one of claims 1 to 3, characterized in that said motor (15) comprising a motor unit (16) and feet (17, 18), at least one connecting bar (41, 42). ) is articulated to the engine block (16).
    [0005]
    5. Driving installation according to any one of claims 1 to 4, characterized in that said connecting bars (41, 42) intersect one above the other between the power transmission (20) and said motor (15), said geometrical axis (103) being arranged between the power transmission box (20) and said motor (15).
    [0006]
    6. Powerplant according to claim 5, characterized in that a minimum distance (D1) separating said geometric axis (103) from the power transmission gearbox (20) is less than a second minimum distance (D2) 20 separating said geometric axis (103) of the motor (15).
    [0007]
    7. Powerplant according to any one of claims 1 to 6, characterized in that said power plant (10) comprises at least one elastic suspension system (60) for connecting said power transmission box (20) to a supporting structure (2).
    [0008]
    8. Driving installation according to any one of claims 1 to 7, characterized in that said power plant (10) comprises at least one energy absorbing means (70) for connecting said motor (15) to a supporting structure (2).
    [0009]
    9. Powerplant according to any one of claims 1 to 8, characterized in that said geometric axis (103) passes through said elastic coupling means (33).
    [0010]
    10. Powerplant according to claim 9, characterized in that, said power transmission chain (30) having a transmission shaft (31) connected to an output shaft (19) of the engine (15) by a first means d an elastic coupling (32) and an input shaft (21) of the power transmission gearbox (20) by a second elastic coupling means (33), said geometric axis (103) passes through said second gear means elastic coupling (33).
    [0011]
    11. Driving installation according to any one of claims 1 to 10, characterized in that said geometric axis (103) is orthogonal to said longitudinal direction (100).
    [0012]
    12. Aircraft (1), characterized in that said aircraft (1) comprises a power plant (10) according to any one of claims 1 to 10.25
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP2910469B1|2016-05-11|
    CN104843180B|2016-09-14|
    CN104843180A|2015-08-19|
    US9359082B2|2016-06-07|
    US20150232187A1|2015-08-20|
    CA2880407A1|2015-08-19|
    CA2880407C|2016-07-05|
    FR3017566B1|2016-02-26|
    EP2910469A1|2015-08-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2718756A|1951-06-14|1955-09-27|Gen Motors Corp|Mounting and supporting structure for aircraft gas turbine power plants having reduction gearing|
    US3034583A|1959-12-22|1962-05-15|United Aircraft Corp|Collective pitch bias|
    FR1388363A|1964-03-24|1965-02-05|Bell Aerospace Corp|Airborne rotary wing machine|
    US3383933A|1966-12-06|1968-05-21|Enstrom Corp|Engine support and belt drive apparatus|
    FR2232481A1|1973-06-08|1975-01-03|Aerospatiale|
    JP2000065265A|1998-08-19|2000-03-03|Sango Co Ltd|Flexible coupling|
    FR2919363B1|2007-07-25|2010-02-12|Eurocopter France|SOFT DISK, FLEXIBLE COUPLING PROVIDED WITH SUCH A SOFT DISK, FIXING FLANGE WITH SUCH A FLEXIBLE COUPLING AND TRANSMISSION SHAFT PROVIDED WITH SUCH A FLANGE|
    EP2712808B1|2007-10-19|2020-09-02|LORD Corporation|Suspension system for aircraft auxiliary power unit with elastomeric member|
    DE102010021024B4|2010-05-19|2014-07-03|Eads Deutschland Gmbh|Main rotor drive for helicopters|
    FR2961787B1|2010-06-28|2013-03-29|Eurocopter France|METHOD AND AIRCRAFT WITH AN OPTIMIZED ROTARY SAIL TO MINIMIZE THE CONSEQUENCES OF NON-STANDARD EMERGENCY LANDING FOR OCCUPANTS OF SAID AIRCRAFT.|FR3040691A1|2015-09-08|2017-03-10|Airbus Helicopters|AIRCRAFT AND AIRCRAFT ENGINEERING GROUP|
    TWI620686B|2017-05-19|2018-04-11|林瑤章|Propulsion device|
    US10994834B2|2018-02-22|2021-05-04|Sikorsky Aircraft Corporation|Case mounted transmission AVC force generators|
    US11156128B2|2018-08-22|2021-10-26|General Electric Company|Embedded electric machine|
    法律状态:
    2015-02-20| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-17| PLFP| Fee payment|Year of fee payment: 4 |
    2018-11-30| ST| Notification of lapse|Effective date: 20181031 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1400444A|FR3017566B1|2014-02-19|2014-02-19|AIRCRAFT AND AIRCRAFT ENGINE INSTALLATION HAVING A LINK DEVICE FOR BINDING A POWER TRANSMISSION BOX AND A MOTOR|FR1400444A| FR3017566B1|2014-02-19|2014-02-19|AIRCRAFT AND AIRCRAFT ENGINE INSTALLATION HAVING A LINK DEVICE FOR BINDING A POWER TRANSMISSION BOX AND A MOTOR|
    EP15000248.3A| EP2910469B1|2014-02-19|2015-01-28|Aircraft and aircraft power plant provided with a connection device for connecting a power transmission unit and an engine|
    CA2880407A| CA2880407C|2014-02-19|2015-01-29|Aircraft and aircraft powerplant installation equipped with a linking mechanism to connect a power transmission gearbox and an engine|
    CN201510075152.2A| CN104843180B|2014-02-19|2015-02-12|Aircraft and there is the aircraft power equipment of attachment means for main-gear box and electromotor being linked together|
    US14/623,166| US9359082B2|2014-02-19|2015-02-16|Aircraft and an aircraft power plant having a connection device for connecting together a main gearbox and an engine|
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