• 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:
    Suspension system of two modules of a propulsion unit, such as two fan modules, comprising a pylon (28), a spreader (30), a part (30 ') of which is articulated on said pylon and opposite ends are articulated on connecting rods (34, 36), characterized in that it further comprises a bar (40) of torque recovery, said bar having an elongate shape and being pivotally mounted on said tower about an axis substantially parallel to an axis (B) elongation of said bar, the ends (42) opposite said bar being fixed to said rudder, on either side of said portion of the latter.
    公开号:FR3041996A1
    申请号:FR1559451
    申请日:2015-10-05
    公开日:2017-04-07
    发明作者:Thomas Gerard Daniel Riviere；Antoine Elie Hellegouarch
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Suspension system of two modules of a propulsion unit
    TECHNICAL AREA
    The present invention relates to a suspension system for two modules, such as two fan modules, of a propulsion unit, in particular an aircraft.
    STATE OF THE ART
    The applicant has undertaken work on an overall propulsion architecture for at least two distributed blowers. These objectives are to seek an optimization of the propulsive efficiency thanks to a high dilution rate, while maintaining an acceptable ground clearance and reduced blowers.
    A schematic diagram of such an assembly 10 is shown in FIG. 1. A gas generator 12 comprises, in a conventional manner, one or more compressors supplying air to a combustion chamber. The gases from the chamber drive one or more turbines connected to the compressors and here a free turbine 14. The latter is secured to a power shaft 16 coaxial with the shaft of the gas generator 12. This power shaft 16 drives by by means of suitable bevel gears, two intermediate radial shafts 18 and 18 'arranged transversely, in particular at right angles to the axis of the gas generator. The intermediate radial shafts each drive a fan shaft 20, 20 'offset and generally parallel to the axis of the gas generator. The power transmission is effected by means of first gears 22 and 22 'with bevel gears between the shaft 16 and the radial shafts 18 and 18' and second gears 24 and 24 'with bevel gears between the radial shafts 18, 18 and the blower shafts 20 and 20 '. Blower shafts 20 and 20 'each drive a fan 26, 26' of axis parallel to that of the gas generator. Such an arrangement makes it possible to achieve the objectives referred to above.
    It is known to suspend a propulsion unit to a structural element of an aircraft, by means of a pylon. For the particular architecture mentioned in the foregoing, the applicant has chosen to suspend the propulsion unit with two blowers to a single pylon.
    However, mounting two fan modules on a single tower requires both modules to generate the same thrust. In this configuration, the pylon is mounted between and in the middle of the modules, the plane of symmetry of the tower being perpendicular to the plane containing the axes of the blowers and located equidistant from these axes.
    However, in production, there is a potential difference of a few percent on the thrust of two fan modules. Moreover, there are concepts of blowers whose thrusts are voluntarily different. In the two aforementioned cases, two different thrusts generate a torque on the pylon, which requires oversizing the pylon so that it has sufficient fatigue and static resistance. This results in a significant impact on the mass of the pylon and thus the suspension system of the propulsion unit.
    To solve this problem of torque, it would be possible to position the pylon in the vertical plane passing through the center of gravity of the propulsion unit (FIG. 2) and provided that the centers of gravity of the propulsion units are positioned so that the lever arms of each of the modules are inversely proportional to their thrust. d.P = .P 'with P and P' the respective thrusts of the modules and d and the respective distances of the centers of gravity of the fan modules 26, 26 'to the pylon 28.
    Another solution would be to position the pylon 28 in the vertical plane passing through the center of gravity of the propulsion unit, and to use an asymmetrical beam 30 so that LP = L'P 'with P and P' the thrusts respective modules and L and L 'the distances of the axes of the modules 26, 26' to the pylon 28 (Figure 3).
    These two solutions are however not entirely satisfactory because they are difficult to adapt in different configurations. In case of module change, thrust variation or failure of a module, these solutions are unable to limit the movement of the modules.
    The present invention provides a solution as needed above, which is simple, effective and economical.
    DESCRIPTION OF THE INVENTION The invention proposes a suspension system of two modules of a propulsion unit, such as two fan modules, comprising a pylon, a spreader part of which is articulated on said pylon and opposite ends are articulated on connecting rods, characterized in that it further comprises a torque recovery bar, said bar having an elongated shape and being pivotally mounted on said pylon about an axis substantially parallel to an axis of elongation of said bar, opposite ends of said bar being fixed to said rudder, on either side of said portion of the latter.
    The torque recovery bar makes it possible to limit the relative displacements between the modules, to simplify the integration of the propulsion unit (reduction of the size of the joints between the nacelles of the modules and between the nacelles and the pylon, reduction of the gears. installation and the master torque of the nacelles, etc.), and to limit the stresses on the nacelles (gain of potential mase). The system according to the invention can be used to suspend two fan modules of a propulsion unit or other types of modules, such as two engines or gas generators, of a propulsion unit.
    The system according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other: said lifter is hinged by rotary links to said pylon and to said connecting rods, said axis of rotation of the bar is substantially coincident with the axis of elongation of the latter, - said ends of the bar are fixed to said rudder near said ends of the rudder, - said rudder extends substantially parallel to the axis of elongation of said bar, or has an elongated shape whose axis of elongation is substantially parallel to the axis of elongation of said bar, - said portion of the rudder is a medial portion or located midway from said ends of the rudder, - said portion of the rudder is a portion located at a distance D1 from one end of the rudder and at a distance D2 from the other end of the rudder. alonnier, D1 being different from D2, - said spreader comprises two support arms of said bar and having mounting holes of said bar, - a distance L1 between said ends of the rudder, is greater than a distance L2 between said ends of the bar bar, which is itself greater than a distance L3 between said arms of the rudder, the distances being measured along said axis of elongation of the bar,
    The present invention also relates to a propulsion assembly, comprising a gas generator and at least two fan modules, characterized in that it is equipped with a system as described above, said rods being articulated respectively on said modules of blower.
    DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will emerge more clearly on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: Figure 1 is a very schematic view of a propulsion unit with two fan modules; FIGS. 2 and 3 are very schematic views of fan module suspension systems of a propulsion unit; FIG. 4 is a very schematic view of a suspension system according to the invention; - Figures 5 to 8 are very schematic views similar to that of Figure 4 and illustrating the principle of operation of the system; FIG. 9 is a very schematic side view of the system and illustrating the mode of operation of FIG. 8; and - Figures 10 and 11 are schematic perspective views of an embodiment of the suspension system according to the invention.
    DETAILED DESCRIPTION
    FIG. 4 represents a nonlimiting embodiment of the invention which concerns a system 32 for suspending two modules of a propulsion unit which comprises at least one gas generator and at least one fan.
    In the case where the propulsion unit comprises two fan modules, as shown in FIG. 1, the suspension system 32 can be used to suspend these two modules to an aircraft.
    The system 32 essentially comprises a pylon 28, a rudder 30, rods 34, 36 thrust recovery, and a bar 40 of torque recovery.
    The tower 28 has an elongated shape and one of its longitudinal ends is articulated here on a portion 30 'of the spreader 30, which is either a median portion of the spreader or another part of the spreader as is the case in the example shown . This part 30 'takes up the thrust forces of the two fan modules.
    The rudder 30 also has an elongated shape with an axis of elongation denoted A. Each of its longitudinal ends is hinged on one end of at least one connecting rod 34, 36, the opposite end of which is intended to be articulated on the one of the fan modules.
    The portion 30 'of the crossbar 30 is located at a distance D1 from the end of the crossbar 30 connected to the connecting rod 34, and at a distance D2 from the opposite end of the crossbar 30 connected to the connecting rod 36. In the example shown , D1 is greater than D2. The articulation means 38 of the pylon 28 to the rudder 30 and the rudder to the rods 34, 36 are preferably of the ball-and-socket type.
    The torque recovery bar 40 has an elongated shape whose elongation axis is denoted B and is substantially parallel to the axis A.
    The bar 40 is fixed rigidly to the spreader 30 and is mounted by a pivotal connection on the pylon 28. The bar 40 extends close to the crossbar 30 and here has a length L2 less than that L1 of the crossbar 30. The longitudinal ends 42 of the bar 40 are fixed on the crossbar 30 on either side of the portion 30 ', and in the vicinity of the ends of the crossbar 30 in the example shown. Preferably, but not exclusively, the rigid connection between the crossbar 30 and the bar 40 is made by means of a male-female connection. In particular, as illustrated in FIGS. 10 and 11, each longitudinal end 42 of the bar 40 has an H-shaped or U-shaped section whose two branches enclose the body of the rudder 30, here of rectangular section. Of course, the rudder 30 could have a H-shaped section body or U with two branches engaging a lug provided at the longitudinal end 42. The male-female connection is of the support-plane type.
    The pylon 28 comprises two arms 44 for supporting and mounting the bar 40. Each arm 44 comprises an orifice 46 for passage and guiding in rotation about the axis B of the bar 40. In the case where the bar 40 would have a cylindrical shape, each arm 44 could comprise a tubular portion 48 defining an inner cylindrical surface for guiding the corresponding arm, as can be seen in the more specific example of FIGS. 10 and 11. The pylon 28 supports the gas generator via the inlet casing and the exhaust casing thereof to the suspension means 31 disposed upstream and downstream of the pylon 28. The suspensions 31 comprise sets of rods arranged generally and respectively in transverse planes to the direction longitudinal of the pylon 28.
    In the embodiment of Figures 10 and 11, each rod 34, 36 has an elongate shape and comprises at each of its longitudinal ends a connecting yoke 50. The rods 34, 36 extend in a plane substantially containing the rudder 30 , and therefore parallel to the axes A and B. Each yoke 50 comprises two lugs between which the corresponding end of the spreader 30 extends. The lugs of each yoke 50 bear, for example, an axis which passes through a bore of a ball joint housed in a spherical housing of the corresponding end of the rudder. The same type of swivel connection can be provided between the pylon 28 and the portion 30 'of the spreader 30. The pylon 28 may thus comprise a yoke in which the portion 30' is inserted and mounted by a swiveling connection. Each link 34, 36 articulated to a fan module can be shifted (non-parallel) with respect to the axis of the gas generator. The offset angle can be between 5 and 15 °.
    Referring now to Figures 5 to 9 which illustrate the operating principle of the system according to the invention.
    FIG. 5 represents the equilibrium system, that is to say when P1.D1 = P2.D2 with P1 and P2 the respective thrusts of the fan modules to which are connected the connecting rods 34, 36. Thus, the torsion in bar 40 is minimal. It should be noted that the relationship P1.D1 = P2.D2 is optimal and desired. Indeed, the dispersions in the manufacture of the fan modules and the different blower speeds involve a residual twist so that the result is of the order of +/- 10%.
    Figure 6 illustrates the case where a disturbance ΔΡ occurs. In this case, a torque C1 is applied on the rudder 30 which rotates about the pivot point (of the rotulante linkage of the rudder 30 to the pylon 28) of an angle a on the pylon.
    As represented in FIGS. 7 to 9, the bar 40 makes it possible to limit the displacements by applying a torque C2 which opposes the displacements by torsion of the bar 40. The magnitudes μ.ΔΡ and ρ.ΔΡ represent the forces induced by the reaction of the bar 40 (resistive torque C2 equal to the induced torque C1). For this purpose, the bar 40 of torque recovery is made of high alloy steel so as to collect the forces. Another material further comprising temperature resistance properties can of course be used for producing the bar 40.
    A propulsion unit with different thrust fan modules can thus be suspended without technical difficulty to a structural element of the aircraft.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Suspension system of two modules of a propulsion unit, such as two fan modules, comprising a pylon (28), a spreader (30) a part (30 ') is articulated on said pylon and opposite ends are articulated on connecting rods (34, 36), characterized in that it further comprises a bar (40) of torque recovery, said bar having an elongate shape and being pivotally mounted on said tower about an axis substantially parallel to an axis (B) of elongation of said bar, opposite ends (42) of said bar being fixed to said rudder, on either side of said part of the latter.
    [2" id="c-fr-0002]
    2. System according to claim 1, wherein said crossbar (30) is articulated by rotulantes links to said pylon (28) and said connecting rods (34, 36).
    [3" id="c-fr-0003]
    3. System according to claim 1 or 2, wherein said axis of rotation of the bar is substantially coincident with the axis of elongation (B) of the latter.
    [4" id="c-fr-0004]
    4. System according to one of the preceding claims, wherein said ends (42) of the bar (40) are fixed to said rudder (30) near said ends of the rudder.
    [5" id="c-fr-0005]
    5. System according to one of the preceding claims, wherein said lifter (30) extends substantially parallel to the axis of elongation (B) of said bar (40), or has an elongated shape whose axis d elongation is substantially parallel to the axis of elongation of said bar.
    [6" id="c-fr-0006]
    6. System according to one of the preceding claims, wherein said portion (30 ') of the rudder (30) is a median portion or is located midway between said ends of the rudder.
    [7" id="c-fr-0007]
    7. System according to one of claims 1 to 5, wherein said portion (30 ') of the rudder (30) is a portion located at a distance D1 from one end of the rudder and at a distance D2 from the other ends of the rudder, D1 being different from D2.
    [8" id="c-fr-0008]
    8. System according to one of the preceding claims, wherein said lifter (30) comprises two arms (44) for supporting said bar (40) and having orifices (46) for mounting said bar.
    [9" id="c-fr-0009]
    9. System according to the preceding claim, wherein a distance L1 between said ends of the spreader (30) is greater than a distance L2 between said ends of the bar (40), which is itself greater than a distance L3 between said arm (44) of the rudder, the distances being measured along said axis of elongation (B) of the bar.
    [10" id="c-fr-0010]
    10. Propulsion unit comprising a gas generator and at least two fan modules, characterized in that it is equipped with a system according to one of the preceding claims, said rods (34, 36) being hinged respectively on said fan modules.
    类似技术:
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    同族专利:
    公开号 | 公开日
    GB2557161B|2020-11-11|
    FR3041996B1|2017-10-27|
    GB2557161A|2018-06-13|
    US10287025B2|2019-05-14|
    GB201805440D0|2018-05-16|
    US20180281980A1|2018-10-04|
    WO2017060581A1|2017-04-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20050067528A1|2003-06-30|2005-03-31|Snecma Moteurs|Aircraft engine rear mount with thrust links and boomerang-shaped lever|
    EP1916406A2|2006-10-25|2008-04-30|United Technologies Corporation|Aircraft propulsion systems|
    US20150274306A1|2014-03-27|2015-10-01|United Technologies Corporation|Hybrid drive for gas turbine engine|
    US4717094A|1986-05-19|1988-01-05|The Boeing Company|Aircraft engine mount system with vibration isolators|
    FR2738034B1|1995-08-23|1997-09-19|Snecma|DEVICE FOR SUSPENDING A TURBOPROPELLER|
    FR2795386B1|1999-06-22|2001-11-09|Eurocopter France|ANTI-VIBRATION SUSPENSION DEVICE WITH TORSIONAL SPRINGS BETWEEN BEATERS AND STRUCTURE, FOR HELICOPTER|
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    US6296203B1|2000-05-24|2001-10-02|General Electric Company|Snubber thrust mount|
    FR2917713B1|2007-06-21|2009-09-25|Airbus France Sas|APPARATUS FOR ATTACHING AN AIRCRAFT ENGINE AND AIRCRAFT HAVING AT LEAST ONE SUCH DEVICE.|
    FR2918644B1|2007-07-09|2009-10-23|Airbus France Sas|ENGINE ATTACHING MACHINE FOR AN AIRCRAFT HAVING A FOUR-POINT ARTICULATED HINGE.|
    US8348191B2|2010-07-14|2013-01-08|Spirit Aerosystems, Inc.|Fail-safe aircraft engine mounting apparatus|
    FR2964364B1|2010-09-03|2012-09-28|Airbus Operations Sas|AIRCRAFT TURBOJET ENGINEERING MACHINE COMPRISING FRONT VANE FRONT FASTENERS|
    FR2969578B1|2010-12-27|2013-02-08|Snecma|DEVICE FOR SUSPENDING A TURBOJET ENGINE|
    FR3014840B1|2013-12-17|2017-10-13|Airbus Operations Sas|AIRCRAFT ASSEMBLY COMPRISING A MOTOR ATTACHING BODY EQUIPPED WITH AT LEAST ONE MANILITY SUPPORT BRACKET PENETRATING IN THE HOUSING OF THE ATTACHING MAT|
    US9738391B2|2014-03-10|2017-08-22|United Technologies Corporation|Engine installation system|
    FR3041996B1|2015-10-05|2017-10-27|Snecma|SYSTEM FOR SUSPENSION OF TWO MODULES OF A PROPULSIVE ASSEMBLY|FR3041996B1|2015-10-05|2017-10-27|Snecma|SYSTEM FOR SUSPENSION OF TWO MODULES OF A PROPULSIVE ASSEMBLY|
    US10464684B2|2016-02-01|2019-11-05|Bell Textron Inc.|Tapered sockets for aircraft engine mount assemblies|
    US10384790B2|2016-02-01|2019-08-20|Bell Textron Inc.|Engine mount assemblies for aircraft|
    US11008884B2|2018-08-10|2021-05-18|Rolls-Royce North American Technologies, Inc.|Gensets and methods of producing gensets from an engine and generator for hybrid electric propulsion|
    FR3093504A1|2019-03-05|2020-09-11|Airbus Operations |Connecting device connecting an aircraft engine and a primary structure of an aircraft mast comprising a rudder bar and a system for limiting the out-of-plane travel of the rudder, aircraft comprising such a connecting device|
    法律状态:
    2016-10-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Search report ready|Effective date: 20170407 |
    2017-09-21| 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 |
    2018-09-19| PLFP| Fee payment|Year of fee payment: 4 |
    2019-09-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-09-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-09-22| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559451A|FR3041996B1|2015-10-05|2015-10-05|SYSTEM FOR SUSPENSION OF TWO MODULES OF A PROPULSIVE ASSEMBLY|FR1559451A| FR3041996B1|2015-10-05|2015-10-05|SYSTEM FOR SUSPENSION OF TWO MODULES OF A PROPULSIVE ASSEMBLY|
    PCT/FR2016/052387| WO2017060581A1|2015-10-05|2016-09-21|System for suspending two modules of a propulsion unit|
    GB1805440.3A| GB2557161B|2015-10-05|2016-09-21|Suspension system for two modules of a propulsion unit|
    US15/764,867| US10287025B2|2015-10-05|2016-09-21|System for suspending two modules of a propulsion unit|
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