• 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 propulsion unit (2) for an aircraft, comprising a gas generator (4) coupled by a coupling mechanism (13) to a thrust generator (6) provided with a structural box for transmitting torque ( 10), and a rigid cradle (16) supporting, firstly the thrust generator at a first suspension plane, and secondly rigidly the gas generator at a second and a second a third separate suspension planes, the cradle being intended to be connected to a structural element (14) of the aircraft via a vibration filtering connection (24).
    公开号:FR3050722A1
    申请号:FR1653824
    申请日:2016-04-28
    公开日:2017-11-03
    发明作者:Nicolas Marc Florent；Geoffroy Marie Gerard Nicq
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Background rinenvention
    The present invention relates to the general field of the suspension of a propulsion unit on a suspension structure intended to be fixed on a structural element of the aircraft that it propels. It relates more particularly to the suspension of a turboprop or turbojet to a cradle for attachment to an aircraft wing box.
    In order to isolate the vibrations created by the turboprop engines and transmitted to the aircraft, the turboprop engines are typically suspended from a cradle by means of flexible filtering suspensions. More specifically, this suspension is generally carried out at two transverse planes, namely a first front plane at a gearbox which drives the turboprop propeller, and a second rear plane at the rear of the engine. gas generator, the gearbox being rigidly and structurally connected to the gas generator. Reference can be made to WO 2014/174222 which describes an example of such a suspension.
    With such an arrangement, the flexible filtering suspensions which are used to suspend the turboprop engine cradle are more effective than the impedance of the downstream structure of the turboprop engine on which they are attached is stiff. However, the turboprop engines are generally positioned in strong cantilever ahead of the wing of the aircraft on which they are attached, which limits the structural stiffness of the cradle that supports them. The effectiveness of the suspension for filtering vibrations is therefore limited.
    In addition, the addition of flexible filtering suspensions in the dynamic chain between the turboprop generator, vibration generator, and the wing on which is fixed the cradle which is located downstream generates particular floating modes (called "flutter modes"). ) which complexify the overall dynamic adjustment of the propulsion system thus suspended.
    Furthermore, to ensure optimal operation of the turboprop engine and reduce the clearances between the stators and rotors thereof, it is important that the engine has a certain rigidity and is strictly aligned with the gearbox that drives the propeller. This constraint implies having to integrate into the propulsion unit connecting rods or a structuring casing that add mass to the assembly.
    In addition, the suspension of the turboprop engine on the cradle via two planes only, at the gearbox and the rear of the gas generator, requires to deposit in a single block the propulsive assembly consisting of the generator of gas and the gearbox when one wishes to intervene on one or the other of these elements (for example for maintenance operations). This constraint lengthens and complicates the removal operations of the engine.
    Object and summary of the invention
    The present invention therefore has the main purpose of providing a suspension mode of a propulsion unit that does not have the aforementioned drawbacks.
    According to the invention, this object is achieved by means of a propulsion system for an aircraft, comprising a gas generator coupled by a coupling mechanism to a thrust generator provided with a torque transmission structural box, and a rigid cradle supporting, on the one hand the thrust generator at a first suspension plane, and secondly rigidly the gas generator at a second and third separate suspension planes, the cradle being intended to be connected to a structural element of the aircraft via a vibration filter link. The propulsion unit according to the invention is remarkable in that it provides for a structural decoupling between the gas generator and the thrust generator, a suspension of the propulsion unit to the cradle according to three separate suspension planes, two of which are dedicated to the suspension of the gas generator and one is dedicated to the suspension of the thrust generator, and a filtering connection of vibrations between the rigid cradle and the structural element of the aircraft on which is intended to be mounted the propulsion unit.
    Such a mode of suspension has many advantages. The cradle allows an axial degree of freedom allowing the thermal expansion of the engine and makes it possible to stiffen the engine while ensuring the alignment of the low-pressure turbine shaft of the gas generator with the torque transmission gearbox. Thus, this suspension eliminates rods or a structuring casing connecting the torque transmission to the gas generator, which represents a significant gain in weight.
    The suspension mode according to the invention has two suspension planes at the gas generator (instead of a single plane in the prior art). Thus, in case of maintenance operation, it is possible to remove the gas generator without having to remove the thrust generator, which represents a significant time saving.
    In addition, the propulsion unit according to the invention is advantageously devoid of flexible suspensions between the gas generator and the cradle (the suspensions are rigid), which avoids the first flutter modes of motor on the cradle. The dynamic sizing of the propulsion unit is simplified.
    The vibration filtering functions are here transferred between the cradle and the structural element of the aircraft (for example the wing box of an aircraft), which makes it possible to benefit from a high impedance at the points of the aircraft. grip that is larger than that available on the cradle. The efficiency of these filtering functions is improved, which can allow to size stiffer suspensions so as to limit the movement of the propulsion system with all the benefits that this includes (in terms of performance in particular).
    Preferably, the cradle rigidly supports the thrust generator at the torque transmission gearbox. The structural box of torque transmission which is rigidly fixed on the cradle thus becomes a component of the cradle, which reduces the mass of the front frame of a traditional cradle. Other benefits relating to mobile part retention capabilities (from the bursting of gears of the torque transmission gearbox) can also be obtained. In addition, the presence of a torque transmission that is rigidly connected to the cradle with the suspension planes transferred to the single gas generator simplifies the engine removal maneuvers and ensures proper alignment with the help of a coupling system between the gas generator and the cardan-type thrust generator with reduced clearance.
    Also preferably, the cradle comprises a main beam which extends parallel to a longitudinal axis of the gas generator, which is rigidly attached at one end to the torque transmission box of the thrust generator to form the first yoke. suspension and which, at one end opposite, is intended to be fixed by the filtering connection to the structural element of the aircraft, and two transverse frames spaced axially from one another and rigidly fixed to the generator of gas to form the second and third suspension planes.
    The cradle may comprise two flexible suspensions intended to form the vibration filtering link with the structural element of the aircraft. The propulsion unit may consist of an airplane turboprop, in which case the thrust generator comprises a propeller which is coupled to the gas generator via a gearbox.
    Alternatively, the propulsion unit may consist of an aircraft turbojet engine in which the thrust generator comprises two counter-rotating propellers which are coupled to the gas generator via a gearbox.
    Still alternatively, the propulsion unit may consist of an airplane turbojet engine in which the thrust generator comprises a streamlined fan which is coupled to the gas generator via a gearbox.
    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: - Figure 1 is a schematic side view of a propulsion unit according to a first embodiment (application of Tmvention to a propeller turboprop); - Figure 2 is a schematic side view of a propulsion unit according to a second embodiment (application of the invention to a turbofan engine with contra-rotating propellers not keeled); and FIG. 3 is a diagrammatic side view of a propulsion unit according to a third embodiment (application of the invention to a fan-cooled turbojet engine).
    DETAILED DESCRIPTION OF THE INVENTION The invention applies to any aircraft propulsion unit which comprises a gas generator coupled by a transmission shaft to a thrust generator provided with a torque transmission structural box, such as a turboprop engine for aircraft such as that represented in FIG.
    In a known manner, this turboprop engine 2 comprises a gas generator 4 driving a thrust generator 6 in rotation, the latter comprising a propeller 8 and a gearbox 10 for transmitting the torque to the propeller.
    More specifically, the gas generator 4 comprises a low-pressure turbine shaft 12 coupled to the gearbox 10 of the thrust generator by means of a coupling mechanism 13 so as to ensure a structural decoupling between the gas generator and the thrust generator.
    The turboprop 2 is intended to be fixed on a wing box 14 of the aircraft by means of a suspension structure called cradle 16.
    This cradle 16 is in the form of a rigid structure comprising a main beam (or main spar) 18 which extends substantially parallel to a longitudinal axis XX of the gas generator 4 and a front end is fixed rigidly to the gearbox 10 of the thrust generator 6 to form a first plane of suspension PI (called plane before suspension).
    The cradle 16 also comprises two transverse frames 20, 22 spaced axially from one another and connected to the main beam 18. At their free end, these transverse frames are each fixed rigidly to the gas generator 4 for respectively form a second suspension plane P2 (called intermediate suspension plane) and a third suspension plane P3 (called rear suspension plane).
    The intermediate suspension plane of the cradle corresponding to the transverse frame 20 is of the conventional boomerang type with a low mass. Indeed, no engine torque recovery passes through this suspension plane, this torque recovery being offset at the rear suspension plane corresponding to the transverse frame 22.
    As for the rear end of the main beam 18 of the cradle (opposite to the front end fixed to the gearbox 10), it is fixed to the wing box 14 of the aircraft via a link filtering of vibrations.
    This vibration filtering connection is here carried out by means of two flexible suspensions 24. For this, various flexible suspensions may be used: laminated elastomer ball joints, struts filtered by elastomers or metal cushions, etc. We can refer to the document FR 2,917,711 which describes an embodiment of these flexible suspensions. The invention also applies to a turbojet engine with counter-rotating propellers (called "Open Rotor" in English) for an airplane such as that represented in FIG. 2.
    This turbojet engine 2 'comprises a gas generator 4' driving in rotation a thrust generator 6 ', the latter comprising two propellers 8'a, 8'b which are counter-rotating and a gearbox 10' for transmitting torque to both 8'a, 8'b propellers.
    The gas generator 4 'comprises a low-pressure turbine shaft 12' which is coupled to the gearbox 10 'of the thrust generator by means of a coupling mechanism 13' so as to ensure a structural decoupling between the gas generator and the thrust generator.
    In the example shown in FIG. 2, the propellers 8'a, 8'b are placed upstream of the gas generator 4 '("Open Rotor" in "puller" version in English) but they could be placed downstream of this one ("Open Rotor" in "pusher" version in English).
    The turbojet 2 'is intended here to be fixed on a wing box or a pylon 14' of the aircraft which it propels through a cradle 16 '. The latter is substantially identical to that described with reference to FIG. 1, namely that it is in the form of a rigid structure comprising a main beam 18 'which extends substantially parallel to a longitudinal axis XX of the gas generator 4 and a front end is fixed to the gearbox 10 'of the thrust generator 6' to form a first plane of suspension PI (called plane before suspension). This first plane of suspension is defined as the plane perpendicular to the longitudinal axis X-X of the gas generator and passing through the attachment points between the cradle 16 'and the gearbox 10'. In the case where the attachment points are shifted axially between them, we will consider the point (s) of the most advanced attachment.
    Fixing between the front end of the main beam 18 'and the gearbox 10' can be effected via a linkage rod 19 considered here as part of the cradle 16 '. The gearbox 10 'is structural, for example using a structural housing. The housings of the coupling mechanism 13 'and the low-pressure turbine shaft 12' can also be structural so that the gas generator 4 'participates in the support of the assembly formed by the thrust generator 6 'and the gearbox 10'.
    Alternatively, the cradle 16 'could be achieved by passing rods 19. For example, the front end of the main beam 18' could be advanced to the first plane of suspension PI and be connected to the gearbox 10 'by a transverse frame. This solution is however not optimal in terms of the mass of the cradle 16 'and the cantilever mass of the assembly.
    The cradle 16 'also comprises two transverse frames 20', 22 'spaced axially from each other and connected to the main beam 18'. At their free end, these transverse frames are each fixed rigidly to the gas generator 4 'to form respectively a second suspension plane (called the intermediate suspension plane) and a third suspension plane (called rear suspension plane) .
    As for the rear end of the main beam 18 'of the cradle (opposite to the front end fixed to the gear box 10'), it is fixed to the wing box or the pylon 14 'of the aircraft by the intermediate of a vibration filtering linkage consisting here of two flexible suspensions 24 '.
    The invention is still applicable to a jet-propelled turbojet engine for aircraft such as that shown in FIG.
    This turbojet engine 2 "comprises a gas generator 4" driving in rotation a thrust generator 6 ", the latter comprising a streamlined fan 8" and a reduction gear 10 "for transmitting the torque to the fan 8".
    The gas generator 4 "comprises a low-pressure turbine shaft 12" which is coupled to the thrust generator gearbox 10 "via a coupling 13" so as to ensure a structural decoupling between the gas generator and the thrust generator.
    The turbojet engine 2 "is intended to be fixed on a wing box or a pylon 14" of the aircraft which it propels through a cradle 16. This latter is substantially identical to those previously described in connection with the 1 and 2, that is to say that it is in the form of a rigid structure comprising a main beam 18 "which extends parallel to a longitudinal axis XX of the gas generator 4" and a front end is fixed of rigidly to the reducer 10 "of the thrust generator 6" to form a first plane of suspension (called plane before suspension).
    The cradle 16 "also includes two transverse frames 20", 22 "axially spaced from each other and connected to the main beam 18". At their free end, these transverse frames are each fixed rigidly to the gas generator 4 "to form respectively a second suspension plane (called intermediate suspension plane) and a third suspension plane (called rear suspension plane) .
    As for the rear end of the main beam 18 "of the cradle (opposite to the front end attached to the gear 10"), it is fixed to the wing box or pylon 14 "of the aircraft via a vibration filtering connection consisting here of two flexible suspensions 24 ".
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    REVENDICATONS
    A propulsion assembly (2; 2 '; 2 ") for an aircraft, comprising a gas generator (4; 4; 4") coupled by a coupling mechanism (13; 13'; 13 ") to a thrust generator (6; 6 '; 6 ") provided with a structural box for torque transmission (10; 10'; 10"), and a rigid cradle (16; 16 '; 16 ") supporting on the one hand the generator at the level of a first suspension plane, and secondly rigidly the gas generator at a second and a third separate suspension planes, the cradle being intended to be connected to an element the aircraft (14; 14 '; 14 ") via a vibration filtering link (24; 24'; 24").
    [2" id="c-fr-0002]
    2. Propulsion unit according to claim 1, wherein it is free of flexible suspensions between the gas generator and the cradle.
    [3" id="c-fr-0003]
    3. Propulsion unit according to one of claims 1 and 2, wherein the cradle rigidly supports the thrust generator at the torque transmission gearbox.
    [4" id="c-fr-0004]
    4. A propulsion assembly according to claim 3, wherein the cradle (16; 16 '; 16 ") comprises: a main beam (18; 18'; 18") which extends parallel to a longitudinal axis (XX) of the generator of gas, which is rigidly attached at one end to the torque transmission box of the thrust generator to form the first suspension plane and which, at an opposite end, is intended to be fixed by the vibration filtering connection to the structural element of the aircraft; and two transverse frames (20, 22; 20 ', 22'; 20 ", 22") spaced axially from each other and rigidly attached to the gas generator to form the second and third suspension planes.
    [5" id="c-fr-0005]
    5. Propulsion unit according to any one of claims 1 to 4, wherein the cradle comprises two flexible suspensions for forming the vibration filtering connection with the structural element of the aircraft.
    [6" id="c-fr-0006]
    A propulsion assembly according to any one of claims 1 to 5, consisting of an airplane turboprop (2) in which the thrust generator (6) comprises a propeller (8) which is coupled to the gas generator (4) by via a gear box (10).
    [7" id="c-fr-0007]
    7. Propulsion unit according to any one of claims 1 to 5, consisting of a turbojet engine (2 ') for aircraft in which the thrust generator (θ') comprises two counter-rotating propellers (8'a, 8'b) which are coupled to the gas generator (4 ') via a gear box (10').
    [8" id="c-fr-0008]
    8. Propulsion unit according to any one of claims 1 to 5, consisting of a turbojet (2 ") for aircraft in which the thrust generator (6") comprises a streamlined fan (8 ") which is coupled to the gas generator (4 ") through a reducer (10'0.
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    同族专利:
    公开号 | 公开日
    GB2551632B|2021-03-17|
    GB2551632A|2017-12-27|
    GB201706739D0|2017-06-14|
    US20170313431A1|2017-11-02|
    US10843806B2|2020-11-24|
    FR3050722B1|2021-07-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP2162358A1|2007-06-04|2010-03-17|Airbus Operations|Aircraft turboprop attachment device comprising hydraulic fastening means|
    FR2917711A1|2007-06-25|2008-12-26|Snecma Sa|SUSPENSION OF A TURBOMOTEUR TO THE STRUCTURE OF AN AIRCRAFT|
    US20130134257A1|2011-11-30|2013-05-30|Honeywell International Inc.|Resilient aircraft engine mounts and aircraft engine mounting systems including the same|
    FR2995282A1|2012-09-13|2014-03-14|Snecma|PYLONE FOR MOUNTING AN ENGINE TO THE STRUCTURE OF AN AIRCRAFT|
    WO2014111654A1|2013-01-21|2014-07-24|Snecma|Suspension structure with variable geometry of a turboprop engine on a structural element of an aircraft|
    WO2014174222A1|2013-04-26|2014-10-30|Snecma|Structure for suspending a twin prop-fan engine from a structural element of an aircraft|
    US2722391A|1952-05-31|1955-11-01|United Aircraft Corp|Engine mount|
    US3288404A|1964-08-24|1966-11-29|Lord Corp|Engine mounting system|
    US5176339A|1991-09-30|1993-01-05|Lord Corporation|Resilient pivot type aircraft mounting|
    GB0613929D0|2006-07-13|2006-08-23|Rolls Royce Plc|An engine core stand arrangement and method of removal and transportation of an engine core|
    FR2978730B1|2011-08-03|2013-09-27|Airbus Operations Sas|ARTICULATION CRANK FOR BLOWER HOUSINGS SUPPORTED BY THESE HOODS IN CLOSED POSITION|
    FR2987347B1|2012-02-28|2014-12-19|Snecma|CUTTING PIECE FOR A REAR SUSPENSION OF A TURBOMOTEUR TO AN AIRCRAFT PYLON AND SUSPENSION COMPRISING SUCH AN ATTACHMENT PIECE.|
    FR3053661B1|2016-07-11|2018-07-13|Safran Aircraft Engines|PROPULSION DEVICE FOR AN AIRCRAFT, SUCH AS A TURBOPROPULSEUR|
    FR3054202B1|2016-07-25|2018-07-13|Safran Aircraft Engines|CRANK FOR TURBOPROPULSEUR WITH INTEGRATED AIR INLET HANDLE|FR3057543B1|2016-10-14|2020-06-19|Safran Aircraft Engines|HORIZONTALLY OFFSET TURBOMACHINE|
    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|
    US20210047964A1|2019-08-16|2021-02-18|Pratt & Whitney Canada Corp.|Pusher turboprop powerplant installation|
    法律状态:
    2017-04-06| PLFP| Fee payment|Year of fee payment: 2 |
    2017-11-03| PLSC| Search report ready|Effective date: 20171103 |
    2018-03-22| 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 |
    2020-03-19| 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
    FR1653824A|FR3050722B1|2016-04-28|2016-04-28|PROPULSION KIT FOR FILTERED CRADLE AIRCRAFT|FR1653824A| FR3050722B1|2016-04-28|2016-04-28|PROPULSION KIT FOR FILTERED CRADLE AIRCRAFT|
    US15/498,722| US10843806B2|2016-04-28|2017-04-27|Aircraft propulsion assembly with a filtered cradle|
    GB1706739.8A| GB2551632B|2016-04-28|2017-04-27|An aircraft propulsion assembly with a filtered cradle|
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