• 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 aims to overcome the problems of complexity and mass of masts made of assembled boxes. To do this, the invention proposes in fact to organize the engine-wing interface around a substantially homogeneous framework, configured to integrate the multiple functions (transmission, safety) and shelter mast equipment (fire extinguishers, heat exchanger, etc.). This framework forms a structuring unit for transmitting the forces and forming an aerodynamic fairing adapted to this framework. A mast according to the invention comprises a single structuring and multifunctional framework formed of main channels (11; 11a to 11e) accommodating equipment and transmission systems between the engine and the wing, and an arm truss (12) and nodes (13) connecting the arms, these arms (12) and / or channels (11; 1 1a to 1 1e) being adapted to fix fairing hoods (14) to form an aerodynamic fairing in a conformation predetermined by pre-established positioning of the arms (12) and the channels (11; 1 1a to 1 1e).
    公开号:FR3040043A1
    申请号:FR1557700
    申请日:2015-08-12
    公开日:2017-02-17
    发明作者:Jean Paul Giavarini
    申请人:SOGECLAIR SA；
    IPC主号:
    专利说明:

    AIRCRAFT ENGINE MAST WITH INTEGRATED MULTIFUNCTIONAL FRAME
    DESCRIPTION
    TECHNICAL AREA
    The invention relates to an aircraft mast for rigidly attaching an engine to the wing or the fuselage of an aircraft, by suspension or attachment, the mast having an integrated multifunctional frame structure.
    The invention relates to the interface between an engine and the rest of an apparatus for any type of industrial product, particularly in the fields of aeronautics and space for which the optimization of mass and cycles production conditions are essential conditions.
    In the avionics field, this link is a mast that connects all types of engines, in particular turbojets or turboprops. FIG. 1 and its magnification at the level of the mast 1 and the turbojet engine 3 (FIG. 1A) illustrate the position of a conventional aircraft mast 1 between a wing 2 and the turbojet engine 3 of this aircraft 100. The mast 1 is equipped of a linkage system to the wing 2 and the turbojet engine 3 by central and rear catches, respectively at the rear level of the fan casing 3s and at the turbine casing 3t.
    As illustrated by the front view of Figure 2, a mast 1 is constituted conventionally by the assembly of several structures: a central rigid primary structure 4C, surrounded by secondary aerodynamic structures -a front structure 4A and a rear structure 4B - On both sides of a 4K connection fairing to the wing 2 (fairing said Karman, whose location is suggested in dashed lines), and a lower aerofoil fairing 4F disposed both under the primary structure 4C and under the rear aerodynamic structure 4B. In this figure, also appear the fastening hooks of the mast on the wing and on the casings of the turbojet engine, namely respectively the fasteners 2c, 2r and 2m, 2n.
    STATE OF THE ART
    The mechanical assembly of a mast consists of several hundred elements assembled in the basic structures, and intended to respond to mechanical stress or to convey fluids while trying to meet the objectives of mass and cycle of production.
    The aircraft mast structures form a complex member and very constrained by the engine environment with multiple functions to satisfy, including: aerodynamic, structuring, thrust load recovery, transmission of electrical wiring systems , fuel supply, hydraulic and pneumatic between the engine and the wing by appropriate hoses.
    These structures usually consist of caissons formed by the assembly of upper and lower spars connected by lateral shroud panels reported and stiffened by transverse ribs. These boxes are designed to transmit to the wing the static and dynamic forces generated by the engines: mass, thrust, dynamic forces, vibrations.
    However, the assembly of such structures - generally secured by screws and rivets - has many mechanical disadvantages related to the large number of parts and therefore the complexity of this assembly: vibration, expansion, mass, aerodynamics, transmission of more systems, etc., while the engines are larger and heavier.
    To remedy these problems, a large number of improvements have been proposed.
    For example, it is known from US patent document 20120080554 to add shear pins to the front wing fasteners to achieve the recovery of the forces exerted along the longitudinal, transverse and vertical directions of the mast.
    To reduce the flexion of the front side fastener fittings on the wing, the patent document EP 2 426 051 provides to equip a central front fastener of a ball joint aligned transversely on first orifices of the front lateral fasteners.
    In the patent document US Pat. No. 8,366,039, the front fastener is flexible in order to absorb the deformations of the front fairing parts caused in particular by blade percussion of the fan.
    Furthermore, in document US Pat. No. 8,336,813, the lower rear part of the mast is curved towards the root of the corresponding wing, in order to cause a deflection of the aerodynamic flow and to compensate for variations in the aerodynamic flow. local lift due to the presence of the mast.
    To limit aerodynamic drag and therefore to reduce fuel consumption, patent document EP 2,030,892 proposes an articulation between two parts of the mast fixed to an engine casing and to the airplane wing, which allows the engine to move away from the kite in the cruising phase and bring them closer - and thus move the engine away from the ground - during the take-off or landing phase.
    In the solution described in US 6 838 955, the gradual widening of the mast in its rear portion and the mounting of the connecting elements in the rear fastener can increase the distance between these junction elements and therefore to transfer significantly higher efforts. Thus, heavier and more powerful engines can be mounted in place of those provided for a given wing.
    Other solutions provide additional means: pedals, cylinders, hydraulic pistons, connecting rods, etc. in order to oppose the longitudinal bending of the engine or to improve the return of thrust forces (see in particular the documents EP 1 571 080, EP 1 571 081 and EP 1 571 082).
    Such assemblies increase the number of parts, so the overall mass, and remain complex in their structure. Thus, the constituent boxes remain difficult approach and limited, which does not allow easy access to internal organs. Moreover, the structuring of these assemblies does not directly take into account the constraints of installation, maintenance, manufacturing, the constraints related to pressure and temperature variations as well as the regulatory requirements for safety (leak recovery, etc.). .
    All these constraints then lead to install circuits requiring connections inside the structures (with risk of leakage) and specific sealing systems and drainage areas.
    In addition, the air circuits installed in the masts include cold air intake pipes and hot air that converge inside the mast to a heat exchanger. These pipes are separate and attached to the structures. The temperature difference between these different pipes and the reception structure can be several hundred degrees Celsius. This results in differential expansion problems that can not be solved simply and effectively.
    STATEMENT OF THE INVENTION
    The invention aims to overcome the problems raised by the state of the art, particularly those related to the complexity and mass of the masts while meeting the aerodynamic requirements, by a resolutely breaking approach to that consisting in assembling an aircraft mast from dedicated caissons and connecting the assembly thus structured to the engine and to the wing by specific fasteners. The invention proposes in fact to organize the motor-motor interface around a substantially homogeneous framework, configured to integrate the multiple functions (via the circuit and pipe systems) and shelter the equipment of a mast (extinguishers, heat exchanger, etc.). This framework forms a structuring unit for transmitting the forces and forming an aerodynamic fairing adapted to this framework.
    For this purpose, the present invention relates to an aircraft mast intended to serve as an interface between an engine and the wing of an aircraft by rigid attachment means to the engine and the wing of the aircraft. aircraft. This mast has a unique structural and multifunctional framework, consisting of main channels hosting equipment and transmission systems between the engine and the wing, and a mesh of arms and connecting nodes between the arms, these arms and / or these channels being adapted to fix fairing covers. The thus fixed covers then form an aerodynamic fairing in a predetermined conformation by a predetermined positioning of the arms and channels.
    Under these conditions, the partitions between the different structures of the masts are removed and the panels, which are no longer structuring, are easily removable: access to equipment - fire extinguishers, heat exchanger - and systems - electrical wiring, hydraulic circuits, fuel and air supply systems, etc. - Is simplified and the installation constraints released by the adaptability of the connecting mesh forming the frame, while promoting a significant decrease in the mass of the assembly.
    In addition, these circuits are an integral part of the frame, which eliminates installation problems, the use of fittings and therefore the associated risks of leakage. Moreover, the integration of cold and hot air circuits to the frame eliminates the possibilities of differential expansion because the frame consists of a single material.
    According to preferred embodiments: the framework is made of metal alloy chosen between a stainless steel containing at least 10% nickel and an alloy mainly based on nickel and chromium, for example "INCONEL" alloys containing also iron, molybdenum, niobium and cobalt; these alloys make it possible to withstand temperatures and / or engine powers beyond the highest current values; the framework is made by a technology chosen from welding, molding and / or 3D printing (that is to say "in three dimensions", this technology being also called "additional layer manufacturing" (or "Additive Layer Manufacturing" in English terminology) - the framework is made either in one piece, by the application of a molding technology or 3D printing, or by several pieces made by molding and / or printing 3D and welded and / or glued together - at least one of the transmission systems is integrated with the channels in a double-skinned structure - the covers are attached to the arms and / or the channels of the framework by mechanical means removable.
    In this text, the qualifiers "upper" and "lower" refer to an engine suspension configuration under the wing in standard use. In engine configuration above the wing, these qualifiers would of course be reversed. Furthermore, the terms "front", "rear" and their equivalents are based on a standard use of the aircraft in its usual movement in flight. The qualifier "lateral" refers to a visualization along a plane parallel to the central plane of symmetry extending longitudinally in the axis of an aircraft.
    PRESENTATION OF FIGURES
    Other data, characteristics and advantages of the present invention will appear on reading the following nonlimited description, with reference to the appended figures which represent, respectively: FIGS. 1, 1A and 2, views of FIG. a conventional aircraft mast (already commented) respectively located between a turbojet engine and an aircraft wing, magnified above the turbojet engine and in lateral vision; - Figures 3 and 4, side and top views of an example of an integrated frame mast according to the invention; - Figure 5, a diagram of double skin hose for hydraulic circulation and fuel supply, and - Figure 6, a view of integrated circuits in the example of mast according to the invention.
    DETAILED DESCRIPTION
    Referring to the side and top views of Figures 3 and 4, illustrating an example of integrated frame mast 10 according to the invention realized by the application of 3D technology in this example, appear main channels 11, namely the channels 11a to 11c, connected by arms 12 forming a connecting mesh 20. The arms 12 connect the channels 11 between them and intersect on nodes 13 of stiffening of the entire frame 10.
    Non-structural covers 14 are fixed by removable means - bolts, clips, collars or equivalents - to the arms 12 of the lattice 20 and the channels 11. In Figures 3 and 4, a portion of the covers 14 is not shown to allow viewing of the mast frame 10, the frame 10 being completely covered with covers 14 during its installation on an aircraft wing. And all the hoods form a fairing whose aerodynamics are controlled by the conformation that results from the relative positioning of the channels 11 and arms 12 of the mesh 20.
    Advantageously, walls 31 of the frame 10 form a thermally insulating housing 30 for a heat exchanger (not shown). In general, thermal and / or electrical insulation walls - forming an integral part of the framework - may be provided between channels and truss arms to form dwellings, for example for a fire extinguisher or other equipment.
    More specifically, the channels, a double-skinned channel 11a P1 and P2, as shown in the diagram of Figure 5, host circuits, for example hydraulic pipes or a fuel supply circuit (see figure). 6). Channels 11d and 11e also house air hoses for air conditioning in the cabin.
    The side view of FIG. 6 illustrates the hydraulic hoses 41a - advantageously configured in a homogeneous sheet -, the fuel circuit 41b and the extinguishing pipe 41c to be integrated respectively in the channels 11a, 11b, and 11c (see FIGS. 4 and 5) of the mast frame 10 according to the invention. These channels are sized and configured to directly accommodate these circuits and pipes.
    In particular, the fuel circuit 41 b is integrated in double skin in the channel 11b, the conformation of the sealed outer skin being controlled by the structural and aerodynamic strength constraints of the frame 10 while respecting the inner diameters and the geometries as well as the interfaces on the wing 2 and the engine 3 (see Figure 1).
    The invention is not limited to the embodiments described and shown. Thus, the dimensioning of the frame advantageously incorporates the over-constraints related to the thermal gradient between the wing and the engine. Furthermore, the material used to make the framework according to the invention may be a stainless steel containing nickel or an alloy mainly based on nickel and chromium, such as alloys "INCONEL" 625 or 718 also containing iron, molybdenum, niobium and cobalt.
    Alternatively to the attachment of the mast under the wing of an aircraft, the mast can be attached, in equivalent embodiments, directly on a fuselage or on the wing of an aircraft.
    Furthermore, the frame can be made in one piece or in several pieces secured by welding, gluing or any other means of fixing such an assembly. The basic technology used is 3D printing and / or molding.
    In addition, the fasteners on the wing and the engine of a frame mast according to the invention include those used in the multi-box structure masts described with reference to Figures 1A and 2.
    In addition, the arm density in the lattice is substantially constant in the frame but may have a higher value in some parts of the mast, for example to form a rear lower fairing.
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1. Aircraft mast intended to serve as an interface between an engine (3) and the wing (2) or the fuselage of an aircraft by rigid attachment means to the engine (2m, 2r) and to the wing ( 2c, 2r) of the aircraft, characterized in that it has a unique structural and multifunctional framework (10), formed of main channels (11; 11a to 11e) accommodating equipment and transmission systems (41a to 41c) between the motor (3) and the wing (2), and a mesh (20) of arms (12) and nodes (13) connecting between the arms (12), these arms (12) and / or channels (11; 11a to 11e) being adapted to fix fairing hoods (14) to form an aerodynamic fairing in a predetermined conformation by a predetermined positioning of the arms (12) and channels (11; 11a to 11e).
    [2" id="c-fr-0002]
    2. aircraft mast according to claim 1, wherein the frame (10) is a metal alloy selected between a stainless steel containing at least 10% nickel and an alloy mainly based on nickel and chromium.
    [3" id="c-fr-0003]
    3. aircraft mast according to one of claims 1 or 2, wherein the frame (10) is made by a technology selected from welding, molding and / or 3D printing.
    [4" id="c-fr-0004]
    4. aircraft mast according to the preceding claim, wherein the frame (10) is made either in one piece, by the application of a molding technology or 3D printing, or several pieces made by molding and / or 3D printing and welded and / or glued together.
    [5" id="c-fr-0005]
    5. Aircraft mast according to one of the preceding claims, wherein at least one of the transmission systems (41a) is integrated with the channels (11a) in a double-skinned structure (P1, P2).
    [6" id="c-fr-0006]
    Aircraft mast according to one of the preceding claims, in which the covers (14) are fixed to the arms (12) and / or to the channels (11; 11a to 11e) of the framework (10) by means mechanical dismountable.
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    同族专利:
    公开号 | 公开日
    CN107922052A|2018-04-17|
    BR112018002091A2|2018-09-18|
    EP3334653B1|2019-06-19|
    EP3334653A1|2018-06-20|
    FR3040043B1|2019-04-12|
    US20180222595A1|2018-08-09|
    CA2995134A1|2017-02-16|
    WO2017025288A1|2017-02-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2931133A1|2008-05-14|2009-11-20|Airbus France Sas|MOTOR ATTACHING MACHINE COMPRISING MEANS FOR FIXING LONGERONS AND AGENCY PANELS OUTSIDE OF THE INTERIOR SPACE OF HOUSING|
    US20110121132A1|2009-11-23|2011-05-26|Spirit Aerosystems, Inc.|Truss-shaped engine pylon and method of making same|
    US20120104162A1|2010-10-28|2012-05-03|Spirit Aerosystems, Inc.|Pylon arrangement for open structure|
    US5123242A|1990-07-30|1992-06-23|General Electric Company|Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine|
    US6838955B1|1996-08-23|2005-01-04|Hub Technologies, Inc.|Data processing device|
    FR2867157B1|2004-03-04|2006-06-02|Airbus France|MOUNTING SYSTEM INTERFERRED BETWEEN AN AIRCRAFT ENGINE AND A RIGID STRUCTURE OF A FIXED HINGING MACHINE UNDER A VESSEL OF THAT AIRCRAFT.|
    FR2867158B1|2004-03-04|2007-06-08|Airbus France|MOUNTING SYSTEM INTERFERRED BETWEEN AN AIRCRAFT ENGINE AND A RIGID STRUCTURE OF A FIXED HINGING MACHINE UNDER A VESSEL OF THAT AIRCRAFT.|
    FR2867156B1|2004-03-04|2006-06-02|Airbus France|MOUNTING SYSTEM INTERFERRED BETWEEN AN AIRCRAFT ENGINE AND A RIGID STRUCTURE OF A FIXED HINGING MACHINE UNDER A VESSEL OF THAT AIRCRAFT.|
    US7104306B2|2004-06-14|2006-09-12|The Boeing Company|Cast unitized primary truss structure and method|
    FR2873988B1|2004-08-05|2007-12-21|Airbus France Sas|AIRBORNE TURBOJET ENGINEERING MACHINE|
    FR2891243B1|2005-09-26|2009-04-03|Airbus France Sas|ENGINE ATTACHING MAT FOR AN AIRCRAFT|
    FR2891252B1|2005-09-28|2007-10-26|Airbus France Sas|MAT TO MONOLITHIC BODY|
    FR2891248B1|2005-09-28|2009-05-01|Airbus France Sas|ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING AN ENGINE AND A MACHINE FOR ATTACHING SUCH A MOTOR|
    CN100509561C|2006-05-30|2009-07-08|空中客车德国有限公司|Assemblage for hanger bracket with engine|
    FR2902406B1|2006-06-20|2008-07-18|Airbus France Sas|FITTING FOR SUSPENSION MAT FROM A TURBOMOTEUR TO AN AIRCRAFT WING|
    FR2920408B1|2007-08-30|2010-02-19|Snecma|PYLONE OF SUSPENSION OF AN ENGINE UNDER AN AIRCRAFT WING|
    US8205825B2|2008-02-27|2012-06-26|Spirit Aerosystems, Inc.|Engine pylon made from composite material|
    FR2935353B1|2008-09-03|2010-09-10|Airbus France|MAT FOR THE SUSPENSION OF A TURBOMOTEUR UNDER AN AIRCRAFT WING|
    FR2939103B1|2008-12-01|2011-01-21|Airbus France|HYDRAULIC SYSTEM FOR TRANSMITTING EFFORTS BETWEEN AN AIRCRAFT TURBOPROPULSOR AND A HITCHING DEVICE|
    US7966921B1|2009-04-01|2011-06-28|The United States Of America As Represented By The Secretary Of The Navy|Aircraft wing-pylon interface mounting apparatus|
    FR2964364B1|2010-09-03|2012-09-28|Airbus Operations Sas|AIRCRAFT TURBOJET ENGINEERING MACHINE COMPRISING FRONT VANE FRONT FASTENERS|
    FR2965548B1|2010-10-01|2012-10-19|Airbus Operations Sas|AIRCRAFT ENGINE ATTACHMENT MAT COMPRISING TWO FRONT SAILING ATTACHES WITH ORTHOGONAL SHEARING PONDS|
    US8661833B2|2011-01-14|2014-03-04|Hamilton Sundstrand Corporation|Bleed valve module|
    US20140151497A1|2012-12-04|2014-06-05|Ge Aviation Systems Llc|Engine pylon for an aircraft|
    JP6419437B2|2014-02-28|2018-11-07|三菱航空機株式会社|Aircraft engine pylon and aircraft|FR3061148A1|2016-12-23|2018-06-29|Airbus Operations|SEMI-CONTINUOUS FASTENING OF A MOTOR ATTACHING MAT TO A FIXING DEVICE BELONGING TO THE VESSEL OF AN AIRCRAFT|
    CN109592050A|2018-11-02|2019-04-09|中国航空工业集团公司西安飞机设计研究所|A kind of aircraft engine hanging structure|
    CN109703773A|2018-12-28|2019-05-03|西北工业大学|It is a kind of to positive unmanned plane rocket thrust transferring structure|
    法律状态:
    2016-07-19| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-17| PLSC| Search report ready|Effective date: 20170217 |
    2017-08-24| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-28| PLFP| Fee payment|Year of fee payment: 4 |
    2019-08-27| PLFP| Fee payment|Year of fee payment: 5 |
    2021-05-07| ST| Notification of lapse|Effective date: 20210405 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557700|2015-08-12|
    FR1557700A|FR3040043B1|2015-08-12|2015-08-12|AIRCRAFT ENGINE MAST WITH INTEGRATED MULTIFUNCTIONAL FRAME|FR1557700A| FR3040043B1|2015-08-12|2015-08-12|AIRCRAFT ENGINE MAST WITH INTEGRATED MULTIFUNCTIONAL FRAME|
    US15/750,527| US20180222595A1|2015-08-12|2016-07-20|Aircraft engine pylon with inbuilt multifunctional framework|
    CA2995134A| CA2995134A1|2015-08-12|2016-07-20|Aircraft engine pylon with inbuilt multifunctional framework|
    BR112018002091-5A| BR112018002091A2|2015-08-12|2016-07-20|aircraft mast|
    CN201680047499.9A| CN107922052A|2015-08-12|2016-07-20|Aircraft engine hanger with built-in multifunctional frame|
    EP16741025.7A| EP3334653B1|2015-08-12|2016-07-20|Aircraft engine pylon with inbuilt multifunctional framework|
    PCT/EP2016/067266| WO2017025288A1|2015-08-12|2016-07-20|Aircraft engine pylon with inbuilt multifunctional framework|
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