• 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 present invention relates to an aircraft comprising a wing (3) comprising a first upstream spar and a second downstream spar extending in a span direction of said wing, and, at least one propulsion unit supported by the wing, propulsion assembly comprising a turboprop and a propeller. According to the invention, the helix comprises an outer annular casing fixed on an extrados surface of the wing (3), and at least the first upstream spar via at least a first and a second fastener.
    公开号:FR3041992A1
    申请号:FR1561014
    申请日:2015-11-16
    公开日:2017-04-07
    发明作者:Kevin Morgane Lemarchand；Tewfik Boudebiza；Gilles Alain Charier；Nathalie Nowakowski
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    Aircraft with Propulsion means with Remote Blower Field of the Invention
    The present invention relates to the field of aeronautical propulsion. It relates to the arrangement of propulsion engines on an aircraft.
    STATE OF THE ART The natural evolution of multi-jet turbojets is to reduce the specific thrust by increasing the dilution ratio, ie the ratio of the secondary flow passing through the blower (s) to the primary air flow passing through the engine. central body with combustion chamber and turbines. In the case of conventional turbojet engines with a turbine connected directly to the fan, the dilution rates are limited by the peripheral speed at the top of the fan blades. The blower architectures driven by a speed reducer - or UHBR (ultra high bypass ratio) - very high dilution rate - partially address this problem by optimizing the efficiency of the turbine at a moderate fan speed .
    However, the additional increase in the dilution rate on such engines hung under wing would be constrained by the minimal ground clearance of the aircraft to respect to the extent that the dilution ratio is related to the diameter of the fan. In addition, always higher diameters would lead to the architecture of the power transmission more complex, causing a significant increase in weight.
    A solution of assembling several blowers on remote axes, that is to say laterally offset, allows an increase in the dilution ratio while maintaining a suitable ground clearance under the wing of the aircraft.
    The implementation of these architectures involves a number of constraints to be taken into account and to respect. These are in particular the following constraints: - Problem related to the realization of the thrust reversal function.
    On conventional turbojet engines the inversion of the thrust is achieved by opening the cowl of the fan and the ejection of the inverted air on the outer sides of the nacelle. The ejection of the produced airflow is not possible downwards, at 6 o'clock, because of the proximity of the ground. It is impossible upward at 12 o'clock because of the presence of the engine attachment pylon and the wing. It is impossible also on the inner sides for the same reasons related to the obstacles encountered. The absence or limitation of the thrust reversal function increases the runway length necessary to land the aircraft. It is therefore necessary to land only on airports with large runway, and the time spent on the ground by the aircraft is increased because the aircraft has moved further away from the boarding area, all these consequences implies a loss of earnings for the airline company. - Strong penalty in mass of the assembly formed by the nacelle and the suspension of the engine.
    On conventional turbofan engines, the center of gravity of the assembly formed by the turbomachine and its suspension must be positioned between the front and rear clashes of the pylon, so as not to create instability. However, when the blower or blowers are offset on the sides of the gas generator, having a second blower module near the first causes the location of the center of gravity upstream of the turbomachine / suspension assembly. This arrangement near the upstream attachment point is a source of instability in flight. In addition, the center of gravity being eccentric with respect to the axis of the gas generator, it contributes to impose moments of torsion and bending to the pylon. - Problem related to lack of interchangeability of blowers.
    On a conventional turbo blower, there is no symmetry constraint. On the other hand, in the case of a multi-fan architecture with a laterally offset fan, an engine located on one side can not be moved under the wing on the opposite side of the aircraft without affecting the mounting of the modules. - Optimization of the specific consumption gain.
    In the context of an architecture with a single tower, it prevents the pylon from working in torsion and flexion while limiting the impact of these forces on the mass of the suspension by controlling the thrusts provided by the two blowers. To remove this constraint would be to add a degree of freedom in the performance model of the propulsion system. This would be a possible factor of gain of specific consumption.
    The object of the present invention is to preserve the advantages of the multi-fan architecture while proposing a new configuration to respond to the problems observed, as mentioned above, in the case of multi blowers with remote fan blowers, namely: - Limitation of the thrust reversal function; - Mass penalties on the pylon / suspension part due to a center of gravity too far from the wing; - Risk of loss of performance with a consumption of games due to the provision of a center of gravity eccentrically of the axis of the turbomachine; - No interchangeability of left and right engines, producing additional costs in production but also during maintenance; - Gain in specific consumption not favorable enough.
    Presentation of the invention
    It is possible to achieve these objectives, in accordance with the invention, with an aircraft comprising at least one wing comprising a first upstream spar and a second downstream spar extending in a span direction of said wing, and at least one fixed propulsion means. to a wing the propulsion means comprising at least one turbine engine and a propeller, the propeller comprising an outer annular casing fixed on an extrados surface of the wing, and at least the first upstream spar via at least a first and a second fasteners.
    By turbine engine, here comprises a multi-flow turbojet engine, in particular with two flows with a streamlined fan and a gas generator which is a gas turbine engine, the fan being disposed on the upstream side of the gas generator. It can also be a turboprop, the fan then being a propeller not faired. It can also be a turbocharged jet engine with counter-rotating propellers. The term "propeller" will be used later but it will include single or multiple blowers as well as single or multiple propellers.
    According to a feature of the invention, the outer annular casing is attached to one of the longitudinal members via a first pylon.
    In particular, the propeller comprises at least one movable hub, a central casing supporting the movable hub and a transmission mechanism, and radial arms connecting the central casing to the outer annular casing.
    According to a characteristic of the invention, the outer annular housing comprises an air intake lip arranged upstream of a plane transverse to the leading edge of the wing.
    According to a preferred embodiment, one of the turbine engine and the propeller is fixed under the wing and the other is fixed on the wing.
    In particular, the axes of the turbine engine and the propeller are located in the same vertical plane.
    According to a characteristic of the invention, the turbine engine is suspended from the wing via a second pylon.
    According to another characteristic, the turbine engine comprises at least one turbine stage driving the offset propeller. Preferably the offset propeller is driven mechanically by said turbine.
    According to another characteristic, the turbine engine and / or the propeller comprises a thrust reverser means. More particularly, at least that of the turbine engine or propeller which is mounted on the wing comprises a thrust reverser means adapted to deflect the flow which passes through it at least upwards and / or laterally.
    Alternatively, at least the turbine engine fixed under the wing comprises a thrust reversal means adapted to deflect the air flow therethrough at least partly laterally.
    BRIEF DESCRIPTION OF THE FIGURES The invention will be better understood, and other objects, details, characteristics and advantages thereof will appear more clearly on reading the following detailed explanatory description of two embodiments of the invention. given by way of purely illustrative and non-limiting examples, with reference to the attached schematic drawings.
    On these drawings:
    Figure 1 shows schematically in axial section an example of engine architecture associated with the wing of an aircraft, according to the invention; Figure 2 shows the diagram of an assembly seen from the front;
    Figure 3 shows a mounting variant, according to the invention and Figure 4 shows a mounting variant, according to the invention.
    DETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION
    Referring to Figure 1, the propulsion assembly 1 is shown mounted on the wing 3 or side wing lift of an aircraft. The aircraft comprises at least two such propulsion units, one on each wing. Each wing comprises in known manner a first upstream structural spar and a second structural downstream structural spar extending from a fuselage in a span direction. Each wing 1 comprises a surface 6 upper so-called extrados and an opposite lower surface 8 called lower surface, and which are connected to each other by a leading edge upstream and a trailing edge downstream of the wing 3 The propulsion assembly comprises a turbojet 5 of axis XX suspended from a pylon 7 under the wing forward with respect to the leading edge of the wing. The turbojet engine 5 comprises according to this embodiment a fan 51 upstream, the upstream being defined relative to the direction of movement of the aircraft in flight. The fan is streamlined by a 51C housing. Downstream of the blower is the gas generator formed here of a dual-body gas turbine engine: a low pressure LP body, formed of a compressor 52 and a turbine 53, and a body High pressure HP, coaxial with the LP body, with a compressor 54 and a turbine 55. A combustion chamber 56 is fed with compressed air from the compressors 52 and 54 in series. The gases produced in the combustion chamber 56 set in motion successively the turbine 55 HP and 53 BP which respectively drive the two compressors, 54HP and 52 BP. The LP turbine drives the streamlined fan 51 directly or by a suitable gearbox. The secondary channel downstream of the fan 51 is according to this embodiment, shorter than the channel of the primary flow. The secondary flow and the primary flow, the latter forming the gases produced by the combustion chamber, are separated, the two streams are ejected into the atmosphere by separate, concentric nozzles. The turbojet could however be mixed flow, the two streams being mixed upstream of the gas ejection nozzle.
    Downstream of the LP turbine 55, the gases of the primary flow drive a free turbine. This turbine 57 drives a shaft 57a in rotation. The propulsion assembly comprises, according to the invention, a propeller. According to the embodiment shown, it is a fan 9 of axis YY, with its housing 91. In particular, the fan comprises a plurality of fan blades 93 which are mounted and which extend radially. from the fan shaft 92 rotated relative to the housing 91. The housing 91 has a generally cylindrical shape. The casing 91 here outer annular also comprises an inner hub 94 through which the fan shaft 92 YY axis and a ferrule defining an annular air stream providing the propulsion force. The hub and the ferrule are connected by stator vanes known as rectifiers or guide vanes 95 for the English designation "Outlet Guide Vanes" (OGV) for straightening the cold flow generated by the fan 51 flowing in the annular vein. These stator vanes are for at least part of them mechanically structuring and ensure the transmission of mechanical loads between the outer annular housing 91 and the hub 94. The mechanical strength of the entire fan is also provided by a plurality radial arms 96 arranged downstream of the stator vanes which connect the hub to the transmission mechanism housed in the outer annular casing 91.
    The fan is mounted on the wing, in particular on the extrados surface 6 by means of a pylon 11 or any other equivalent structure forming a support for the fan on the wing. The blower can be detached at the top of the wing or be flush with the wing depending on the desired aerodynamic conditions. The axis of the fan 9 is substantially parallel to that of the turbojet engine 5.
    In the example where the fan 9 is flush with the wing, or even integrated in the wing as shown in Figure 4, the propulsion assembly comprises suspension means comprising a first attachment upstream and a second attachment downstream connected to the outer annular housing 91. The first and second fasteners are also connected to the first upstream spar of the wing.
    Alternatively, the first attachment is connected to the first upstream spar and the second attachment is connected to the second downstream spar.
    Fasteners can be attached directly to the spar or via a pylon.
    The turbine engine may also be arranged by means of two fasteners to the upstream spar or, alternatively, an upstream attachment to the upstream spar and an attachment to the downstream spar.
    According to this representation, the plane of rotation of the fan is upstream of the leading edge of the wing 3. More specifically, the outer annular casing 91 comprises an air intake lip arranged upstream of a transverse plane. at the leading edge of the wing 3.
    The rotor of the fan is rotated by an intermediate shaft 13. This is, in this example, made in two parts. A lower portion 13i under the wing and an upper portion 13s. The two parts are connected to each other by a suitable coupling 13a. This coupling allows disassembly of the two parts of the intermediate shaft. It also ensures the transmission of motion in the event of non-alignment resulting from deformations in the structure likely to occur in flight. The lower part 13i of the intermediate shaft is rotated by the output shaft 57a of the free turbine 57 through a conical gear 13ic. At the other end the upper portion 13s meshes with the drive shaft 92a of the fan 9 via a bevel gear 13sc.
    In operation, the turbine engine 5 formed by the turbojet engine provides part of the thrust on the aircraft by the entire primary and secondary flow that is produced. The free turbine 57 rotates the rotor of the fan 9 by the intermediate shaft 13 thus providing another part of the thrust.
    Compared to an arrangement of the prior art where the remote blower would be at the same axial level as the fan 51 of the turbojet, the center of gravity CG of the propulsion unit is shifted downstream because the remote blower 9 is downstream relative to the fan 51. This provision is favorable in terms of stability in flight.
    Figure 2 shows the arrangement of the propulsion assembly. The axes of the turbojet engine 5 and the fan 9 are advantageously parallel to each other and in the same vertical plane which is favorable from the point of view of the stability in flight because the thrust forces are in the same vertical plane. This is also favorable in the accidental case of a single thrust reverser, either on the wing propeller or on the wing propeller, which would activate without the other. In such a case, the pylon would be subjected to less significant effort compared to a configuration with two propellers laterally deported under wing.
    It is also observed that by this means the dilution ratio is increased relative to that of the turbo reactor but without the ground clearance was impacted.
    An aerodynamic fairing can be arranged to enhance the aerodynamic performance of the power package. In particular, this fairing could be connected to the skin of the wing and wrap the upstream upstream and downstream and the pylons. The fairing may comprise a first fairing portion intended to cap the nose of the pylons and a second fairing portion connecting the extrados surface of the wing to the outer annular casing 91 of the fan. The second part of fairing can end advantageously downstream of the pylon by connecting to a distal tip portion connecting the first fairing portion and the trailing edge. The second part of fairing can still form in the upper part a console the upstream portion of the housing 91 of the fan so provide an aerodynamic connection.
    Fixing the second fairing portion on the downstream of the pylon may be provided by terminal ribs bolted to longitudinal ribs of the downstream beam. The fastening may be reinforced by rivets or bolts passing through the pylon and penetrating openings provided in the second fairing portion. The distal fairing portion may be secured by interlocking ribs bolted therebetween.
    Alternatively, the annular fan casing and the turbojet casing can be fixed on the same pylon having a unitary or compound structure, so as to balance the thrusts with respect to the wing around the torsion axis thereof and thus to give the center of thrust an advantageous position relative to the center of drag. The balancing of the weights with respect to the torsion axis is also very favorable to the stability of the propulsion assembly and reduces the fatigue of the wing. In addition, the propulsion assembly is placed at an optimum distance from the axis of the fuselage and this over an appreciable length of the wing. Furthermore, the bending moment of the wing linked to the weight of the blowers and the turbojet engine can be reduced relative to a conventional arrangement where the blowers and turbojet engines are staggered along the wing.
    The superposition of the blower and the turbine engine in a vertical plane facilitates their assembly reduces yaw movements caused by blowers and turbine engines spaced apart from each other along the wing, particularly in case of failure of one of the blower and the turbine engine. The surface required for the rudder or its steering angle are thus limited. The propulsion assembly with the turbine engine and the fan arranged vertically can advantageously replace a conventional propulsion unit. This allows various choices of blower and / or turbine engine. The dimensions of the housings can be reduced. As a result, the free space on the ground relative to the lower part of the turbine engine is made less critical, which makes it possible to equip the aircraft with a shorter and lighter landing gear with consequently easy access. to the cabin and the bunkers.
    In the case where the fan and the turbine engine are arranged on the same pylon, it can in one piece. Alternatively, it can be in several parts. In the case where the pylon is in one piece, the lower part of the pylon is fixed in point being substantially located in line with the downstream side. In the case of a pylon in several parts, for example two parts, the pylon comprises two front and rear beams, the rear beam is also attached at a point located at the lower rear of the front beam.
    The fan and the turbine engine can be fixed on the same pylon at two points of attachment with respect to the turbine engine, such as in the middle part of the wing and upstream of the pylon and at two points of attachment for the fan.
    The pylon in one piece or in two parts assembled, is preferably constituted by a ribbed beam.
    In a particular embodiment not shown, the pylon may be constituted by the assembly of a lower front beam and a rear upward beam, each beam may comprise a ribbed profiled core respectively rectangular section, provided with regularly staggered ribs and reinforcing ribs. The cores can be covered by covers respectively and are laterally bordered by preferably plates which have reinforcing ribs on their inner face.
    The front beam may comprise in known manner a triangular nose in a region at the front of the pylon. On the other hand, it has a donkey profile in the region of attachment of the turbine engine to the wing box and the rear face of the core can be located substantially in the plane of the rear face of the wing box.
    With reference to FIG. 4, at the fixing point B, the cover of the webs of the beam 7 has an orifice for an anchor fixed on the face of the box.
    Finally at the point C, the face of the lower beam 7 carries an ear on either side of which are mounted two V-links articulated to a double ear secured on the rear face of the box. As seen in Figure 5, the double ear is preferably formed at the base of a double fork whose branches are fixed over the entire height of the face of the box of the wing and enclose it. This connection system makes it possible to absorb all the stresses that may be subjected to the connection between the lower beam 7 and the caisson 2 in the various operating conditions of the aircraft. The mutual subjection of the beams 7, 8 and the caisson 2 at the faces of these parts is completed in the following manner: at the fixing point D, the upper parts of the faces each carry a double clevis with two ears respectively, connected by vertical links. The connection is completed by an oblique horizontal rod disposed between two ears.
    In the lower part, around the point E, the fixing is provided by a yoke formed at the bottom of a face into which an ear fixed to the base of a face of the beam 8. The fastening means thus provided confer on all the rigidity and security desirable.
    Another advantage of the solution appears in this figure. The thrust reversal doors can be arranged in five sectors without there being a risk of interference of the reverse flows with a surface of the aircraft. In M or i2 the two sectors are lateral and allow to generate inverted flows, free of interference with the fuselage, the wing or the ground. In particular, the thrust reversal doors are installed on either side of the vertical plane passing through the axis of the turbojet and following an angular sector between + 60 ° and -60 ° relative to a horizontal plane perpendicular in the vertical plane and between 120 ° and -120 ° with respect to the horizontal plane by considering that the perimeter of the annular housing forms a circle. The perimeter portion where inverter doors can be integrated is maximized.
    It is still possible to arrange the thrust reversers on the fan 9. Here three orientations are possible: two lateral, i3 and i4, and one, i5, upwards. The addition of an additional sector i5 with respect to a conventional under-wing fan brings a gain in efficiency of the thrust reversal. Advantageously, but not exclusively, the thrust reversal doors are installed in an angular sector between -60 ° and -120 ° relative to the horizontal plane perpendicular to the vertical plane passing through the axis of the turbojet. The invention is not limited to this embodiment. The turbojet can be another turbine engine such as a turboprop with a propeller instead of the fan 51 or the fan 9 can be replaced by a propeller.
    Figure 3 shows an alternative embodiment where the arrangement of the turbine engine 5 is on the wing while that of the fan 9 'is under the wing. We find the same elements as in the embodiment of Figure 1 but inverted with respect to the wing 3. In this example, the outer annular casing of the fan can be directly connected to the upstream and downstream beams of the wing or be supported by the pylon. The air inlet of the outer annular housing 91 is arranged upstream of the plane transverse to the leading edge of the wing 3. The transmission mechanism connects the remote blower to the turbine engine disposed on the upper surface of the wing.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Aircraft comprising: - a wing (3) comprising a first upstream spar and a second downstream spar extending in a span direction of said wing; and at least one propulsion unit supported by the wing, the propulsion assembly comprising a turbine engine and a propeller, characterized in that the propeller comprises an outer annular casing fixed at least to the first upstream spar via at least a first and a second attachment.
    [2" id="c-fr-0002]
    2. Aircraft according to claim 1, characterized in that the outer annular casing is attached to the downstream beam via the second fastener.
    [3" id="c-fr-0003]
    3. Aircraft according to claim 1 or 2, characterized in that the outer annular casing is attached to one of the longitudinal members via a first pylon.
    [4" id="c-fr-0004]
    4. Aircraft according to any one of the preceding claims, characterized in that the propeller comprises at least one movable hub, a central casing supporting the movable hub, and radial arms connecting the central casing to the outer annular casing.
    [5" id="c-fr-0005]
    5. Aircraft according to any one of the preceding claims, characterized in that the outer annular housing comprises an air intake lip arranged upstream of a plane transverse to the leading edge of the wing.
    [6" id="c-fr-0006]
    6. Aircraft according to any one of the preceding claims, characterized in that one of the turbine engine and the propeller is fixed under the wing and the other is fixed on the wing, the axis of the turbine engine and of the propeller being located in the same vertical plane.
    [7" id="c-fr-0007]
    7. Aircraft according to claim 6, characterized in that the turbine engine is suspended from the wing via a second pylon.
    [8" id="c-fr-0008]
    8. Aircraft according to any one of the preceding claims, characterized in that the turbine engine is a multi-jet turbojet engine or a turboprop.
    [9" id="c-fr-0009]
    9. Aircraft according to one of the preceding claims wherein the turbine engine (5) comprises at least one free turbine stage (57) driving said propeller (9).
    [10" id="c-fr-0010]
    10. Aircraft according to one of the preceding claims wherein the turbine engine and / or the propeller is equipped with a thrust reverser.
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    同族专利:
    公开号 | 公开日
    FR3041992B1|2019-05-10|
    US10850859B2|2020-12-01|
    US20170240286A1|2017-08-24|
    FR3041991B1|2020-05-01|
    FR3041991A1|2017-04-07|
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    法律状态:
    2016-11-09| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-07| PLSC| Publication of the preliminary search report|Effective date: 20170407 |
    2017-10-20| 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 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 5 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 6 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1559452A|FR3041991B1|2015-10-05|2015-10-05|AIRCRAFT WITH REMOTE BLOWER PROPULSION|
    FR1559452|2015-10-05|US15/284,895| US10850859B2|2015-10-05|2016-10-04|Aircraft with a propulsion unit with offset fan|
    US15/765,404| US11015521B2|2015-10-05|2016-10-05|Aircraft propulsion assembly equipped with a main fan and with at least one offset fan|
    GB1616883.3A| GB2544625B|2015-10-05|2016-10-05|Aircraft with a propulsion unit with offset fan|
    PCT/FR2016/052569| WO2017060629A1|2015-10-05|2016-10-05|Aircraft propulsion assembly equipped with a main fan and with at least one offset fan|
    US15/764,864| US11174781B2|2015-10-05|2016-10-05|Aircraft propulsion assembly equipped with a main fan and with a least one offset fan|
    PCT/FR2016/052567| WO2017060628A1|2015-10-05|2016-10-05|Aircraft propulsion assembly equipped with a main fan and with at least one offset fan|
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