• 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 an aircraft turbojet engine nacelle, the nacelle (1) having a rear section (4) without a lower bifurcation, the rear section comprising a thrust reversal system, the thrust reversal system comprising a movable cowl (20), the nacelle being characterized in that it comprises a guide system integral in translation with the movable cowl (20), said guide system cooperating with at least one fixed slider relative to the nacelle (1) , the guide system and the slider being arranged near the so-called "6 o'clock" position.
    公开号:FR3031725A1
    申请号:FR1550489
    申请日:2015-01-21
    公开日:2016-07-22
    发明作者:Olivier Kerbler；Fabrice Henri Emile Metezeau；Patrick Gonidec；Loic Grall
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a turbojet engine nacelle, to a propulsion unit equipped with such a nacelle, and to an aircraft provided with such a propulsion unit. An aircraft is propelled by several turbojets each housed in a nacelle, each nacelle furthermore containing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped. Modern nacelles are intended to house a turbojet engine capable of generating through the blades of the rotating fan a flow of hot gases (also called primary flow) and a cold air flow (also called secondary flow) which circulates outside the turbojet engine through an annular passage, also called vein, formed between two concentric walls of the nacelle. The primary and secondary flows are ejected from the turbojet engine from the rear of the nacelle.
    [0002] A turbojet engine nacelle generally has a tubular structure comprising: a front section, or air intake, located in front of the turbojet engine; a median section intended to surround the fan of the turbojet engine; a rear section, intended to surround the combustion chamber of the turbojet, and generally embodying means of thrust reversal; an ejection nozzle, the outlet of which is situated downstream of the turbojet engine. The rear section generally has an external structure, which defines, with a concentric internal structure, called "lnner Fixed Structure" (IFS), the annular vein used to channel the flow of cold air. The thrust reversal means allow, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward a majority fraction of the thrust generated by the turbojet engine. In this phase, the inverter generally obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft. The means used to achieve this reorientation of the cold flow vary according to the type of inverter. A common configuration is that of thrust reversers known as "gate". In this type of thrust reverser, the outer cover of the rear section is sliding. The translation towards the rear of this sliding hood makes it possible to discover inversion grids placing in communication the cold flow vein and the outside of the nacelle. The translation of the sliding cover also makes it possible to deploy locking flaps in the cold flow vein. Thus, by the combined action of the locking flaps and the inversion grids, the cold flow is redirected towards the front of the nacelle. As mentioned above, the thrust reversal means are housed in the rear section of a nacelle. Three types of structural configuration are known for the rear section, namely the so-called "C" (or, in English, "C-duct"), "D" (or "Dduct") and "0" structures. "(Or" 0-duct "). In a nacelle structure D, the inner and outer structures of the rear section of the nacelle are secured to one another, through two islands of links called birfucations. The bifurcations are arranged respectively according to the positions known as "at twelve o'clock" (upper bifurcation) and "at six o'clock" (lower bifurcation). The sliding cowl is in this case mounted in translation on the outer structure of the rear section. The sliding cover is generally made of two half-parts. In a 0 or C-frame nacelle, the rear section is configured so that a bifurcation is not necessary. This represents a great gain in efficiency for the propulsion unit since the cold flow vein is no longer obstructed in its lower part, as is the case for the D structures. Moreover, the structures in 0 or in C also allow significant gains in terms of mass. In a 0 or C structure, the sliding cowl, or moving cowl, is generally mounted on rails disposed on either side of the pylon (or mast) for suspending the propulsion unit. These slides can be arranged directly on the pylon, or on a fixed intermediate element secured to the pylon when the propulsion unit is mounted. The hood is guided is supported only at these slides, so only near the "twelve o'clock" position. Alternatively, in a 0-shaped structure, the sliding cowl forms an integral structure. In order to respond to various constraints such as avoiding air re-intake by the engine, avoid directing a fraction of the thrust to the fuselage of the aircraft, etc., the profile of the grids ensuring the redirection of the cold flow n ' is generally not uniform along the circumference of the set of grids. It follows that the lateral forces related to the thrust reversal experienced by the grids are not uniformly distributed.
    [0003] The sum of these lateral forces is non-zero, which generates a lateral force applied to the set of grids and therefore to the propulsion unit. This lateral force generates a rocking movement of the propulsion unit. This nonuniform distribution also generates a nonuniform deformation of the inverter, which becomes ovalized during the thrust reversal phases. The invention proposes to solve the drawbacks of the state of the art by making it possible to limit the deformations and parasitic movements mentioned above. To this end, the invention relates to an aircraft turbojet engine nacelle, the nacelle having a rear section without a lower bifurcation, the rear section comprising a thrust reversal system, the thrust reverser system comprising a mobile cowl, the nacelle being characterized in that it comprises a guide system integral in translation of the movable cowl, said guide system cooperating with at least one fixed slider relative to the nacelle, the guide system and the slider being arranged near the "6 o'clock" position. Thus, by providing a guide system cooperating with a fixed slider, it ensures a recovery of lateral forces in the lower part of the nacelle, in the "six o'clock" position. The strains and parasitic movements generated in the "0-duct" or "C-duct" nacelles of the state of the art are thus strongly limited or even totally eliminated. In addition, the guide system according to the invention is simply integrated into the nacelle because the guide system is advantageously inserted in place of a solid gate, that normally positioned at six o'clock. Furthermore, it will advantageously realize a short type of guidance, thus allowing the lateral forces to be correctly recovered while limiting the risk of hyperstatism in guiding the movable cowl. In one embodiment, the slide is secured to a peripheral frame 35 intended to be fixed to the fan casing of a turbojet engine.
    [0004] In one embodiment, the slide is intended to be fixed directly to the fan casing. In one embodiment, the guide system comprises a guide rail.
    [0005] In one embodiment, the guide rail has two lateral rails. In one embodiment, the slide comprises at least two guide pads each cooperating with one of the two rails of the guide rail.
    [0006] In one embodiment, the thrust reversal system comprises inversion grids, in particular sliding inversion grids. In one embodiment, the inversion system comprises sliding inversion gates, a front end of the guide system being integral with a peripheral frame integral with the inversion gates.
    [0007] In one embodiment, a rear end of the guide system is integral with a peripheral frame of the movable cowl. In one embodiment, the guide system is extended by a beam secured to the movable cowl. The invention also relates to a propulsion unit for an aircraft, comprising a turbofan engine, the propulsion unit comprising a nacelle as defined above. The invention finally relates to an aircraft comprising at least one propulsion unit as defined above, the propulsion unit being supported by a pylon, the pylon having guide rails of the movable cowl of the nacelle. The present invention will be better understood on reading the detailed description which follows, made with reference to the appended drawings, among which: FIGS. 1a and 1b show a nacelle according to the invention, respectively in jet configuration direct "and" reverse jet "; FIGS. 2a and 2b show a portion of the rear section of the nacelle of FIGS. 1a and 1b, with the thrust reversal system respectively in the retracted and deployed position; Figures 3a and 3b are detail views respectively of Figures 2a and 2b; - Figure 3c is a view corresponding to Figure 3a, without the slide and the peripheral frame of which the slide is secured; - Figures 4a and 4b are isolated views of the guide system and the slider in two relative positions respectively corresponding to the retracted and deployed positions of the thrust reversal system; - Figures 5a and 5b show partial views of a nacelle rear section according to the invention and having an enlarged guide rail; - Figure 6 shows a partial view of a nacelle rear section according to the invention, showing the guide system and the slide seen from the side. Figures la and lb show a view of a nacelle 1 according to the invention. The latter conventionally comprises an air inlet 2, a median section 3, and a rear section 4. In FIG. 1a, the platform 1 is shown alone, whereas in FIG. see the nacelle 1 mounted on a pylon 5 (also known as "reactor mast"). Furthermore, Figure la shows the nacelle configuration "direct jet", that is to say with the reverse thrust system retracted position, while Figure 1b shows the nacelle configuration "reverse jet" , that is to say with the thrust reversal system in the deployed position. Thus it can be seen in Figure lb that a movable cover 20 of the rear section 4 is in the retracted position, revealing a set of reversing grids 22. In the example, the movement of the movable cowl 20 is supported and guided by rails 50 disposed on either side of the tower 5. In the example, the structure of the nacelle is of type "0" (or "0-duct") and therefore does not include a bifurcation in the part lower vein of cold flow. It should be noted that the invention is also applicable to a C-frame nacelle. Figures 2a and 2b show a portion of the rear section of the nacelle of Figures 1a and 1b, showing the elements of the inversion system. respectively in the retracted position and in the extended position. The thrust reverser system includes a movable, integral hood 20, which forms the outer surface of the rear section of the nacelle. The mobile cowl 20 is slidably mounted, in the example by means of the rails 50, integral with the pylon 5 supporting the propulsion unit (ie the assembly formed by a turbojet and the associated nacelle). The thrust reversal system further comprises reversing grids 22, in the example of sliding grids, and locking flaps 24 movable in rotation. The thrust reverser system comprises actuators (not shown), including electromechanical actuators, for sliding the movable cowl between its retracted position (Figure 2a) and its extended position (Figure 2b), and vice versa. When the thrust reversal system is retracted (Figure 2a): - the movable cowl 20 is in the retracted position, corresponding to an advanced position in which it provides aerodynamic continuity with the median section of the nacelle; - The locking flaps 24 are in the retracted position, in which position they are aligned with the inner surface of the movable cover 20; the inversion gates 22 are in the retracted (or advanced) position, in which position they are arranged around the fan casing of the turbojet engine. When the thrust reversal system is deployed (FIG. 2b): the movable cowl is in the extended position, corresponding to a retracted position, in which it discovers the reversing grids 22 which are in their retracted position; - The blocking flaps 24 are in the deployed position, in which position they at least partially obstruct the flow of cold flow; the inversion gates 22 are in the deployed (or retracted) position, in which position they are arranged behind the turbojet fan casing, and in which they redirect the cold flow towards the outside of the nacelle. It should be noted that, in the example of the sliding gates, the reversing gates 22 are linked in translation with the movable cowl 20, and the relative position of the gates 22 with respect to the mobile cowl 20 does not vary. when deploying or retracting the thrust reversal system. The reversing gates 22 are secured to a front peripheral frame 26. A plurality of housings 28 are provided for the actuators of the thrust reverser system. These housings 28, four in number in the example of FIGS. 2a and 2b, are arranged between some of the inverting grids 22. In the "six o'clock" position (or close to this position), at the normally occupied position by a solid grid (provided conventionally to avoid redirection of the cold flow downwards), a guide system 30 is arranged. In accordance with the invention, the guide system 30 is stationary relative to the movable hood 20 (and therefore , in the example, with respect to the inverting grids 22), being in the example integral with the front peripheral frame 26.
    [0008] The guide system 30 cooperates with a slider 32, movable relative to the moving cowl 20 and to the thrust reversal grids, and therefore with respect to the guide system 30. The slider 32 is, however, fixed with respect to the non-moving elements of the slider 32. the nacelle and the propulsion unit. In the example, the slide 32 is integral with a peripheral frame 34, which in example 15 is a part integral with the fan casing, known as the intermediate casing shell. Alternatively, the slider 32 may be attached directly to the fan housing. Thus, as can be seen in Figures 2a and 2b, the relative position of the slider 32 and the guide system 30 is related to the position of the movable cover 20 and thus the inverting grids 22. This relative position has two extreme, corresponding to the retracted and deployed positions of the thrust reversal system. These two extreme positions are better visible in FIGS. 3a (retracted thrust reverser) and 3b (thrust reverser deployed). FIGS. 4a and 4b are isolated views of the guide system 30 and the slide 32. The guide system 30 comprises a body 300 which has a front portion 302, designed to be fixed to the front peripheral frame 26, for example by splinting and a rear portion 304, intended to be fixed to the movable cowl 20, for example by riveting and / or splicing. In the example, the guiding system 30 is secured to a peripheral frame 202 (visible in FIG. 3c) of the movable cover 20. The guiding system 30 comprises a protruding portion, a guide rail 306. In the For example, the guide rail 306 has two side rails 308, 310. In the example of Figures 4a and 4b, the guide system 30 is a single piece. However, it may be preferred to make this element in two or more parts, for example the body 300 and the guide rail 306, in particular to allow to fix the rail 306 to the body 300 in an adjustable manner (especially in height). In addition, these two elements may be made of different materials, for example a composite material for the body 300 and a metallic material for the rail 306. The slide 32 comprises guide pads 320 (visible in FIG. 5a) cooperating with each of the side rails 308, 310. In the example, the slide 32 comprises four guide pads, arranged on either side of the rail 306, facing two by two. The guide pads are made of or coated with a material facilitating sliding, such as Teflon. The guide shoes 320 and can be rotatably mounted on the slider 32, or form slippery pads. Figure 5a shows an enlarged guide rail 306, thus increasing the rigidity of the guide system. Figure 6 shows the guide system and the slide 32 viewed from the side. In the example the guide length R provided by the rail 306 is 500 mm, while the longitudinal gap L between the support points of the guide pads is 80 mm. In order to ensure a satisfactory recovery of side forces while avoiding the risk of hyperstatism, it is advantageous to carry out a short guide. For this purpose, it will be ensured that the ratio between the longitudinal gap L between the bearing points of the pads and the guide length R 20 is less than 0.2. In a variant not shown, the guide rail may have at its rear portion, an extension extending in the form of a fixed beam of the movable cover 20. Thus, through this extension, the guide system will be securely attached to the movable hood 20 25 and participate in the rigidity thereof. Although the invention has been described in connection with a particular embodiment, it is obvious that it is not limited thereto and that it includes all the technical equivalents of the means described and their combinations. 30
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Aircraft turbojet engine nacelle, the nacelle (1) having a rear section (4) without a lower bifurcation, the rear section comprising a thrust reverser system, the thrust reverser system comprising a movable cover (20) , the nacelle being characterized in that it comprises a guide system (30) integral in translation of the movable cowl (20), said guide system (30) cooperating with at least one slider (32) fixed relative to the nacelle (1), the guide system (30) and the slider (32) being arranged near the so-called "6 o'clock" position.
    [0002]
    2. Nacelle according to claim 1, wherein the slide (32) is either secured to a peripheral frame (34) intended to be fixed to the fan housing of a turbojet, or intended to be fixed directly to the fan casing. 15
    [0003]
    The nacelle of claim 1 or 2, wherein the guide system (30) includes a guide rail (306).
    [0004]
    4. Nacelle according to the preceding claim, wherein the guide rail (306) comprises two rails (308, 310).
    [0005]
    5. Nacelle according to the preceding claim, wherein the slider (32) comprises at least two guide pads (320) each cooperating with one of the two rails (308, 310) of the guide rail (306).
    [0006]
    6. Nacelle according to one of the preceding claims, wherein the thrust reversal system comprises reversing grids, including sliding reversing grids (22). 25
    [0007]
    7. Nacelle according to one of the preceding claims, wherein the reversing grids (22) are sliding, a front end (302) of the guide system (30) being integral with a front peripheral frame (26) integral with reversing grids (22).
    [0008]
    8. Platform according to one of the preceding claims, wherein a rear end (304) of the guide system (30) is integral with a peripheral frame (202) of the movable cowl (20).
    [0009]
    9. Nacelle according to one of the preceding claims, wherein the guide system (30) is extended by a beam integral with the movable cowl (20).
    [0010]
    10. Aircraft propulsion unit comprising a turbofan engine, the propulsion unit comprising a nacelle (1) according to one of the preceding claims.
    [0011]
    11. Aircraft comprising at least one propulsion unit 5 according to the preceding claim, the propulsion unit being supported by a pylon (5), the pylon (5) having guide rails of the movable cowl of the nacelle.
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    同族专利:
    公开号 | 公开日
    US10590886B2|2020-03-17|
    CN107207096A|2017-09-26|
    EP3247632B1|2019-06-26|
    WO2016116709A1|2016-07-28|
    US20170327240A1|2017-11-16|
    FR3031725B1|2018-06-01|
    CN107207096B|2020-10-20|
    EP3247632A1|2017-11-29|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3280562A|1963-09-30|1966-10-25|Northwest Airlines Inc|Thrust reversing device for fan type jet engines|
    GB1147351A|1965-06-07|1969-04-02|Howard Nicholas Matthews|Improvements in thrust reverser for jet propulsion engine|
    US7484356B1|2005-07-26|2009-02-03|Aeronautical Concepts Of Exhaust, Llc|Cascade reverser without blocker doors|
    FR2999239A1|2012-12-12|2014-06-13|Aircelle Sa|PLATFORM PUSH INVERTER AND NACELLE EQUIPPED WITH AT LEAST ONE INVERTER|
    US3829020A|1973-06-13|1974-08-13|Boeing Co|Translating sleeve variable area nozzle and thrust reverser|
    GB0608985D0|2006-05-06|2006-06-14|Rolls Royce Plc|Aeroengine thrust reverser|FR3031726B1|2015-01-21|2017-02-24|Aircelle Sa|SYSTEM FOR THE INSTALLATION AND REMOVAL OF A PROPULSIVE ASSEMBLY ON A MAT OF AN AIRCRAFT|
    US10399687B2|2015-12-03|2019-09-03|The Boeing Company|Methods and apparatus to vary an air intake of aircraft engines|
    FR3047973B1|2016-02-23|2018-03-09|Airbus Operations|AIRCRAFT ENGINE ASSEMBLY, COMPRISING A MOTOR ATTACHING DEVICE EQUIPPED WITH STRUCTURAL MOBILE HOOKS CONNECTED TO THE CENTRAL CABIN|
    FR3059299B1|2016-11-30|2021-11-12|Safran Nacelles|AIRCRAFT TURBOREACTOR NACELLE, POWER UNIT AND AIRCRAFT CONTAINING SUCH A NACELLE|
    FR3074853B1|2017-12-13|2020-01-03|Safran Nacelles|PROPELLENT ASSEMBLY FOR AN AIRCRAFT HAVING A SIX HOUR ASSEMBLY BOX|
    FR3075760B1|2017-12-21|2020-01-31|Safran Nacelles|AIRCRAFT ENGINE PLATFORM|
    GB201806563D0|2018-04-23|2018-06-06|Rolls Royce Plc|Gas turbine engine keel beam|
    FR3108949A1|2020-04-02|2021-10-08|Safran Nacelles|Turbojet thrust reverser|
    法律状态:
    2015-12-30| PLFP| Fee payment|Year of fee payment: 2 |
    2016-07-22| PLSC| Publication of the preliminary search report|Effective date: 20160722 |
    2017-01-05| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-19| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550489|2015-01-21|
    FR1550489A|FR3031725B1|2015-01-21|2015-01-21|AIRCRAFT TURBO BOILER NACELLE|FR1550489A| FR3031725B1|2015-01-21|2015-01-21|AIRCRAFT TURBO BOILER NACELLE|
    EP16702579.0A| EP3247632B1|2015-01-21|2016-01-21|Aircraft turbojet engine nacelle|
    CN201680006473.XA| CN107207096B|2015-01-21|2016-01-21|Aircraft turbojet engine nacelle|
    PCT/FR2016/050119| WO2016116709A1|2015-01-21|2016-01-21|Aircraft turbojet engine nacelle|
    US15/655,276| US10590886B2|2015-01-21|2017-07-20|Aircraft turbojet engine nacelle|
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