• 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 a thrust reversing device with gates (21) for turbojet engine nacelle comprising: - a fixed structure (31), and - a movable structure (33) with respect to said fixed structure, comprising at least one door (23) pivotally mounted via pivots (39) between a retracted position corresponding to operation of the direct jet nacelle, and an extended position corresponding to an operation of the nacelle reverse jet. The thrust reverser device according to the invention is remarkable in that it comprises a device (41) for sampling a portion of a secondary air flow, adapted to withdraw a portion of the secondary air flow. from a circulation stream of the secondary air flow and for conveying said withdrawn air flow to at least one pivot (29) of the door.
    公开号:FR3019591A1
    申请号:FR1453106
    申请日:2014-04-08
    公开日:2015-10-09
    发明作者:Pierre Caruel；Docte Thiery Le
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a thrust reverser with doors, to a nacelle equipped with such thrust reverser, and to a propulsion assembly comprising such a nacelle. An aircraft is propelled by one or more propulsion units. Referring to Figure 1 illustrating an example of a propulsion assembly according to the prior art. A propulsion unit 1 comprises a turbojet engine 3 housed in a tubular boat. Each propulsion unit is attached to the aircraft by a mast, not shown, generally located under a wing or at the fuselage. A nacelle generally has a substantially tubular structure comprising an upstream section 7 defining an air inlet, a median section 9 intended to surround a fan of the turbojet engine, a downstream section 11 capable of housing a thrust reverser device 13, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine. The modern nacelles are intended to house a turbofan engine capable of generating via the gas generator a hot air flow F1, called primary flow, and through the blades of the rotating fan a flow of cold air F2, called secondary flow, which circulates outside the turbojet engine 3 through an annular channel defining a circulation vein of the secondary air stream 15.
    [0002] The vein 15 is delimited between an internal fairing 17 of the turbojet engine and an outer shell 19 housing the thrust reverser device. The two air flows F1 and F2 are ejected from the turbojet engine 3 from the rear of the nacelle. In the present application, upstream and downstream are defined with respect to the direction of flow of air in the propulsion unit in direct jet operation, the air inlet being situated upstream with respect to the nozzle ejection, located downstream of the nacelle. The role of a thrust reverser during the landing of an aircraft is to improve the braking capacity of an aircraft by redirecting forward at least a portion of the thrust generated by the turbojet engine. In this phase, the inverter obstructs the gas ejection nozzle and directs the ejection flow of the engine towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the engine. the plane. The means implemented to achieve this reorientation of the flow vary according to the type of inverter. However, in all cases, the structure of an inverter 35 comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a retraction position in which they close this passage. These mobile hoods may furthermore perform a deflection function or simply the activation of other deflection means. In the grid inverters, for example, the movable hoods slide along rails so that when backing up during the opening phase, they discover deflection vane grids arranged in the thickness of the nacelle . A linkage system connects the movable hood to blocking doors that expand within the ejection channel and block the output in direct flow. In the door-thrust reversing devices, such as that which equips the platform shown in FIG. 1, each movable cowl pivots so as to block the flow and deflect it and is therefore active in this reorientation. More specifically, a door-thrust reverser device 21 comprises several doors 23 pivotally mounted so as to be able, under the action of drive means, to switch between a retracted position corresponding to an operation of the direct jet nacelle. the position in which the doors 23 provide, with a fixed structure 31 of the thrust reverser device, an aerodynamic continuity of the nacelle, as shown in FIG. 2, and an extended position causing the nacelle to operate in a reverse jet, 3, the position in which the doors 23 have pivoted so that a downstream part 25 of each door at least partially obstructs the circulation duct 15 of the secondary air flow F 2, and upstream portion 27 opens in the downstream section 11 of the nacelle a passage 31 allowing the air flows F1 and F2 to be partially ejected from the nacelle, then redirected upstream of the nacelle by the doors 23 deployed. When a door is in the retracted position, corresponding to all phases of flight except that of landing, the door is in contact with the flow of cold air passing through the secondary air stream. from its retracted position towards its deployed position, a part of the hot primary air flow passing through the turbojet engine comes into contact with the door, the door then undergoes a rise in temperature, in particular at the level of the pivots of the door and of the zones. This elevation of the temperature substantially weakens the rigidity of the nacelle at these zones 35 In order to avoid such a weakening of the structure, the parts which make up the zones which surround the door pivots , and the door pivots themselves, are generally oversized, which greatly increases the mass of the nacelle.In addition, these parts are generally made of materials capable of withstanding such high temperatures, such as thermosetting resins of polybismaleimide type, or even aluminum 2219, very expensive materials. The present invention aims to reduce the mass of thrust reversers doors, and their manufacturing cost. For this, the present invention relates to a door thrust reversal device for an aircraft turbojet engine nacelle comprising: a fixed structure, and a structure movable relative to said fixed structure, comprising at least one door pivotally mounted via pivots between a retracted position corresponding to a direct jet nacelle operation, and an extended position corresponding to a reverse jet nacelle operation, characterized in that it comprises a sampling device a portion of a secondary air flow, adapted to take, when the inverter is being deployed, a part of the secondary air flow from a secondary circulation flow stream and to convey said air flow taken to at least one pivot 20 of the door. Thus, by providing such a device for sampling a portion of the secondary air flow, adapted to withdraw a portion of the cold air flow circulating in the secondary vein of the nacelle, then to convey the air taken to a pivot From the door, the door pivots are permanently cooled, regardless of the position of the door, retracted or deployed. This advantageously eliminates the need to make the pivots of the door and the neighboring areas of these pivots in particularly heavy and expensive materials, which reduces both the weight of the nacelle and the cost of manufacture thrust reversing devices with doors. According to all the optional features of the invention: the fixed structure comprises an outer wall and an inner wall in contact with the circulation stream of the secondary air flow and said inner wall comprises at least one ventilation day allowing communication. between the circulation duct of the secondary air flow and a space for conveying the withdrawn secondary air flow defined between said inner and outer walls; - The device for sampling a portion of the secondary air flow comprises at least one ventilation valve movable alternately between a closed position in which it covers the ventilation day and an open position in which it discovers at least partially the ventilation day; - The ventilation valve is pivotally mounted on an axis substantially parallel to an axis transverse to a longitudinal axis of the thrust reverser device; - The device for sampling a portion of the secondary air flow comprises means adapted to maintain the ventilation valve in its closed position when the door is in the retracted position, and to allow the passage of said ventilation flap in its position. opening when said door is in the deployed position; said means adapted to hold the ventilation flap in its closed position when the door is in the retracted position, and to allow the passage of said ventilation flap in its open position when said door is in the deployed position, comprise at least one ramp integral with the ventilation valve, cooperating with said door when said door is in the retracted position and being shaped to allow the passage of the ventilation valve from its closed position to its open position when the door passes from its retracted position to its deployed position; - The door comprises a locking / unlocking device comprising at least one locking hook integral with said door, adapted to cooperate with a hook secured to the fixed structure of said thrust reverser device for a retracted position of said door, and the locking hook comprises an extension finger supported by the ramp of the device for withdrawing part of the secondary air flow when the door is in the retracted position; the ventilation valve comprises resilient means adapted to permanently return said valve to its open position, which makes it possible for the valve to open easily during maintenance operations, by a simple operation of opening the door of the door; the inverter; - The fixed structure of the thrust reverser device comprises at least one air outlet in the vicinity of the shaped door pivots for discharging at least a portion of the withdrawn secondary air flow.
    [0003] The present invention also relates to a nacelle for aircraft turbojet remarkable in that it comprises at least one thrust reverser device with doors according to the invention. Finally, the present invention relates to a propulsion unit for an aircraft comprising a turbojet engine housed in a nacelle according to the invention, remarkable in that the device for sampling a portion of the secondary air flow is positioned upstream of a plane of ejection of the primary air flow of the turbojet.
    [0004] Other features, objects and advantages of the present invention will appear on reading the following description and on examining the appended figures, in which: FIG. 1 illustrates a propulsion assembly comprising a platform equipped with a thrust reverser device with doors according to the prior art; FIG. 2 represents in isometric view the thrust reversing device of FIG. 1, represented in the direct jet operating position; FIG. 3 is a view similar to that of FIG. 2, in which the thrust reverser device is shown in the reverse jet operating position; FIG. 4 is an isometric view of the thrust reverser device according to the invention, represented in the direct jet operating position; - Figure 5 shows the device for sampling a portion of the secondary air flow according to the invention; - Figures 6 and 7 show the kinematics of unlocking the doors of the thrust reverser device; FIG. 8 illustrates the routing of the flow of air taken from the secondary vein; - Figure 9 shows the thrust reverser device in the reverse jet operating position.
    [0005] Note that in the description and in the claims, the terms "upstream" and "downstream" must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet engine. , that is from left to right with reference to FIGS. 1 to 9.
    [0006] Similarly, the terms "internal" and "external" will be used in a nonlimiting manner with reference to the radial distance from the longitudinal axis of the nacelle, the expression "internal" defining a zone radially closer to the nacelle. longitudinal axis of the nacelle, as opposed to the term "external". Moreover, in the description and the claims, to clarify the description and the claims, the longitudinal, vertical and transverse terminology will be adopted in a nonlimiting manner with reference to the direct trihedron L, V, T indicated in the figures, whose longitudinal axis L is parallel to the longitudinal axis 51 of the nacelle shown in FIG. 4. In addition, throughout the figures, identical or similar references represent identical or similar members or assemblies of members. Referring to Figure 4, showing the thrust reversal device with doors 21 according to the invention in the direct jet operating position. The door-thrust reversal device, hereinafter referred to as "the inverter", comprises a fixed structure 31 and a movable structure 33 with respect to said fixed structure. The fixed structure 31 is constituted by a beam of the inverter, comprising an inner wall 35 in contact with the circulation duct 15 of the secondary air flow (visible in FIG. 1), and an outer wall 37 (concealed from the 4, visible in FIG. 2) separated from the inner wall by a space 38. The mobile structure 33 comprises several doors 23, for example two, pivotally mounted via pivots 39 between a retracted position according to FIG. which they provide, with the fixed structure 31 of the inverter, an aerodynamic continuity external of the nacelle, corresponding to an operation 25 of the nacelle direct jet, position shown in Figure 4, and an extended position that it creates a passage in the nacelle, corresponding to an operation of the nacelle reverse jet, position shown in Figure 9. In known manner, the holding of the doors in the retracted position is achieved through diary of a hook 32 S-shaped (visible in Figure 5) mounted on the fixed structure 30 of the inverter 31, cooperating at each of its ends with a latch hook 34 integral with each of the doors. The hook 32 is pivotally mounted, by means of actuating means, so that the pivoting of the hook 32 releases the locking hooks 34 of the doors, thus allowing the doors to pass from a retracted position to an extended position. As represented in FIG. 1, in the direct jet operating position, the cold air flow F 2, generated by means of the blades of the rotating fan of the double-flow turbojet engine housed in the nacelle, circulates in the annular channel. defining the circulation duct 15 of the secondary air stream and is ejected by the downstream of the nacelle. According to the invention, the inverter comprises a device 41 for sampling a portion of the secondary air flow, adapted to withdraw a portion of the secondary air flow from a circulation stream of the secondary air flow and to convey said flow of air taken to at least one pivot of the door. The thrust reverser device is capable of equipping a nacelle supporting a turbojet engine, and the device for sampling a portion of the secondary air stream is positioned upstream of a jet ejection plane. primary air of the turbojet engine, which allows to take only cold air, not mixed with the hot primary air stream from the turbojet engine. Referring to Figure 5, illustrating an enlargement of the zone V of Figure 4.
    [0007] According to the invention, the inner wall 35 comprises, for each of the beams of the fixed structure of the inverter, at least one ventilation day 43 forming communication between the circulation vein of the secondary air flow and the space 38 routing of the secondary air stream taken. The ventilation day 43 is capable of being closed by a ventilation valve 45 pivotally mounted via a hinge 47 on an axis 49 substantially parallel to an axis transverse to a longitudinal axis 51 of the inverter, shown in Figure 4. The locking hook 34 of the door is secured to a finger 52 forming an extension of the locking hook. The finger 52 is supported, when the door is in the retracted position shown in Figure 5, by a ramp 55 secured to the outer wall 53 of the ventilation valve 45. The operation of the device 41 for taking a portion of the flow of secondary air will now be described. When the door is in the retracted position, the position shown in FIG. 5, the ramp 55, integral with the ventilation valve 45, cooperates with the door of the inverter by means of the finger 52, keeping the ventilation flap 45 in position. a closing position in which it closes the ventilation day 43. At this stage, the secondary air flow circulating in the secondary vein 35 passes through the vein and is ejected conventionally downstream of the nacelle.
    [0008] When the operation of the nacelle in reverse jet is controlled, the hook S-shaped 32 pivots about an axis parallel to a substantially vertical axis of the inverter, which releases the locking hook 34 of the door, as shown in Figures 6 to 8 referred to now.
    [0009] When the hook S-shaped 32 pivots according to the arrow F3 shown in Figure 6, the locking hook 34 secured to the door is unlocked, which causes the passage of the door from its retracted position to its deployed position, according to the F4 arrow shown in Figure 7. When the door moves to its extended position, the finger 52 10 secured to the hook 34 moves along the ramp 55, then releasing the ventilation valve 45. The ventilation flap, in contact permanent with the secondary air flow flowing in the secondary vein, rotates about the axis 49 of the hinge 47, towards the space 38 contained between the inner and outer walls 15 of the fixed structure of the inverter under the effect of the pressure generated by the secondary air flow. The ventilation valve 45 then moves from its closed position to its open position, thereby uncovering the ventilation day 43. Alternatively, resilient means such as a torsion spring 20 can be mounted on the pivot axis of the ventilation valve so as to permanently reminder the valve in its open position, which allows easy opening of the valve during maintenance operations, by a simple operation of opening the door of the inverter. When the ventilation flap is in its open position, the secondary air stream flowing in the secondary duct then passes through the ventilation day 43, as represented by the arrow F5 shown in FIG. air taken from the secondary vein is then conveyed along the inner wall 35 along the arrow F6 of Figure 9, to the pivots 39 of the doors 23, to refresh the pivots 29 and the areas 29 adjacent the pivots.
    [0010] The zones 29 adjacent the pivots comprise air outlets 57 shaped to evacuate at least part of the secondary air flow taken, according to the arrows F7. Thus, by virtue of the present invention, the mass of the nacelle and the cost of manufacture of the door thrust reverser are considerably reduced in that it is no longer necessary to provide door pivots in materials capable of to withstand the high temperatures generated by the primary air flow from the turbojet engine. It goes without saying that the invention is not limited to the embodiments of the thrust device, the nacelle and the propulsion unit, described above solely as illustrative examples, but on the contrary it embraces all variants involving the technical equivalents of the means described and their combinations if they fall within the scope of the invention.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A thrust reversing device with doors (21) for an aircraft turbojet engine nacelle comprising: - a fixed structure (31), and - a movable structure (33) with respect to said fixed structure, comprising at least one door (23). ) pivotally mounted by means of pivots (39) between a retracted position corresponding to an operation of the direct jet nacelle, and an extended position corresponding to an operation of the nacelle in reverse jet, said thrust reverser device being characterized in that it comprises a device (41) for sampling a portion of a secondary air flow, adapted to withdraw a portion of the secondary air stream from a stream (15) of circulation of the flow of secondary air and for conveying said withdrawn air flow to at least one pivot (29) of the door.
    [0002]
    2. thrust reverser device according to claim 1, wherein the fixed structure (31) comprises an outer wall (37) and an inner wall (35) in contact with the vein (15) for circulation of the air flow. secondary, characterized in that said inner wall (35) comprises at least one ventilation day (43) allowing a communication between the vein (15) circulation of the secondary air flow and a space (38) for routing the flow withdrawn secondary air, defined between said inner and outer walls.
    [0003]
    3. Thrust reversal device according to claim 2, characterized in that the device (41) for sampling a portion of the secondary air flow comprises at least one ventilation valve (45) movable alternately between a position of closure that covers the ventilation day (43) and an open position that it discovers at least partially the ventilation day (43).
    [0004]
    4. A thrust reverser device according to claim 3, characterized in that the ventilation valve (45) is pivotally mounted on an axis (49) substantially parallel to an axis transverse to a longitudinal axis (51) of the device 35. thrust reversal.
    [0005]
    5. Thrust reversal device according to one of claims 3 or 4, characterized in that the device (41) for sampling a portion of the secondary air flow comprises means adapted to maintain the ventilation flap ( 45) in its closed position when the door (23) is in the retracted position, and to allow the passage of said valve in its open position when said door is in the extended position.
    [0006]
    6. thrust reverser device according to claim 5, characterized in that said means adapted to maintain the ventilation valve (45) in its closed position when the door (23) is in the retracted position, and to allow the passage said valve in its open position when said door is in the deployed position, comprise at least one ramp (55) integral with said ventilation valve (45), cooperating with said door (23) when said door is in the retracted position and being shaped to allow the passage of said ventilation valve from its closed position to its open position when the door passes from its retracted position to its deployed position.
    [0007]
    7. A thrust reverser device according to claim 6, wherein the door (23) comprises a locking / unlocking device comprising at least one locking hook (34) integral with said door, adapted to cooperate with a hook (32). ) secured to the fixed structure (31) of said thrust reverser device for a retracted position of said door, characterized in that the locking hook (34) comprises an extension finger (52) supported by the ramp (55) the device (41) for withdrawing part of the secondary air flow when the door is in the retracted position.
    [0008]
    8. thrust reversal device according to any one of claims 3 to 7, characterized in that the ventilation valve (45) comprises resilient means adapted to constantly return said valve in its open position.
    [0009]
    Thrust reversal device according to one of Claims 1 to 8, characterized in that the fixed structure (31) of the thrust reverser device comprises at least one air outlet (57) close to the Pivots 35 (39) shaped door for discharging at least a portion of the secondary air stream taken.
    [0010]
    10. Nacelle for aircraft turbojet characterized in that it comprises at least one thrust reverser device (21) according to any one of claims 1 to 9.
    [0011]
    11. Propulsion unit for an aircraft comprising a turbojet engine housed in a nacelle according to claim 10, characterized in that the device (41) for sampling a portion of the secondary air flow is positioned upstream of an ejection plane. the primary air flow of the turbojet engine.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3129631B1|2017-09-20|Door-type thrust reverser device for aircraft turbojet engine nacelle
    EP2635788B1|2014-07-02|Thrust reverser device without a control rod in the stream
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    WO2008135644A1|2008-11-13|Thrust reverser for a jet engine
    CA2696393C|2015-06-09|Jet engine nacelle equipped with a system for mechanically inhibiting a thrust reverser
    FR2978990A1|2013-02-15|PUSH REVERSING DEVICE
    CA2792288A1|2011-10-13|Aircraft propulsion system provided with reverse thrust means
    WO2010012878A1|2010-02-04|Thrust reverser device
    EP3149318B1|2018-08-22|Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors
    FR3067406B1|2019-07-12|THRUST INVERTER SYSTEM HAVING LIMITED AERODYNAMIC DISTURBANCES
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    FR2966882A1|2012-05-04|THRUST INVERTER FOR AIRCRAFT TURBOJET ENGINE WITH REDUCED ACTUATOR NUMBERS
    EP3039274A1|2016-07-06|Nacelle comprising a thrust reverser device with maintained mobile grids
    FR2927956A1|2009-08-28|THRUST INVERTER FOR DOUBLE FLOW TURBOREACTOR NACELLE
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    EP3724481A1|2020-10-21|Propulsion unit for aircraft comprising an assembly box-type structure in the six o'clock position
    FR3018863A1|2015-09-25|NON-GRILLED PUSH REVERSING DEVICE FOR AIRCRAFT TURBO BOREHOLE
    CA2887470A1|2014-05-15|Turbojet engine nacelle comprising a unit assembly capable of moving along a guide assembly
    FR3076865A1|2019-07-19|REAR ASSEMBLY OF AN AIRCRAFT TURBOJET AIRCRAFT COMPRISING A SLIDING GRID INVERTER WITH SLIDING GRIDS
    同族专利:
    公开号 | 公开日
    FR3019591B1|2020-07-17|
    WO2015155432A1|2015-10-15|
    EP3129631A1|2017-02-15|
    EP3129631B1|2017-09-20|
    CA2942461A1|2015-10-15|
    US10605196B2|2020-03-31|
    US20170022934A1|2017-01-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2319771A1|1975-07-28|1977-02-25|Gen Electric|ORIENTABLE THRUST EJECTION TUBE COOLING SYSTEM|
    FR2568315A1|1984-07-24|1986-01-31|Hurel Dubois Avions|THRUST INVERTER WITH DOORS FOR REACTION ENGINE|
    EP0632196A1|1993-06-23|1995-01-04|Hispano-Suiza|Jet engine thrust reverser with aerodynamic cooling|
    EP1327767A1|2002-01-10|2003-07-16|Hurel-Hispano|Cooling device for a common nozzle of a turbofan engine|FR3097596A1|2019-06-21|2020-12-25|Safran Nacelles|Thrust reverser grille including longitudinal cooling channels|US3920203A|1974-12-23|1975-11-18|Boeing Co|Thrust control apparatus for obtaining maximum thrust reversal in minimum time upon landing of an aircraft|
    US6260801B1|1999-09-17|2001-07-17|The Nordam Group, Inc.|Swing pivot thrust reverser|
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    US7946104B2|2006-05-12|2011-05-24|Rohr, Inc.|Bleed air relief system for engines|FR3063522B1|2017-03-06|2021-05-07|Safran Nacelles|ACTUATION DEVICE FOR A THRUST INVERTER WITH ANTI-DEPLOYMENT BODY|
    GB201707690D0|2017-05-12|2017-06-28|Safran Nacelles|Methods of coating a workpiece|
    US11149688B2|2018-10-05|2021-10-19|The Boeing Company|Blocker door pressure relief systems and methods|
    FR3107092A1|2020-02-11|2021-08-13|Safran Aircraft Engines|PROCESS AND CONTROL SYSTEM OF AN AIRCRAFT THRUST SHUTTLE|
    法律状态:
    2016-03-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-03-31| 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 |
    2018-04-27| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453106|2014-04-08|
    FR1453106A|FR3019591B1|2014-04-08|2014-04-08|DOOR INVERTER DEVICE FOR AIRCRAFT TURBOREACTOR NACELLE|FR1453106A| FR3019591B1|2014-04-08|2014-04-08|DOOR INVERTER DEVICE FOR AIRCRAFT TURBOREACTOR NACELLE|
    PCT/FR2015/050733| WO2015155432A1|2014-04-08|2015-03-24|Door-type thrust reverser device for aircraft turbojet engine nacelle|
    CA2942461A| CA2942461A1|2014-04-08|2015-03-24|Door-type thrust reverser device for aircraft turbojet engine nacelle|
    EP15719262.6A| EP3129631B1|2014-04-08|2015-03-24|Door-type thrust reverser device for aircraft turbojet engine nacelle|
    US15/286,955| US10605196B2|2014-04-08|2016-10-06|Door-type thrust reverser device for aircraft turbojet engine nacelle|
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