Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/56—Reversing jet main flow
  • F02K1/566—Reversing jet main flow by blocking the rearward discharge by means of a translatable member
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/56—Reversing jet main flow
  • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/56—Reversing jet main flow
  • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/56—Reversing jet main flow
  • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
  • F02K1/605—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers the aft end of the engine cowling being movable to uncover openings for the reversed flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/76—Control or regulation of thrust reversers
  • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/50—Kinematic linkage, i.e. transmission of position
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/50—Kinematic linkage, i.e. transmission of position
  • F05D2260/52—Kinematic linkage, i.e. transmission of position involving springs
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to a door for thrust reverser doors and such a thrust reverser and a nacelle equipped with such a thrust reverser.
• 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.
• 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.
• the structure of an inverter comprises movable covers moved 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 retracted position in which they close. this passage.
• These mobile hoods may furthermore perform a deflection function or simply the activation of other deflection means.
• 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.
• a door-thrust reversal device comprises one or more doors pivotally mounted so as to be able, under the action of drive means, to switch between an inactive position called closure during operation of the so-called turbojet engine.
• the doors constitute a part of the downstream section, and an inverting position or opening position in which they swing in such a way that a downstream part of each door comes to obstruct at least partially the duct of the nacelle and an upstream portion opens in the downstream section a passage allowing the flow of air to be channeled radially relative to a longitudinal axis of the nacelle.
• the pivot angle of the doors is adjusted so as to greatly reduce or eliminate the thrust force generated by the flow escaping in direct jet and up to possibly generate a counter-thrust by generating a component of the deflected flow upstream of the nacelle.
• the doors In order to be able to improve the reorientation of the air flow in a direction tending as close as possible to a longitudinal direction of the nacelle, the doors have been equipped with deflection means, generally constituted by terminal spoilers, also called deflectors, forming upstream of the door a return substantially perpendicular to the latter.
• deflection means generally constituted by terminal spoilers, also called deflectors, forming upstream of the door a return substantially perpendicular to the latter.
• the spoiler when the door is in the reverse thrust position, the spoiler is oriented in a substantially longitudinal direction of the nacelle and forces the flow of air in this direction.
• each spoiler Conversely, when the door is in the closed position, each spoiler is oriented in a direction substantially perpendicular to the longitudinal axis of the nacelle. Each spoiler then enters the flow of the flow of air stream and may then block the flow of air flowing in the nacelle direct jet, which is not permissible.
• the doors have been designed to have an upstream cavity at an inner surface of said door. Therefore, the door has upstream a reduced thickness which allows both the spoiler to project from said door and not to have a length greater than the thickness of the nacelle upstream of the door so as not to enter the flow vein of the airflow when the door is in the closed position.
• a general inverter gate structure is shown in FIGS. 1 and 2 in respectively closed and open positions. It should be noted, however, that such a cavity is a major aerodynamic accident inside the air flow duct when the door is in the closed position, which reduces the overall performance of the turbojet engine.
• a drawback related to this achievement lies in the reliability of the actuating system of the door spoiler, not proving sufficiently strong compared to the forces developed by the spoiler when it opens.
• the deflection means are subjected to significant forces that can lead to tearing of the deflection means when the latter are in the deployed position, that is to say for a door open position.
• the present invention aims at improving the direct jet and reverse jet performance of the thrust reverser with doors, by proposing a door for thrust reverser with doors, whose deflection means do not deform under load and do not vibrate. when using the low frequency turbojet engine, and whose actuating systems such spoilers are strong enough to withstand the forces generated by the spoilers when they open.
• the present invention proposes a door for thrust reverser with doors capable of being pivotally mounted on a fixed structure of a thrust reverser comprising:
• air deflection means arranged at an upstream end of the door and movably mounted, in rotation about an axis substantially perpendicular to a front frame of the door, between a retracted position corresponding to a position closing the door and an extended position in which the deflection means protrude from the door corresponding to an open position of the door, means for actuating said deflection means from one to the other of their retracted and deployed positions,
• said gate being remarkable in that said actuating means comprise:
• said resilient means being adapted to open the angle formed by said second and third connecting rods.
• the actuating means according to the invention are shaped to withstand the forces suffered by the deflection means when they open and allow said deflection means to be maintained in a position in which they ensure optimum reorientation of the flow passing through the vein and blocked. through the door.
• the actuating means according to the invention comprise a set of three connecting rods connected to elastic means, which constitutes a relatively easy system to assemble and limited in number of parts necessary for the deployment and retraction of the deflection means , which makes it possible to reduce the mass of the assembly constituted by the deflection means and by its actuating means.
• the deflection means have at least one surface forming an extension of the inner surface of the door when said door is in the open position.
• the elastic means are contained integrally inside the deflection means when the door is in the closed position.
• the elastic means comprise a tension or compression spring.
• the first bielle is a dte to abut an internal centering of the compression spring.
• the door comprises secondary retaining means comprising at least one abutment integral with the deflection means and shaped to engage in at least one support integral with the front door frame.
• the axis of rotation of the deflection means is located near a lateral end of the door.
• the invention also relates to a thrust reverser with doors comprising at least one door and a fixed structure on which said door is pivotally mounted between a first position, said closure, in which it closes the inverter and is a part of a outer cowling, the deflection means of the flow being in the retracted position, and a second position, called the open position, in which it releases a passage in the fixed structure and is able to at least partially block a flow of air generated by a turbojet, the deflection means being in the deployed position.
• said thrust reverser with doors comprises primary retaining means comprising at least one upper stop secured to the deflection means and shaped to engage in at least one support stop member secured to the front door frame, and at least one bottom stop shaped to engage in at least one stop support integral with the fixed part of the inverter.
• the retaining means allow the locking of the spoiler during its rotational movement about its axis of rotation, corresponding to the passage from a closed position to an open position of the door.
• the thrust reverser comprises guiding means comprising, on the one hand, a roller secured to the deflection means and able to move along a ramp integral with the fixed structure of the thrust reverser and, secondly, a guide secured to the deflection means and able to move along a profile of the support integral with the front door frame.
• the invention also relates to a turbojet engine nacelle, said nacelle being remarkable in that it is equipped with at least one thrust reverser system according to the invention.
• FIG. 1 is a sectional view of a thrust reverser doors according to the prior art, the door is in the closed position;
• FIG. 2 is a view similar to that of Figure 1, the door being in the open position;
• FIG. 3 schematically shows a spoiler according to the prior art
• FIG. 4 shows a first embodiment of a door provided with the deflection means according to the invention, said means being in the retracted position;
• FIG. 5 illustrates illustrates the deflection means in the deployed position
• FIG. 6 illustrates, in the manner of FIG. 4, a second embodiment of the door according to the invention
• FIG. 7 is a sectional view of the compression spring of the actuating means
• FIG. 10 represents the guiding of the deflection means on the fixed part of the inverter
• FIG. 1 1 illustrates the lower stop of the deflection means penetrating into a stop support of the fixed structure of the inverter
• FIG. 12 is an isometric view of the deflection means; - Figure 13 illustrates the curved surface of the deflection means in the deployed position.
• upstream and downstream are defined by reference to the flow direction of the air flow in the nacelle in direct jet operation, the upstream of the nacelle corresponding to a part of the nacelle by which the flow enters, and the downstream corresponding to an ejection zone of said air flow.
• FIG. 1 illustrates a known example of embodiment of a thrust reverser with doors equipped with a deflection spoiler.
• a thrust reverser of this type comprises three main parts, namely a fixed part 1, situated upstream in the extension of an outer wall of an airflow duct of the turbojet, a movable part 2, and a ferrule rear 3, fixed.
• the fixed part 1 comprises an outer panel 4 of nacelle and an inner panel 5 constituting an outer panel of a vein 6 for circulating the air flow.
• the outer panel 4 and inner 5 of the fixed part 1 are connected by a front frame 7 which also supports the control means of the movable part 2, constituted in this case by a jack 8.
• the movable part 2 is decomposed in one or more displaced elements commonly called doors 9.
• Each door 9 is pivotally mounted so as to be able, under the action of the control means 8, to swing between a position in which it ensures the structural continuity between the fixed part 1 and the rear part 3 as well as the inside of the vein 6 and an open position in which it releases a passage between the fixed portion 1 and the rear portion 3 allowing an escape of the air flow through said opening.
• the door 9 comprises, on the one hand, an outer panel 10 coming, in a direct jet, to be placed in the extension of the outer panel 4 of the fixed part and to ensure external aerodynamic continuity with a panel 5, and on the other hand, an inner panel 1 1 and a front frame 12 of the door 9, constituting an upstream end of the door, relying on the outer panel 1 0 and the inner panel 1 1.
• the front frame 1 2 is extended by means of deflection 13 intended, when the door 9 is open, to reorient a part of the air flow towards the front of the nacelle thereby generating a counter-thrust.
• the deflection means are, according to the prior art, fixed or movable.
• the deflection means 13 are movable in rotation around an axis of rotation 1 7 sensibly. perpendicular to the front frame 1 2 of door 9, and located near a lateral end of the door.
• the deflection means 13 are in an extended position and project from the door 9, a position corresponding to an open position of the door for operation of the nacelle in reverse jet.
• the deflection means 13 are replaced by the deflection means 16. It may be for example spoilers or flaps, the geometry is further specified below.
• FIG. 4 illustrates the door 9 according to the invention in a so-called closing position, in which position the nacelle operates in a direct jet and the deflection means are retracted.
• the deflection means do not enter the circulation channel 6 when the door is closed, which allows not to disturb the flow of air flow.
• the door 9 is able to be opened by the activation of the control means 8.
• These control means may be constituted for example by a cylinder whose end is connected to the fixed structure of the inverter.
• the activation of the control means of the door causes the opening of the door 9, and moreover the deployment of the deflection means 16.
• the deflection means 16 are adapted to be mounted beyond the window of the window 9 to the actuating means 21 comprising a set of connecting rods. 23 and elastic means 25.
• the elastic means 25 consist of a tension spring 27.
• the traction spring 27 is contained integrally inside the spoiler 16 when the latter is in the retracted position, so as not to encumber the thrust reverser.
• the spring 27 is connected by one of its ends to the set of rods 23 and the other of its ends to an axis 28 integral with the spoiler 16.
• the lateral ends of the spring 27 adopt a substantially loops shape penetrating into the orifices of the assembly of connecting rods 23 and the axis 28. These loops prevent the spring from escaping in case of vibrations.
• the set of connecting rods 23 comprises a first connecting rod 29, a second connecting rod 31 and a third connecting rod 33 being made integral at one of their ends by an axis 35.
• Said connecting rods are movable in rotation about said axis 35, axis of concurrence rods, substantially parallel to the axis of rotation 17 of the spoiler 1 6. Led it axis of rotation 1 7 is located near a lateral end of the door 9, but can quite be located near the median axis 18 of the door 9.
• the angle formed between the second connecting rod and the first connecting rod, and the angle formed between the third connecting rod and the first connecting rod, are relatively small, more specifically generally less than 45 °.
• the first connecting rod 29 is connected at one of its ends to the two other links 31 and 33 and at the other end to the tension spring 27, connected to the spoiler 16 via the axis 28.
• the second connecting rod 31 is connected at one of its ends to the two other links 29 and 33 and at the other of its ends to the front frame 12 of the door 9.
• the connection between said second connecting rod and said front frame 12 is made by the intermediate support 37 secured to the front door frame.
• Said second connecting rod 31 is rotatable about an axis 38 of the support 37, said axis being substantially parallel to the axis of rotation 17 of the spoiler 16.
• the third connecting rod 33 is connected at one of its ends to the two other rods 29 and 31 and at the other end to the movable spoiler 16.
• the connection between said third rod and said movable spoiler 1 6 is made via a support 39 secured to the movable spoiler.
• Said third connecting rod 33 is rotatable about an axis 40 of the support 39, said axis being substantially parallel to the axis of rotation 17 of the spoiler 16.
• the activation of the control means 8 of the door 9 allows the pivoting of said door and the opening thereof.
• the deflection means 16 are no longer supported on the fixed surface of the inverter, and the elastic means, connected to the second connecting rod 29, tend to attract it. , thereby causing a displacement of the axis of concurrence 35 of the rods in a direction such that the angle between the rod 31 and the connecting rod 29, and the angle between the connecting rod 33 and the connecting rod 29, are substantially increased relative to said angles formed when the door was in a closed position, which allows deployment of the deflection means, and then holding in this extended position when the door is fully open.
• angles are generally greater than or equal to 70 ° when the door is in the open position.
• the deflection means 1 6 then project from the door 9, which improves the orientation of the air flow upstream of the nacelle.
• actuating means ensure a good retention deflection means when they are subjected to significant effort, due to the air flow redirected by the door when it opens.
• the deflection means come to rest on the fixed surface of the thrust reverser protruding, which will rotate the deflection means 1 6 in a position where they are retracted.
• the deflection means 16 do not enter the vein 6, and therefore do not interfere, therefore, the flow of air in said vein when the door is in the closed position.
• This embodiment is identical to the first embodiment, except that the elastic means 25 are constituted by a compression spring mounted in a tube 41 and not by a tension spring.
• FIG. 6 illustrates the deflection means 16 in the retracted position, corresponding to a closed position of the door 9, for which the actuating means consist of a compression spring mounted in a tube 41, and by the connecting rods 29, 31, 33.
• the compression spring 43 is wound around an inner tube 45 integral at one of its ends with the set of connecting rods. Led it compression spring and said inner tube are then mounted in the outer tube 41 integral at one of its ends of the axis 28 integral with the spoiler.
• the outer tube 41 comprises inside a wall 47 secured to the inner tube 45 on which the spring 43 is supported during the opening of the door, which will achieve the traction function of the axis of competition 35 of the connecting rods, so as to allow the increase of the angles between the second and first connecting rods, and between the third and first connecting rod, and therefore the deployment of the deflection means.
• the outer tube 41 is provided with an internal centering device 49 of the compression spring 43.
• the compression spring 43 is completely contained in the spoiler when the door is in the closed position, so as not to encumber the thrust reverser.
• FIG. 8 illustrates, in the manner of FIG. 5, the deflection means 16 in the deployed position, the elastic means being constituted by the compression spring, the arrangement of which has just been described.
• the deployment of the deflection means 16 is performed in a manner similar to that described above when the elastic means were constituted by the tension spring. Referring now to Figure 9, showing the spoiler 16 in the deployed position.
• the thrust reverser comprises spoiler retaining means 16, said retaining means for locking said spoiler during its rotational movement about its axis, corresponding to the passage from a closed position to a opening position of the door.
• the spoiler 16 comprises for this purpose so-called primary retaining means comprising an upper stop 51 integral with the spoiler 16. Said upper stop engages an abutment support 53 secured to the front frame 12 of the door to allow the spoiler to lock when the rotational movement of said spoiler.
• Said primary retention means further comprises a lower abutment 65 (visible in Figure 1 1), also integral with the spoiler 16, and engaging in a stop support 67 integral with the fixed structure 1 of the thrust reverser.
• the spoiler 16 comprises so-called secondary retaining means, said means comprising a stop 52 integral with the spoiler 16 and engaging in the support 37 secured to the front frame 1 2 door.
• the secondary retaining means allow, when the primary retaining means are not operational, for example following a break of the upper or lower stop, to ensure the locking of the spoiler 16 during its rotational movement about its axis.
• said spoiler 16 In order to secure the spoiler 16 in case of rupture of the primary and secondary retaining means, said spoiler comprises so-called tertiary retaining means.
• the tertiary retention of the spoiler 16 is performed when the end of the first biel comes into contact with the internal center of the compression spring.
• said spoiler is provided with guide means.
• Such guide means are constituted by a guide 55 and the support 37 integral with the front door frame.
• the support 37 is in fact arranged so that the guide 55 moves along a profile 56 of the support 37 when the spoiler 16 is rotated about its axis of rotation.
• the guiding means also comprise an assembly consisting of a roller 57 integral with the spoiler 16 and situated on a peripheral wall 59 of said spoiler, the axis of rotation 61 of which substantially passes through the median axis of the door.
• the roller 57 is intended to come into contact with a ramp 63 secured to the fixed part 1 of the inverter.
• the spoiler 16 adopts a substantially curved parallelepiped shape, and is preferably made of carbon.
• said spoiler 16 comprises an inner surface 69 curved and shaped to provide an extension of the inner surface 1 1 of the door 9 substantially parallel to the motor axis when said door is in the open position and the spoiler 16 deployed.
• the actuating means according to the invention comprise a relatively small number of parts, which facilitates assembly and reduce the mass of the door relative to the prior art.
• the invention is not limited to the embodiments of this door, thrust reverser and nacelle incorporating said inverter, described above as examples, but it embraces all variants.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Wind Motors (AREA)
• Power-Operated Mechanisms For Wings (AREA)
• Refrigerator Housings (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

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ID=47505233

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Family Cites Families (10)

• 2011
  • 2011-12-23 FR FR1162356A patent/FR2984964B1/fr not_active Expired - Fee Related
• 2012
  • 2012-12-07 CA CA2858504A patent/CA2858504A1/fr not_active Abandoned
  • 2012-12-07 WO PCT/FR2012/052837 patent/WO2013093283A1/fr active Application Filing
  • 2012-12-07 CN CN201280063668.XA patent/CN104011360A/zh active Pending
  • 2012-12-07 BR BR112014015279A patent/BR112014015279A8/pt not_active IP Right Cessation
  • 2012-12-07 RU RU2014129435A patent/RU2014129435A/ru not_active Application Discontinuation
  • 2012-12-07 EP EP12810371.0A patent/EP2795087A1/fr not_active Withdrawn
• 2014
  • 2014-06-20 US US14/310,184 patent/US20140301837A1/en not_active Abandoned

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