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
  • F02K1/64—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
  • F02K1/64—Reversing fan flow
  • F02K1/68—Reversers mounted on the engine housing downstream of the fan exhaust section
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• • 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 structure of an inverter 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 position retraction 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.
• each movable hood pivots so as to block the flow and deflect it and is therefore active in this reorientation.
• 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 nacelle said direct jet in which the doors constitute a part of the downstream section, and an inverting position or opening position in which they swing so that a downstream portion of each door at least partially obstruct the conduit 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, during operation of the nacelle reverse jet.
• a thrust reverser has the main purpose of allowing a reduction in the braking distance of an aircraft, by orienting upstream of the nacelle the flow of air passing through the turbojet engine.
• the door (s) of the thrust reverser must therefore ensure on the one hand, a sufficient redirection of the air flow so that the thrust reverser actually performs its functions and, on the other hand, an exhaust of a portion of the air flow in sufficient quantity to avoid the thrust reversal function damaging the turbojet engine.
• EP 0 558 381 which discloses pierced spoilers, is known from the state of the art in order to allow part of the air flow to pass when the doors are open, contributing to the solution. the problem of damage to the engine, but having the disadvantage of losing efficiency with respect to the thrust reversal function.
• EP 0 836 000 aims to increase the flow rate of the air through by creating leakage areas under the doors. Another objective of this document is to enable the recovery of all or part of the created fuels in order to recover the additional thrust of the main counter-thrust.
• the device according to EP 2 060 766 provides for placing spoilers longitudinally on the door of the inverter, so as to better straighten the flow and improve back thrust.
• the devices of the prior art are complex to achieve, or unsuited to the problem inherent in aeronautics, that i is the permanent search for weight reduction.
• an object of the present invention is to solve the disadvantages of the prior art, by proposing an easy integration device, ca ble at the same time of the efforts to co-push all by not increasing the pressure inside the nacel, in order not to damage the turbojet engine.
• the invention proposes a gate for a thrust reverser with doors capable of changing between a position corresponding to a jet operation of a nacel for the turbojet engine for integrating said thrust reverser, and a position corresponding to a reverse jet operation of said nacelle, said door comprising an internal wall designed to integrate with a flow passage of an air flow generated by it it turbojet engine, an external wall designed to provide external aerodynamic continuity of said nacelle, at least one side wall providing the connection between said inner and outer walls of the said door, and means for deflecting the air flow generated by the turbojet engine, the said door being rema rq ublic in that the said deflection means comprise a cavity of the door, said cavity being shaped to convey at least a fraction of said air flow since at least one air inlet sol idaire of the inner wall of the door to at least one air outlet secured to the side wall of the door, so as to redirect, during operation of the nacelle in reverse jet, at least a portion of said air flow
• part of the air flow through the cavities is red irigated forward, that is to say upstream of the nacelle, thus increasing the efforts against -poussée.
• the outgoing air flow is increased by the air inlets created in the inner wall of the door. This makes it possible not to damage the turbojet engine during reverse jet operation.
• the deflection means comprise an extension of the outer wall forming a skirt extending, on the one hand, in a direction substantially parallel to the surface of the inner wall of the door according to the invention and, on the other hand, beyond the side wall of the door.
• the deflection means consist of an insert whose one of its sides is adapted to be fixed inside the inner wall of the door according to the invention and another of its sides is adapted to be fixed to the door. interior of the side wall of said door.
• the cavity is constituted by a solid base of the sides of the insert, said bottom being curved in a direction such that an air flow is deflected from the air inlet of the internal wall of the door to the air outlet of the side wall of said door.
• the curved bottom of the insert allows for the deflection of a portion of the air flow from the air inlet to the inner wall of the door to the sidewall outlet of said door.
• the air inlets are located at the lateral ends of the inner wall of said door.
• the door according to the invention comprises two air inlets and two air outlets.
• the air inlets and outlets are located in the lower part of said door. This arrangement has the advantage of allowing the air inlets to receive a large volume of air, allowing an increase in the leakage rate.
• the invention also relates to a door thrust reverser for turbojet engine nacelle comprising at least one door according to the invention.
• the invention relates to a turbojet engine nacelle equipped with at least one thrust reverser with doors according to the invention.
• FIG. 1 represents a turbojet engine nacelle in reverse jet operation, equipped with a thrust reverser with a door according to the invention
• FIG. 2 illustrates a front view of a door according to the invention
• FIG. 3 is an enlargement of zone III of FIG. 2, corresponding to a centered isometric view of the door according to the invention
• FIG. 4 is an isometric view also centered on the air inlet and outlet of the door according to the invention, a portion of the inner wall of the door not being shown;
• FIG. 5 shows schematically the path of the air traveling through the inner wall of a door according to the invention and deflected by the cavities.
• a thrust reverser comprises generally and known at least one door adapted to be actuated by actuating means such as cylinders to move from a "closed door” position corresponding to a direct jet operation of the nacelle, at an "open door” position corresponding to a reverse jet operation of the nacelle.
• actuating means such as cylinders to move from a "closed door” position corresponding to a direct jet operation of the nacelle, at an "open door” position corresponding to a reverse jet operation of the nacelle.
• door 5 is one of the doors 5a or 5b in the following description.
• a door 5 according to the invention consists of an inner wall 7 connected to an outer wall 9 via a side wall 11, and comprises according to the invention deflection means 13.
• the inner wall 7 of the door 5 forms, with the internal structure 2 of the turbojet engine fairing 3, a vein V intended for the circulation of a flow of cold air F of the turbojet 3, also called secondary air flow.
• the outer wall 9 of the door 5 is designed to provide external aerodynamic continuity of the nacelle 1 during a direct jet operation of the latter.
• the deflection means 13 make it possible to deflect the trajectory of a portion of the flow of cold air F.
• the door 5 comprises at each of its lateral ends 15 a substantially rectangular cutout of a portion of the inner wall 7 of the door 5.
• This cutout constitutes an air inlet 17 shaped to let part of the air flow F into a space defined in the interior part of the door 5, that is to say between the inner walls 7, outer 9, and side 1 1 of the door 5.
• Such a cutout can of course adopt another geometrical shape adapted to let part of the air flow F into the inner part of the door 5.
• the air inlets and outlets 17 and 19 are located in the lower part of the door 5, that is to say, and as can be seen in FIG. 2, that said inputs and outputs air outlets are located in an area of the door 5 closer to the vein V than a free edge 6 of the door 5, during a reverse jet operation of the nacelle, said free edge corresponding to the opposite edge to that which is connected to the nacelle during a reverse jet operation of said nacelle.
• the door 5 ideally comprises two air inlets 17 and two air outlets 19.
• the inner wall 7 of the door 5 comprises an air inlet 17 as previously described.
• the side wall 1 1 of the door 5 also comprises a cutout, of substantially rectangular shape and substantially of the same dimensions as the cutout forming the air inlet 1 7, intended to form an air outlet 1 9 to let s evacuate the flow of air previously entered through the air inlet 17, as described below.
• Such a cutout can obviously adopt another geometric shape of the same dimensions as those of the cutout forming the air inlet 17.
• FIG. 4 illustrating the door 5 according to the invention, centered on the air inlet and outlet 17 and 19, on which a portion of the inner wall 7 and side 1 1 of the door is not shown. .
• the deflection means 13 consist of a part 21 shaped to create a passage for conveying the air from the air inlet 17 to the air outlet 19.
• the part 21 comprises a bottom 23 of substantially rectangular shape and curved. This bottom 23 is shaped to connect a length of the cutout forming the air inlet 17 to a length of the cutout forming the air outlet 19.
• the bottom 23 is covered in width by plates 25 substantially of triangular shape.
• the part 21 comprises two sides 22a, 22b, each side being constituted by a set of stops corresponding to the length of the bottom 23 and to one side of each triangular plate 25.
• the part 21 is intended to be attached to the door 5.
• a first side 22a of the part 21 is secured to the inside of the inner wall 7 of the door 5, and a second side 22b of the part 21 is secured. from the inside of the side wall 1 1 of the door 5.
• This bonding can be achieved by welding, gluing, or by any other means known to those skilled in the art to bring a piece to another.
• the part 21 defines a cavity of the door 5, and the air inlet and outlet 17 and 19 thus communicate with each other via the curved bottom 23 of the part 21.
• the deflection means 13 also comprise a skirt 27 referenced in FIG. 3, formed by a portion of the lateral end of the outer wall 9.
• the surface of the skirt 27 extends towards the outside of the door 5, that is to say beyond the side wall 1 1 of the door 5.
• said skirt 27 extends in a direction substantially parallel to the surface of the inner wall 7 of the door 5.
• This skirt is preferably formed by an extension of the outer wall 9 beyond the side wall January 1 of the door 5.
• an air flow F "coming from the air flow F 'flowing on the inner wall 7 of the door 5 is created via deflection means 13.
• part of the air flow F ' is directly redirected upstream of the nacelle 1 and another part F "enters each air inlet 17 of the inner wall 7 of the door 5.
• the air flow F "then escapes from the cavity of the door 5 by the air outlet 19 at the side wall 1 1 of the door 5.
• the air flow F" is then directed upstream of the inner wall 7 of the door 5, thereby increasing the counter-thrust forces.
• the skirt 27 formed by the lateral end of the outer wall 9 of the door 5, extending in a direction substantially parallel to the surface of the inner wall 7 of the door 5, allows the F "airflow better be straightened.
• the leakage rate of the secondary air flow F circulating in the vein V is increased thanks to the air inlets and outlets 17 and 19, which makes it possible to preserve the turbojet engine from the high stresses due to the counter forces. significant push.
• the counter-thrust forces are substantially increased by the curved bottoms of the door cavity and the air outlets at the side walls of the door, and the risk of damage to the turbojet engine is reduced by creating air inlets on the inner wall of the door.
• the invention is not limited to the embodiments of these doors, thrust reverser provided with these doors and nacelle incorporating such a thrust reverser, described above as examples, but it on the contrary, 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)
• Aviation & Aerospace Engineering (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Wind Motors (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=46968293

Family Applications (1)

Country Status (8)

Families Citing this family (7)

Family Cites Families (11)

• 2011
  • 2011-09-29 FR FR1158733A patent/FR2980825B1/fr not_active Expired - Fee Related
• 2012
  • 2012-09-11 CA CA 2849233 patent/CA2849233A1/fr not_active Abandoned
  • 2012-09-11 WO PCT/FR2012/052027 patent/WO2013045787A1/fr active Application Filing
  • 2012-09-11 CN CN201280047512.2A patent/CN103827473A/zh active Pending
  • 2012-09-11 BR BR112014006690A patent/BR112014006690A2/pt not_active IP Right Cessation
  • 2012-09-11 EP EP12767064.4A patent/EP2761158A1/fr not_active Withdrawn
  • 2012-09-11 RU RU2014116079/06A patent/RU2014116079A/ru not_active Application Discontinuation
• 2014
  • 2014-03-26 US US14/226,180 patent/US20150113944A1/en not_active Abandoned

Non-Patent Citations (1)

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