Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
• • 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
  • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing 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
  • F02K1/78—Other construction of jet pipes
  • F02K1/80—Couplings or connections
  • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle 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
  • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
  • F02K1/32—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for reversing thrust
• • 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
• • 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
  • F05D2240/00—Components
  • F05D2240/55—Seals
• • 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
  • F05D2250/00—Geometry
  • F05D2250/40—Movement of components
  • F05D2250/41—Movement of components with one degree of freedom
• • 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 thrust reversal device of a nacelle of an aircraft.
• the invention also relates to a nacelle comprising such a device and a method implemented by such a device.
• An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.
• ancillary actuating devices include, in particular, a mechanical thrust reversal system.
• a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing the thrust reverser means and intended to surround the engine room. combustion of turbojet engine and, generally terminated by an ejection nozzle located downstream of the turbojet engine.
• This nacelle is intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air from the combustion chamber of the turbojet engine, and a flow of cold air circulating outside the turbojet engine through an annular channel called vein.
• the thrust reversal device is, during landing of the aircraft, intended to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine.
• the thrust reverser device obstructs the stream of cold air flow 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 implemented to achieve this reorientation of the cold air flow vary depending on the type of inverter.
• an inverter comprises a movable cover movable between, on the one hand, an extended position in which it opens in the nacelle a passage for the flow of deflected air, and secondly , a retraction position in which it closes this passage.
• This hood can perform a deflection function or simply activation of other deflection means.
• the reorientation of the air flow is carried out by deflection grids, associated with inversion flaps, the hood having a simple sliding function to discover or cover these deflection grilles.
• the inversion flaps form locking doors that can be activated by the sliding of the hood causing a closing of the vein downstream of the grids, so as to optimize the reorientation of the cold air flow.
• the deflection grids are attached to the turbojet engine casing and the median section of the nacelle using a front frame.
• the sliding cowl belongs to the rear section and has a downstream side forming the ejection nozzle for channeling the ejection of the air flows.
• the optimum section of the ejection nozzle can be adapted according to the different flight phases, namely the take-off, climb, cruise, descent and landing phases of the aircraft.
• An object of the present invention is to overcome these disadvantages.
• the invention proposes a thrust reverser device comprising an upstream structure comprising a front frame, a cover, said cover being extended by a nozzle of variable section, said cover being movable in translation towards at least one deployed position causing a variation of the nozzle section and a retracted position in which the nozzle is in a position in which it provides aerodynamic continuity of the hood, said device being remarkable in that at least a part of the frame before is movable in translation with the hood during its displacement to a position causing a variation of the nozzle section.
• the geometrical tolerances and the relative deformations between the movable cowl and the fixed structure comprising the front frame have less impact during movements of said hood to vary the section of the nozzle, in the sense that the hood no longer moves relative to the front frame during operation in the nozzle variation mode and that the functional clearance between these two parts can be selected at a lower value.
• a device according to the invention may comprise one or more of the following characteristics, taken individually or in combination technically possible:
• the entire front frame is movable in translation with the hood during its movement to a position causing a variation of the nozzle section;
• the front frame comprising a cover panel with a fan casing and a deflection edge, said panel and at least a portion of the deflection edge are movable in translation with the hood during its displacement to a position causing a variation of the nozzle section;
• the front frame is mounted on at least one guide rail placed in the plane of the cover panel;
• the front frame is able to move away from the hood during a movement of the cover to a position ensuring a reverse thrust of the device.
• the invention also relates to a nacelle comprising a thrust reverser device as mentioned above and a fan casing remarkable in that the fan casing comprises an extension structure upstream of the front frame adapted to receive at least partly the cover panel and ensure its movement inside the extension structure.
• a nacelle according to the invention may comprise one or more of the following characteristics, taken in isolation or in combination technically possible:
• the extension structure has dimensions adapted to allow longitudinal movement of the inner cover panel upstream and downstream relative to the position of the front frame corresponding to the retracted position of the cover;
• the interface between the cover panel and the extension structure comprises sliding sealing means
• the nacelle further comprises a removable axial abutment adapted to limit the downstream movement of the cover panel;
• the nacelle further comprises removable locking means of the hood and the front frame.
• the invention also relates to a method implemented with a thrust reverser device as aforesaid in which at least a portion of the front frame is moved when the cap is moved to a position causing a variation of the nozzle section.
• FIG. 1 shows a partial sectional view of a nacelle of an aircraft according to the present invention
• FIG. 2 is a sectional view of a first embodiment of a thrust reverser device according to the present invention
• FIG. 3 and 4 are sectional views respectively of a second and a third embodiment of a thrust reverser device according to the present invention.
• FIGS 5, 5b, 5c and 6 are sectional views of a thrust reverser device according to Figure 2, wherein the nozzle has, respectively, a reduced section, normal, increased and reverse jet;
• FIG. 7 to 9 illustrate sectional views of successive steps of a maintenance method of a thrust reverser device according to the invention
• FIGS. 10a and 10b are an alternative embodiment of the figures
• a nacelle 1 is intended to constitute a tubular housing for a turbojet engine and serves to channel the air flows that it generates by means of blades of a fan 2 that is to say a flow of hot air passing through a combustion chamber and a cold air flow circulating outside the turbojet engine.
• the nacelle 1 generally has a structure comprising an upstream section 3 forming an air inlet, a central section 4 surrounding the turbojet fan and a downstream section 5 surrounding the turbojet engine.
• the downstream section 5 comprises an external structure 1 1 comprising a thrust reverser device 20 and an internal engine fairing structure 10 defining with the external structure 1 1 a vein 13 intended for the circulation of a cold stream in the case of the turbojet turbojet engine nacelle as presented here.
• the downstream section 10 further comprises a front frame 30, a hood
• the front frame 30 is extended by a hood 40 slidably mounted along the longitudinal axis of the nacelle.
• the front frame 30 supports a plurality of deflection grids
• the front frame 30 includes a front panel (not shown) for attaching the center section of the basket to a structural member (not shown). It is called a sail belonging to the front frame. This structural element allows possible resistance to fire.
• the front frame 30 also includes a deflection edge member 31 providing the aerodynamic line.
• This element 31 is extended at these two ends by covering panels 32, 3 ensuring the overlap between the front frame 30 and respectively the fan casing 6 and the median section of the pod 4. These panels will be described in more detail with reference in Figure 2.
• the interface between the front frame 30 and the mobile hood 40 is conventional and known to those skilled in the art.
• a seal 15 is placed at the interface between the front frame 30 and the upstream portion of the hood 40 (see FIG. 2).
• the cover 40 movable meanwhile, is intended to be actuated in a substantially longitudinal direction of the nacelle 1 between a closed position in which it comes in partial overlap of the front frame 30 and ensures the aerodynamic continuity of the outer lines of the section downstream 10 and an open position in which it is spaced from the front frame 30, then opening a passage in the nacelle by discovering the airflow deflection grids.
• the passage allows the secondary flow of the turbojet engine to escape at least partially, this portion of flux being redirected towards the front of the nacelle 1 by the deflection grids, thereby generating a counter-thrust capable of aiding braking of the plane.
• the thrust reverser device 20 comprises a plurality of inversion flaps 21, distributed around the circumference of the inner cover 40 of the inverter 20, and each mounted pivotally by one end about an axis of articulation, on the cover 40 sliding between a retracted position in which the flap 21 closes the opening and ensures the internal aerodynamic continuity of the vein 13 and an extended position in which, in situation of reverse thrust, it at least partially closes the vein 1 3 to deflect a flow of gas to the grids.
• Such an installation can be carried out conventionally with the aid of a set of connecting rods 22 terminated by a spring blade 23.
• the sliding cover 40 forms all or part of a downstream part of the nacelle 1, the flaps 21 then being retracted into the sliding cover 40 which closes the gateway.
• the inversion flaps 21 can remain in the retracted position when the movable cover 40 is displaced from the stroke required for the variation of the nozzle section 41, and begin their pivoting beyond only when the spring 23 is fully compressed.
• the sliding cover 40 is moved downstream position and the flaps 21 pivot in the closed position so as to deflect the secondary flow to the grids and to form an inverted flow guided by the grids.
• the sliding cover 40 has a downstream side forming the exhaust nozzle 41 for channeling the ejection of the air flows.
• the optimum section of the exhaust nozzle 41 can be adapted according to the different phases of flight, namely the take-off, climb, cruise, descent and landing phases of the aircraft.
• the movable hood 40 is thus movable in a nozzle section variation position, namely at least one nozzle section decrease position and a nozzle section increase position.
• the nozzle 41 may comprise a series of movable panels rotatably mounted at a downstream end of the movable cap 40 and distributed over the periphery of the ejection nozzle section 41.
• Each panel is adapted to, on the one hand, pivot to a position causing a variation of the section of the nozzle 41 and, on the other hand, pivot to a position in which they ensure the aerodynamic continuity of the hood.
• Each panel is carried by the movable hood 40 via pivot points along an axis perpendicular to the longitudinal axis of the nacelle with the inner part of the mobile cover 40 and with said movable panel.
• the passage from one position to another of a movable panel is controlled by actuating means connected to the panel by means of a drive system 60 consisting for example of driving rods.
• the actuating means 50 are able to activate the displacement of the movable cover 40 as well as the pivoting of the panel towards a position causing the variation of the section of the nozzle 41.
• Moving the movable cover 40 can thus be done by a rail / slider system known to those skilled in the art or any other suitable actuating means 50 comprising at least one electric, hydraulic or pneumatic linear actuator.
• At least part of the front frame 30 is movable in translation with the cover 40 during its displacement towards a position causing a variation of the nozzle section 41.
• the front frame 30 is adapted to slide together with the cover 40 movable between the extreme positions of section variation and to deviate from the cover 40 when moving the cover 40 to a thrust reverser position.
• Two independent actuating systems can be considered or a single system capable of independently achieving the movement of the front frame 30 or the movable cowl 40, such as a telescopic jack.
• the entire front frame 30 including the cover panels 32, 33 with the blower housing 6 and the deflection grilles are movable in a manner that is translation.
• such a sliding front frame does not modify its interface with the movable cover 40, in particular for the management of the sealing and positioning tolerances.
• the interface between the front frame 30 and the fan casing 6 is the following. As illustrated in FIG. 2, the interface between the fan casing 6 and the movable front frame 30 is slippery with overlapping provided by the above-mentioned cover panels 32, 33.
• the fan casing 6 is extended, in its internal part, downstream, by an extension structure 60 so as to ensure the overlap with the movable front frame 30 and in particular the internal cover panel 32 of the front frame 30.
• This extension structure 60 has a section of generally rectangular shape with a downstream opening adapted for the passage of the inner cover panel 32 of the front frame 30.
• the dimensions of the extension structure 60 are adapted to allow longitudinal displacement of the inner cover panel 32 upstream and downstream relative to the position of the front frame 30 corresponding to the position of the cover 40 associated with the nominal section.
• a sliding seal 62 seals between the extension structure 60 of the fan casing 6 and the movable front frame 30. This seal 62 is extended to the seal located between the movable cover 40 and the front frame 30, and slides along the reactor mast (not shown).
• the extension structure 60 further comprises an axial stop 63 to prevent movement of the front frame 30 beyond a position corresponding to a position of the hood 40 assigned to a maximum increase of nozzle section 41 and to take the axial forces from grids in reverse jet.
• This abutment 63 of general section I is placed at the opening required for the passage of the inner cover panel 32 of the front frame 30.
• Such a stop 63 advantageously allows the front frame 30 to remain in contact with the extension structure 60 of the fan casing 6 during the thrust reversal phase for which the cover 40 is moved in translation further downstream, in order to allow the flaps to pivot inversion 21 in a closed position of the vein 13 of cold flow and the complete clearance of the passage to the deflection grids.
• the geometric tolerances and relative deformations between the movable cover 40 and the fixed front structure of the state of the art do not disturb plus closing the hood 40 on the front frame 30 since the latter moves partly with the hood 40 in the nozzle section variation phases.
• the front frame 30 can be mounted on at least one rail placed in the plane of the grids and, preferably on two rails, one of which is placed in the plane of the internal cover panel 32.
• Each rail can slide directly on the reactor mast so as to allow the retraction of the grids in the case where the structure of the inverter is only one part and must be translated to give access to the engine equipment.
• two rails are placed in the upper and lower beams.
• the front frame 30 comprises actuating means adapted to actuate the front frame 30 relative to the fan casing 6 or to a part which is integral therewith.
• Non-limiting examples include hydraulic, pneumatic or electric actuators or motorized connecting rod screws.
• the movable hood 40 can be actuated either with respect to the fan casing, or preferentially with respect to the front frame 30.
• the actuators of the movable cover 40 remain stationary during the variable nozzle variation phase and the hood 40 moves in concert with the front frame 30 through the means of actuating the front frame 30.
• the movable cover 40 can be locked with respect to the front frame 30 in a direct jet and this for all the nozzle positions, in order to preserve two lines of defense against an inadvertent tripping in flight of the inversion. thrust.
• the movable front frame 30 and the movable cover 40 can thus be connected by conventional latching locking means 70 in the actuator or hooks connecting the two structures.
• Such locking means 70 are adapted to lock the cover 40 movable with the front frame 30 during the phases of nozzle section variation 41 direct jet and to release the cover 40 mobile reverse jet during the reverse thrust.
• the fan housing extension structure 60 is integral with the beams of the inverter.
• the sliding seal 62 sealing between the extension of the fan casing 6 and the movable front frame 30 slides, meanwhile, along the upper and / or lower bifurcation.
• a second embodiment proposes that a front frame portion 30 only be movable in translation with the movable hood 40, namely the internal cover panel 32 and the deflection edge portion 31 defined until to the seal 15 between the front frame 30 and the hood 40.
• the operating principle of the thrust reverser device 20 is as follows.
• the cover 40 In direct jet and the nozzle 41 being in normal section position, namely ensuring the aerodynamic continuity of the cover 40, the cover 40 is in a closed position ensuring the aerodynamic continuity with the front frame 30. It is locked with the latter ( Figure 5b) with the locking means 70 above.
• the movable hood 40 moves upstream of the nacelle causing a decrease in the nozzle section 41.
• the front frame 30 locked with the movable hood 40 also moves upstream of the nacelle, the inner cover panel 32 moving in the extension structure 60 of the fan casing 6.
• the flaps 21 in turn retain their position ensuring the aerodynamic continuity of the inner cover 40.
• the front frame 30 is in a position of abutment against the extension structure 60 of the fan casing 6.
• the cover 40 is released from the front frame 30 by disengaging the locking means 70, this to allow its further displacement downstream of the nacelle in a position in which it discovers the deflection grids and causes the pivoting of the flaps 21 reverse thrust in the vein to redirect air from the vein to the grids.
• FIGS. 7 to 9 show a first embodiment of a method of maintenance of a thrust reverser device 20 according to the invention, allowing access to the equipment housed inside the nacelle. 1 to ensure their maintenance by translation of all moving parts.
• the displacement is ensured by the stroke of the actuators of the front frame 30.
• a suitable space E is thus available to access the equipment of the nacelle for maintenance, as shown in FIG. 9.
• This method offers the advantage of using the actuators already in place in the device and to preserve the structural continuity of the front frame 30.
• Figures 10a and 10b illustrate a second embodiment of a maintenance method of a thrust reverser device according to the invention.
• the inner cover panel 32 is separated from the rest of the front frame 30 to access the equipment of the nacelle.
• a removable axial interface 80 of the assembly type comprising an inverted U-shaped structure 81 cooperating with a plurality of grooves 82, 83 respectively carried by the internal covering panel 32 and the front frame 30 coming into engagement as shown in Figure 10a.
• the front frame assembly 30 is moved without translation without an internal cover panel 32, a movable cover 40 and deflection grids downstream of the platform 1 by means of an actuating system dedicated to maintenance. and known to those skilled in the actuator type art 90.
• this maintenance actuator 90 is placed near or even inside the axis of the hinge of the U-shaped structure 80, so as not to interfere with the trajectory of this structure 80 during opening. or closing the hood 40.
• This embodiment offers the advantage of segregating the variable nozzle function to that of maintaining and maintaining the support of the seal sliding seal even during maintenance operations to limit the risk of damage.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Wind Motors (AREA)
• Body Structure For Vehicles (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=42989468

Family Applications (1)

Country Status (8)

Families Citing this family (6)

Family Cites Families (19)

• 2010
  • 2010-03-25 FR FR1052192A patent/FR2957979B1/fr active Active
• 2011
  • 2011-03-25 CA CA2792973A patent/CA2792973A1/fr not_active Abandoned
  • 2011-03-25 BR BR112012023764A patent/BR112012023764A2/pt not_active IP Right Cessation
  • 2011-03-25 US US13/635,951 patent/US20130009005A1/en not_active Abandoned
  • 2011-03-25 CN CN201180014886.XA patent/CN102812273B/zh not_active Expired - Fee Related
  • 2011-03-25 RU RU2012144581/06A patent/RU2571705C2/ru not_active IP Right Cessation
  • 2011-03-25 WO PCT/FR2011/050657 patent/WO2011117555A1/fr active Application Filing
  • 2011-03-25 EP EP11717298A patent/EP2550471A1/fr not_active Withdrawn

Non-Patent Citations (1)

Also Published As

Similar Documents

Legal Events