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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/005—Repairing methods or devices
• • 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
  • F02K1/60—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
  • F02K1/56—Reversing jet main flow
  • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
  • F02K1/625—Reversing jet main flow by blocking the rearward discharge by means of flaps 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
  • 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
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/76—Control or regulation of thrust reversers
  • F02K1/766—Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices 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
  • F05D2230/00—Manufacture
  • F05D2230/80—Repairing, retrofitting or upgrading methods
• • 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
  • F05D2240/10—Stators
  • F05D2240/14—Casings or housings protecting or supporting assemblies within
• • 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 an aircraft propulsion assembly.
• An aircraft propulsion unit is formed by a nacelle and a turbojet and is intended to be suspended from a fixed structure of the aircraft, for example under a wing or on the fuselage, by means of a suspended suspension mast. to the turbojet engine or to the nacelle.
• the turbojet engine usually comprises a so-called “upstream” section comprising a fan provided with blades and a so-called “downstream” section housing a gas generator.
• the blades of the fan are surrounded by a housing for mounting said turbojet engine in the nacelle.
• the nacelle that has the el, has a generally tubular shape comprising an air inlet upstream of the turbojet engine, a median section intended to surround the turbojet engine fan, and a downstream section housing thrust reverser means and intended to surround the gas generator of the turbojet engine.
• a gas ejection nozzle may extend downstream the thrust reversal means.
• the thrust reverser means obstruct the gas ejection nozzle and direct 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 aircraft.
• a common structure of thrust reverser means comprises a cowl in which an opening is provided for the deflected flow which, in a situation of direct thrust of the gases, is closed by the sliding cowl and which, in a reverse thrust situation, is disengaged by displacement in translation downstream (with reference to the flow direction of the gases) of the sliding cover, by means of displacement cylinders, said displacement cylinders being mounted on a front frame upstream of the opening.
• the maintenance between the median section of the nacelle and the front frame is made by a male part or “vee blade”, usually carried by the front frame, cooperating with a female part or “groove vee”, usually carried by a so-called intermediate housing of the middle section, the male part fixed on the front frame coming to close on the female part.
• an intermediate piece 101 is closed on two female parts 102 mounted on the intermediate casing 103 and the front frame 104, thus providing the connection between the intermediate casing 103 and the front frame 104 of the inverter.
• Such a configuration also has the disadvantage of weighing down the nacelle as well as having a large footprint, this type of connection having an influence on the length of the nacelle.
• the movable cowl is translated to its reverse jet position and deflection grids mounted on the fixed outer structure and more particularly on the front frame are deposited.
• the turbojet is then accessible either by the presence of traps located on the internal structure or by the lateral displacement of the latter downstream.
• Another alternative is to install the grilles on a mobile front frame.
• the front frame is uncoupled from the intermediate casing and the sliding cover assembly, front frame and deflection grids is translated downstream of the nacelle to give access to the motor body.
• the present invention aims to overcome the disadvantages mentioned above.
• the present invention aims to simplify the conventional arrangements, this in particular in order not to weigh down the nacelle.
• An object of the present invention is thus to provide an aircraft propulsion unit that is simpler to produce and has a smaller mass.
• another object of the present invention is to provide an aircraft propulsion system that is simple to implement and to use during maintenance operations.
• the invention proposes an aircraft propulsion unit comprising at least one nacelle comprising at least one intermediate casing and a frame having been designed to be mounted in front of an external port to be fixed. intermediate, said front frame comprising a deflection edge and a support member directly or indirectly at least one flow deflection means characterized in that the deflection edge and said support member are integrated with the outer shell of the intermediate casing .
• the interface between the front frame and the intermediate casing is simplified to the extent that any removable connection is removed between the two elements.
• the reduction in the number of parts at this interface reduces the weight of the nacelle and associated production costs but also reduce the length of the latter.
• the assembly of the invention comprises one or more of the following optional characteristics considered alone or according to all the possible combinations:
• the entire front frame is integrated in the outer shell of the intermediate housing, in one piece or not;
• the assembly further comprises a turbojet engine housed in the nacelle, the turbojet engine comprising a fan surrounded by a casing, said fan casing and an air intake structure of the nacelle or the single fan casing being integrated in the outer shell of the intermediate housing in one piece or not, further limiting the mass of the nacelle;
• the intermediate casing further comprising a hub and flux rectifying blades and optionally radial connecting arms connecting the hub to the outer shell, the hub and / or the flux rectifying blades and / or the arms are integrated in the outer shell of the intermediate casing, in one piece or not;
• the deflection edge, said support member and the outer shell of the intermediate casing are composite material, further reducing the nacelle and facilitating the production of such parts;
• the flow deflection means comprises complementary locking / unlocking means able to engage the flow deflection means with the inverted jet front frame and to detach the flow deflection means from the front frame when a maintenance of said assembly, thus favoring a connection between the front frame and the optimal deflection means in inverted jet in particular and easily detachable during maintenance operations;
• the assembly comprises, downstream from the front frame, an outer cowl mounted to move in translation along a substantially longitudinal axis of the nacelle, said cowl being capable of driving, once the means for deflecting detached flows, in translation the flow deflection means during a maintenance operation;
• the assembly comprises one or more actuators intended to move the cover in translation along a substantially longitudinal axis of the nacelle downstream of the front frame towards at least one thrust reversal position, said cover being able to drive in translation of one or more actuators during a maintenance operation, this making it possible to offer greater access during the maintenance of the assembly.
• FIG. 1 is a partial schematic representation of an aircraft propulsion unit
• FIG. 2 is a partial schematic representation of the connection of a nacelle front frame and an intermediate casing of the aircraft propulsion unit of FIG. 1;
• FIG. 3 is a representation of the prior art in partial longitudinal section of a nacelle comprising a downstream reverse thrust structure having a reversing cover in the closed position;
• - Figure 4 is a partial longitudinal sectional view of a nacelle comprising a reverse thrust reversal structure having a reversing cover in the closed position according to a first embodiment of the present invention
• - Figure 5 is a partial longitudinal section of a nacelle comprising a reverse thrust reversal structure having a reversing cover in the closed position according to a second embodiment of the present invention
• FIGS. 6 and 7 are longitudinal sectional views of the nacelle of Figure 5 with its inversion cover translated downstream, respectively in the inverted jet position and in the maintenance position;
• FIG. 8 is a longitudinal sectional view of a first embodiment of a front frame of the downstream thrust reversal structure of Figures 3 to 6;
• FIG. 9 is a longitudinal sectional view of a second embodiment of a front frame of the downstream reverse thrust structure of Figures 4 to 7;
• an aircraft propulsion unit 1 comprises a nacelle 2 surrounding a turbojet engine 3 which both have a main longitudinal axis A.
• the turbojet engine 3 comprises a fan 4 delivering an annular air flow with a primary flow which supplies the engine 5 driving the fan 4 and a secondary flow that is ejected into the atmosphere while providing a significant fraction of the thrust of the aircraft.
• the fan 4 is contained in an outer casing 6 which channels downstream the secondary flow, this flow passing through a wheel formed by an intermediate casing 7 flat at a median section of the nacelle 2.
• the nacelle 2 typically comprises an upstream air inlet structure 8, a median structure 9 surrounding blades 18 of the fan 4 of the turbojet engine 3, and a downstream structure 10 that can incorporate thrust reversal means 20 .
• This nacelle 2 also comprises an internal structure 1 1 comprising a fairing 13 of the engine 5 downstream of the blades 18 of the fan 4 and which defines, with the downstream structure 10, an annular air stream 17 through which the secondary air flow is intended to circulate, as opposed to the hot primary flow generated by the engine 5.
• the blower 4 is rotatably mounted on a fixed hub 14 connected to the fan casing 6 by a plurality of fixed arms 16 which can transmit a portion of the forces between the motor 5 and its support.
• the intermediate casing 7 is thus a structural element which comprises the hub 14, an annular outer shell 12, in contact with the secondary flow, and which supports the shell of the fan casing 6 and the radial link arms 16 which connect the hub 14. to the outer shell 12.
• This intermediate casing 7 can either consist of a single piece, or a welded or bolted assembly of primary parts.
• the thrust reverser means 20 are, for example, in the form of a movable cowl 21 in longitudinal translation downstream of the nacelle 2 so as to clear an opening in the external downstream structure 10 of the nacelle 2 and discovering deflection grids 22 adapted to reorient a portion of the secondary air flow generated by the turbojet engine towards the front of the nacelle 2 through the opening thus released, as illustrated in FIG. 6.
• the inverter is in the closed position.
• the hood 21 ensures the external aerodynamic continuity of the nacelle 2 with the median section 9 and covers the deflection grids 22.
• locking flaps 23 ensure the internal aerodynamic continuity of the downstream section with the median section 9. When the inverter is activated, these flaps 23 pivot to come at least partially block the flow stream 17 of the secondary flow and assist in its redirection through the deflection grids 22 and the opening in the external downstream structure 10 of the nacelle 2.
• the activation of the inverter is conventionally carried out by at least one actuator of the jack type 24 adapted to drive the cover 21 in translation.
• the deflection grids 22 are attached to the median section 9 of the nacelle by means of a front frame 25 closing the thickness of the nacelle upstream of the hood 21.
• this front frame 25 comprises a front panel 251 intended to support the outer skin of the nacelle placed facing the outer shell 12 of the intermediate casing 7, fixed to a torsion box 253.
• the shape of the rear of the torsion box 253 ensures the aerodynamic function of the secondary flow deflection edge through the grids 22.
• An outer ring 255 allows the attachment of torsion box 253 and deflection grids 22.
• the front frame 25 may be made using radial ribs 252 instead of a torsion box 253 to stiffen the structure.
• These ribs 252 are placed in the concavity of an element 253 forming a deflection edge of the frame before 25 so as to ensure the aerodynamic line of the front frame 25.
• the intermediate casing 7 integrates in its downstream part and, more specifically, downstream of the outer shell 12, the deflection edge 253 and the support elements. deflection grids 22.
• connection between the outer shell 12 of the intermediate casing 7 and the front frame 25 is a complete non-removable connection, that is to say that any mobility is removed between the front frame 25 and the shell 12 .
• This non-removable connection between the front frame 25 and the shell 12 may be riveting, bonding, forced fitting, welding in non-limiting examples of the present invention.
• the support elements of the deflection gratings may be the outer ring 255 and the torsion box 253.
• the outer shell 12 of the intermediate casing 7, the torsion box 253 or the deflection edge assembly with its ribs 252 are formed in one piece.
• the entire front frame 25 is integrated in the outer shell 12 of the intermediate casing 7 in one piece or not.
• the outer shell 12 of the intermediate casing 7 is integrated with the fan casing 6 alone or with the inner shell of the air inlet structure 8.
• the outer shroud assembly 12 of the intermediate casing 7 and the front frame 25 are integrated with the flow straightening vanes 15 and / or the hub 14 and / or the connecting arms and the suspension screeds. motor if they are located on the outer shell 12 of the intermediate casing of the intermediate casing 7.
• the members mentioned in the third and fourth variants are formed of a single structural element.
• outer shell 12 of the intermediate casing 7 and / or the front frame 25 may be made of a composite material.
• the composite material may be selected from materials based on carbon fibers, glass fibers, aramid fibers or a mixture of these materials with a resin.
• This composite material can be obtained from pre-impregnated fabrics or by a so-called Liquid Composite Molding (LCM) process in which the resin is mixed with dry carbon fabrics or a woven or braided preform, where appropriate. .
• LCD Liquid Composite Molding
• the above-mentioned set of integrated members to the outer shell 12 of the intermediate casing that is to say the entire front frame 25, the hub 14, the OGVs 1 5 and the motor suspension screeds are formed of a single structural element for example composite material. This makes it possible to obtain a multipurpose piece of overall weight that is much lower than all the parts it replaces, and that does not require any assembly operation.
• the actuating jacks 24 of the cover 21 and the deflection grids 22 are supported on the assembly formed by the front frame 25 and the outer shell 12 of the intermediate casing 7 according to FIG. invention.
• the deflection grids 22 are able to be connected to the front frame 25 in a detachable manner by locking / unlocking means which allow the disengagement of said grids 22 from the front frame 25 and the middle section 9 and their downstream translation. regardless of the frame before 25.
• the fixed front frame 25 and the removable inversion gates 22 are attached in the operating configuration of the inverter, in the inverted jet phase when the cowl 21 slides downstream of the nacelle 2 and the inversion flaps. 23 obstruct the vein 17 as shown in Figure 6 and in the flight phases.
• the front frame assembly 22 and the intermediate casing 7 form a non-movable fixed assembly in a maintenance position while the deflection grids 22 and the cover 21 form a unitary movable assembly that can be moved in this position. maintenance position.
• the locking / unlocking means 30 between the deflection gratings 22 and the front frame 25 may be of any type.
• the locking / unlocking means 30 comprise at least one pair of male and female connectors 32, one integral with the front frame assembly 25 / outer shell 12 and the other of the deflection gratings 22.
• the connectors are arranged in such a way that they cooperate during the phases of flight and the inverted jet phases (see FIGS. 4 to 6) joining the deflection grids 22 with the front frame assembly 25 / outer shell of the casing 7 and detach during maintenance operations illustrated in Figure 7 to translate the assembly formed by the cover 21 and the deflection means 22.
• the propulsion unit 1 according to the invention and more specifically the thrust reverser is implemented as follows.
• the cover 21 moves from a closed position where it provides aerodynamic continuity with the center section 9 of the nacelle to an open position downstream of the nacelle 2, in order to discover the deflection grids 22 to deflect part of the secondary air flow through these grids 22.
• inversion flaps 23 also move during the race of the hood 21 and deploy in the vein 17 cold flow.
• the locking means 30 are first disengaged between the front frame assembly 22 / outer shell 12 of the intermediate casing 7 and the deflection grilles 22.
• an assembly formed by the cover 21 and the deflection grids 22 can be moved in translation downstream of the nacelle 2 of the closed position of the cover 21 at a position maintenance, either through the actuating cylinders 24 of the cover 21 or by any other suitable means.
• the jacks 24 can be translatable to the maintenance position and thus move simultaneously with the hood 21 and the deflection grilles 22.
• the displacement of the cylinders 24 offers the advantage of not hampering access to the engine 5 of the turbojet engine 3.
• the various movements completed, an opening is then released, which allows any person to access in particular the internal structure 1 1 fixed nacelle 2 or the body of the engine 5.
• the aforementioned maintenance position of the cover 21 may correspond to the position of the inverted jet cover 21 or to a position downstream of the position of the inverted jet cover 21.

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• 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)

Applications Claiming Priority (2)

Publications (1)

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ID=43919867

Family Applications (1)

Country Status (8)

Families Citing this family (7)

Family Cites Families (22)

• 2010
  • 2010-10-04 FR FR1057998A patent/FR2965588B1/fr active Active
• 2011
  • 2011-10-03 RU RU2013119476/06A patent/RU2013119476A/ru not_active Application Discontinuation
  • 2011-10-03 BR BR112013006465A patent/BR112013006465A2/pt not_active IP Right Cessation
  • 2011-10-03 CN CN2011800481237A patent/CN103154489A/zh active Pending
  • 2011-10-03 CA CA2811481A patent/CA2811481A1/fr not_active Abandoned
  • 2011-10-03 EP EP11779780.3A patent/EP2625413A1/de not_active Withdrawn
  • 2011-10-03 WO PCT/FR2011/052298 patent/WO2012045965A1/fr active Application Filing
• 2013
  • 2013-04-03 US US13/856,038 patent/US20130277454A1/en not_active Abandoned

Non-Patent Citations (1)

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