EP3194749A1 - Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle - Google Patents

Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle

Info

Publication number
EP3194749A1
EP3194749A1 EP15788468.5A EP15788468A EP3194749A1 EP 3194749 A1 EP3194749 A1 EP 3194749A1 EP 15788468 A EP15788468 A EP 15788468A EP 3194749 A1 EP3194749 A1 EP 3194749A1
Authority
EP
European Patent Office
Prior art keywords
flange
ferrule
downstream
outer skin
protrusion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP15788468.5A
Other languages
German (de)
French (fr)
Inventor
Bertrand Desjoyeaux
Simon VERGER
Sylvain SENTIS
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Safran Nacelles SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Nacelles SAS filed Critical Safran Nacelles SAS
Publication of EP3194749A1 publication Critical patent/EP3194749A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/16—Aircraft characterised by the type or position of power plant of jet type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
    • 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
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2260/30—Retaining components in desired mutual 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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 invention relates to an air intake of an aircraft turbojet engine nacelle.
  • the invention relates to a particular form of the structure of the air inlet for its attachment to a nacelle fan casing according to a radial interface surface.
  • An aircraft is driven by several turbojet engines each housed in a nacelle housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.
  • a turbojet engine nacelle generally has a substantially tubular structure which extends along a longitudinal axis from upstream to downstream, depending on the direction of flow of the air flow.
  • the nacelle comprises an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section surrounding the combustion chamber of the turbojet engine, intended to channel the secondary air stream and possibly incorporating d thrust reversal, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • the air inlet comprises in particular an annular entry lip forming a leading edge which is adapted to allow optimal capture of the air necessary for the supply of the blower and the internal compressors of the turbojet engine. Downstream of the lip, an acoustic downstream structure properly channels the air to the vanes of the blower.
  • This downstream structure of the air inlet comprises in particular an annular duct whose structure is particularly adapted to attenuate the noise emitted by the turbojet engine, also called the acoustic air inlet shell.
  • the ferrule is mainly constituted by an acoustic sandwich structure comprising, an acoustically permeable skin also forming an inner skin of the air duct, an impervious outer skin, and a honeycomb core of predetermined height connecting the two skins, this core being generally Honeycomb type, the assembly constituting an acoustic damper.
  • the shell is assembled in its downstream part with the fan casing according to a clamping plane by means of a device comprising fasteners connecting vis-à-vis the flange of the air intake ferrule and the housing.
  • the clamping plane For safety reasons in case of loss of a blade of the blower, the clamping plane must be positioned upstream of the blade of the plane of the blower.
  • the document FR-A-2767560 describes and represents a device comprising a first L-shaped flange integral with the fan casing and a second L-shaped flange, an axial base of which is riveted to the outer skin of the shell and a flange of which radial is attached to the first flange.
  • This type of device has the disadvantage of having to bind the inner skin and the outer skin of the ferrule to associate them in one to the attachment area of the second flange L.
  • FR-A-2869360 which proposes a second L-shaped flange attached to the outer skin of the ferrule
  • this type of device has the disadvantage of perforating the outer skin.
  • the quality of the fixation is difficult to verify and the acoustic cavity between the outer skin and inner skin is impaired reducing the efficiency of the area.
  • This document also proposes an L-flange directly glued or made to the back of the outer skin of the ferrule, however this device has the risk of punching the cellular material connecting the inner skin and the outer skin during mechanical deformations induced by the operation of the turbojet.
  • Also known device described and shown in FR-A-2959726 which comprises a first flange which is integral with the housing and a second flange which is integral with the ferrule.
  • This device provides advantages by proposing an L-flange bonded to the ferrule and which is offset to the back of the outer skin of the ferrule which avoids impacting the acoustic treatment of said shell, but is difficult and expensive to achieve.
  • the present invention aims in particular to solve these disadvantages and relates for this purpose to a device for fixing a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle, the air inlet comprising an acoustic ferrule having an annular shape which extends axially from upstream to downstream along a longitudinal axis and which is delimited radially by an internal skin and an external skin trapping an acoustic panel, the device comprising a first flange which is secured to the housing, and a second L-shaped flange which comprises a base adapted to be connected to the shell, and a flange adapted to be connected to the second flange, characterized in that it comprises a protrusion which s' extends longitudinally from an integral upstream section of the outer skin of the ferrule, to a flared upstream section which delimits a radial space with the ferrule and which is adapted é to be fixed on the base of the second L-shaped flange by fixing
  • the device according to the invention is of simple design and offers a reliable and costly solution for fixing a ferrule on a fan casing.
  • the invention makes it possible not to alter and maintain the integrity of the acoustic structure of the ferrule formed by the outer skin, the inner skin and the acoustic panel of the ferrule.
  • the protuberance has the shape of an annular ring which extends around the axis of the ferrule.
  • the acoustic panel of the ferrule extends longitudinally continuously from upstream to downstream at least to the downstream portion of the protrusion.
  • the ring and the second flange can each be made of a separate material which is chosen to best meet the mechanical stress and imposed weight requirements.
  • the second flange is made of metallic material.
  • the second flange is made of a plurality of independent parts which are arranged in a ring around the axis of the ferrule.
  • the crown is made of composite material. This type of material offers a weight / strength compromise adapted to the mechanical stresses subjected to the crown.
  • the ring has a wavy shape which draws an alternation of hollow and bumps distributed around the axis of the shell, said bumps each forming a radial extra thickness designed to promote the attachment of the second L-shaped flange.
  • the acoustic panel extends longitudinally downstream beyond the plane of the second L-shaped flange.
  • the design of the device according to the invention makes it possible not to perforate the acoustic panel by fixing means, thus preserving all the acoustic absorption performance of the panel.
  • the device comprises a wedge which is interposed radially between the outer skin of the ferrule and the flared downstream portion of the crown.
  • the fastening means comprise a plurality of metal links which connect the flared upstream portion of the ring to the base of the second L-shaped flange.
  • the invention also relates to a method for manufacturing a device for fixing a downstream end of an air intake on a fan casing of an aircraft turbojet engine nacelle, according to any one of the preceding claims, characterized in that the protrusion is made integrally with the outer skin of the ferrule.
  • FIG. 1 is a schematic view in longitudinal section, which illustrates an aircraft turbojet engine nacelle
  • FIG. 2 is a schematic longitudinal sectional view, which illustrates a device for fixing the air intake ring on a fan casing of the nacelle of Figure 1, according to the invention
  • FIG. 3 is a detail view broken away in perspective, which illustrates the first flange and the second flange of the device of FIG. 2;
  • - Figure 4 is a detail view broken away in perspective, which illustrates the first flange and the second flange of the device of Figure 2 according to an alternative embodiment;
  • FIG. 5 is a detail view with tear in perspective, which illustrates the connecting ring of the second flange on the ferrule of the device of Figure 2;
  • FIG. 6 is a detailed cross-sectional view, which illustrates the connecting ring of the second flange on the ferrule of the device of Figure 2.
  • upstream and downstream must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet engine. , that is from left to right according to FIG.
  • FIG. 1 shows a nacelle 10 of a turbojet engine 12 which has a tubular structure and which extends along a longitudinal axis A from upstream to downstream in the direction of flow of the airflow, from the left to the right according to Figure 1.
  • the nacelle 10 comprises an air inlet 14 arranged upstream of the turbojet engine 12, a median section 16 intended to surround a fan 18 of the turbojet engine 12, a downstream section 20 intended to surround the combustion chamber of the turbojet engine 12 and possibly including means thrust reverser (not shown), and an ejection nozzle 22.
  • the air inlet 14 comprises in particular an annular inlet lip 24 forming a leading edge, and a downstream tubular structure forming a ferrule 28 acoustics on which is reported the lip 24 for channeling the air towards the vanes of the blower 18.
  • the acoustic ferrule 28 is extended longitudinally by a fan casing 30 to guide the flow of air.
  • the ferrule 28 has an annular shape of axis A, which extends axially from upstream to downstream along the longitudinal axis A of the nacelle 10 and which is delimited radially by a skin internal 32 and an outer skin 34 which traps a cellular acoustic panel 70.
  • the inner skin 32 is acoustically permeable and is for example constituted by a perforated skin allowing the sound waves to pass through it.
  • the outer skin is waterproof and acoustically impermeable.
  • the acoustic panel 70 is preferably a cellular material keeping the inner skin 32 and the outer skin 34 at a distance, the acoustic panel 70 forming a cavity designed to absorb and dampen the sound waves.
  • the nacelle 10 is equipped with a device 36 for fixing the air inlet 14 on the fan casing 30, more particularly for fixing the acoustic shell 28 on the casing 30.
  • the fixing device 36 comprises a first metal flange 38 which is fixed on an upstream end of the casing 30, and a second L-shaped metal flange 40 which is fixed on a downstream end of the ferrule 28.
  • the first flange 38 has an annular base 42 extending generally axially along the longitudinal axis A of the nacelle 10 and which is fixed to the casing 30 by a mechanical connection means (not shown) as a set of screws. and nuts for example, or by any other means of attachment.
  • first flange 38 has an annular collar 44 projecting radially outwardly from the base 42 and defining a first radial clamping face 46 arranged opposite the second flange 40.
  • second flange 40 has an annular base 48 which extends generally axially along the longitudinal axis A of the nacelle 10 and an annular flange 50.
  • the flange 50 of the second flange 40 projects radially outwardly from the associated base 48, the flange 50 delimiting a second radial flange face 52 intended to cooperate with the first flange face 46 complementary to the first flange 38.
  • the second clamping face 52 and the first clamping face 46 are contiguous along a radial clamping plane P, and they each delimit a series of holes for the passage of fastening means, such as a set of screws and bolts. nuts 54 for example, or any other means of attachment.
  • the second flange 40 is made of metal alloy, and preferably of aluminum alloy or titanium.
  • alloys have high strengths and elongations before rupture which are particularly suitable for producing this type of flange which must withstand significant deformations imposed by the casing 30 in extreme cases of failure of a blade of the blower.
  • the second flange 40 may be made of composites among discontinuous and continuous fiber thermocompression technologies, or RTM molding of fibrous textures.
  • the fibers are preferably chosen from carbon fibers, glass fibers, and matrices from thermosetting epoxy polymers and thermoplastics from the Polyaryletherketone family.
  • the flange 50 of the second flange 40 and the flange 44 of the first flange 38 can be machined.
  • the second flange 40 is made of a plurality of sector-shaped portions 55 which are independent and identical and which are arranged in a ring around the axis of the ferrule 28.
  • each part 55 delimits three holes which are uniformly distributed around the axis A and which are provided for the passage of the fastening means on the first flange 38.
  • the second flange 40 is made in one piece in the form of a ring.
  • the second flange 40 may be made of a plurality of parts which are mechanically interconnected by means of reported links.
  • the device 36 comprises an annular crown protrusion 56 which extends around the axis A of the nacelle 10 and which extends longitudinally from an upstream section 58 integral with the outer skin 34 from the shell 28, to a downstream section 60 which is adapted to be fixed on the base 48 of the second L-shaped flange 40 by means of fasteners 61.
  • the downstream section 60 of the ring 56 has a globally frustoconical flared shape of increasing radial section in an axial direction from upstream to downstream, this flared shape allowing the downstream section 60 to delimit a radial space 62, or cavity, with the outer skin 34 of ferrule 28.
  • the ring 56 is made of composite material.
  • the ring 56 is made of a succession of fabric skins which are pre-impregnated with a binder, such as resin.
  • the ring 56 is made at the same time as the outer skin 34 of the collar 28, by a stack of layers of fabric and or fibers that can be part of the constitution of the outer skin 34.
  • the layers of fabrics and / or fibers are impregnated with resin and solidified by polymerization.
  • the skins of the crown 56 can be made by placing process pre-impregnated fibers of binder or draping pre-impregnated sheets of binder.
  • the ring 56 can also be made by injection molding, for example by a resin injection process in a fiber preform arranged in a mold, this type of process is known by the acronym RTM for "resin transfer molding".
  • the crown 56 can be glued or co-fired with the fiber layers of the outer skin 34 of the ferrule 28.
  • the ring may be made by any other type of process for manufacturing a part made of composite material.
  • an extractable tooling element (not shown) can be inserted for draping and polymerization of the assembly. .
  • the downstream portion 60 of the ring 56 which is radially offset from the acoustic shell 28, has the advantage of not altering the geometric shape of the acoustic assembly formed by the outer skin 34, the inner skin 32 and the acoustic panel. 70 of the shell 28 which then extends axially continuously downstream continuously beyond the ring 56 and can extend up to the plane P of clamping, and possibly even beyond inside the fan casing 30.
  • the device 36 comprises a wedge 64 of triangular section, shown in Figure 4, which is interposed radially between the outer skin 34 of the ferrule 28 and the downstream portion 60 flares from the ring 56 .
  • the wedge 64 is for example made of composite material and in particular makes it possible to avoid or limit the deformation of the downstream section 60 of the ring 56, the wedge 64 possibly having the shape of a closed or open ring or formed of several angular sectors. .
  • the fixing means 61 of the downstream section 60 of the ring 56 on the base 48 of the second flange 40 comprise a plurality of metal links, such as a set of screws and nuts and / or a set of rivets for example.
  • the base 48 of the second flange 40 delimits a series of holes 65 for the passage of the fastening means 61.
  • the holes 65 are distributed in two rows, staggered as shown in Figure 4 or vis-à-vis as shown in Figure 3.
  • downstream portion 60 of the ring 56 can be machined if necessary to promote cooperation between the downstream section 60 of the ring 56 and the base 48 of the second flange 40 associated.
  • downstream section 60 of the ring 56 has a shape corrugated which draws an alternation of hollow 66 and bumps 68 distributed around the axis A of the ferrule 28.
  • the bumps 68 each form a radial excess thickness designed to promote the fixing of the ring 56 on the second flange 40 by the fastening means 61, as can be seen in FIG.
  • the acoustic panel 70 extends longitudinally beyond the plane P of the second flange 40 in L.
  • the acoustic panel 70 may extend only to the clamping plane P, the casing 30 then comprising an additional acoustic panel arranged in the extension.
  • the fixing device 36 is lightweight, simple in design, robust and reliable, and it enables the ferrule 28 to be connected to the casing 30 without perforating the acoustic panel 70, thus preserving all its absorption capacities of the noise.
  • the invention also relates to a method for manufacturing the device 36 described above.
  • the protrusion 56 is made integrally with the outer skin 34 of the ferrule 28.
  • the expression "made from material” means that the excrescence 56 is performed simultaneously with the outer skin 34 of the ferrule 28, as previously described.

Abstract

The invention relates to a device (36) for attaching a downstream end of an air inlet onto a fan casing (30) of an aircraft turbojet nacelle. The air inlet comprises an acoustic ferrule (28) that is radially defined by an inner skin (32) and an outer skin (34) that confine an acoustic panel (70). The device (36) comprises: a first flange (38) that is rigidly connected to the casing (30); a second L-shaped flange (40) that includes a base (48) provided such as to be connected to the ferrule (28); and a collar (50) provided such as to be connected to the first flange (38). Said device is characterized in that it comprises an extension (56) that longitudinally extends from an upstream section (58), rigidly connected to the outer skin (34) of the ferrule (28), to a widened downstream section (60) that defines a radial space (62) with the ferrule (28) and is attachable onto the base (48) of the second L-shaped flange (40) by attachment means (61), without damaging the outer skin (34) of the ferrule (28).

Description

Dispositif pour la fixation d'une entrée d'air sur un carter de soufflante d'une nacelle de turboréacteur d'aéronef  Device for attaching an air inlet to a fan casing of an aircraft turbojet engine nacelle
L'invention concerne une entrée d'air d'une nacelle de turboréacteur d'aéronef. The invention relates to an air intake of an aircraft turbojet engine nacelle.
Plus précisément, l'invention concerne une forme particulière de la structure de l'entrée d'air pour sa fixation sur un carter de soufflante de nacelle suivant une surface d'interface radiale.  More specifically, the invention relates to a particular form of the structure of the air inlet for its attachment to a nacelle fan casing according to a radial interface surface.
Un aéronef est mû par plusieurs turboréacteurs logés chacun dans une nacelle abritant un ensemble de dispositifs d'actionnement annexes liés à son fonctionnement et assurant diverses fonctions lorsque le turboréacteur est en fonctionnement ou à l'arrêt.  An aircraft is driven by several turbojet engines each housed in a nacelle housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.
Une nacelle de turboréacteur présente généralement une structure sensiblement tubulaire qui s'étend selon un axe longitudinal d'amont en aval, suivant le sens d'écoulement du flux d'air.  A turbojet engine nacelle generally has a substantially tubular structure which extends along a longitudinal axis from upstream to downstream, depending on the direction of flow of the air flow.
La nacelle comprend une entrée d'air en amont du turboréacteur, une section médiane destinée à entourer une soufflante du turboréacteur, une section aval entourant la chambre de combustion du turboréacteur, destinée à canaliser le flux d'air secondaire et intégrant éventuellement des moyens d'inversion de poussée, et est généralement terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.  The nacelle comprises an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section surrounding the combustion chamber of the turbojet engine, intended to channel the secondary air stream and possibly incorporating d thrust reversal, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
L'entrée d'air comprend notamment une lèvre d'entrée annulaire formant bord d'attaque qui est adaptée pour permettre la captation optimale de l'air nécessaire à l'alimentation de la soufflante et des compresseurs internes du turboréacteur. En aval de la lèvre, une structure aval acoustique canalise convenablement l'air vers les aubes de la soufflante.  The air inlet comprises in particular an annular entry lip forming a leading edge which is adapted to allow optimal capture of the air necessary for the supply of the blower and the internal compressors of the turbojet engine. Downstream of the lip, an acoustic downstream structure properly channels the air to the vanes of the blower.
Cette structure aval de l'entrée d'air comprend notamment un conduit annulaire dont la structure est particulièrement adaptée pour atténuer le bruit émis par le turboréacteur encore appelée virole d'entrée d'air acoustique.  This downstream structure of the air inlet comprises in particular an annular duct whose structure is particularly adapted to attenuate the noise emitted by the turbojet engine, also called the acoustic air inlet shell.
Pour cela la virole est principalement constituée d'une structure sandwich acoustique comprenant, une peau acoustiquement perméable faisant également peau interne du conduit d'air, une peau externe étanche, et une âme alvéolaire de hauteur prédéfinie reliant les deux peaux, cette âme étant généralement de type Nid d'abeille, l'ensemble constituant un amortisseur acoustique. La virole est assemblée dans sa partie avale avec le carter de soufflante suivant un plan de bridage au moyen d'un dispositif comportant des fixations reliant en vis-à-vis les bride de la virole d'entrée d'air et du carter. For this purpose the ferrule is mainly constituted by an acoustic sandwich structure comprising, an acoustically permeable skin also forming an inner skin of the air duct, an impervious outer skin, and a honeycomb core of predetermined height connecting the two skins, this core being generally Honeycomb type, the assembly constituting an acoustic damper. The shell is assembled in its downstream part with the fan casing according to a clamping plane by means of a device comprising fasteners connecting vis-à-vis the flange of the air intake ferrule and the housing.
Pour des raisons de sécurité en cas de perte d'une aube de la soufflante, le plan de bridage doit être positionné en amont de l'aube du plan de la soufflante.  For safety reasons in case of loss of a blade of the blower, the clamping plane must be positioned upstream of the blade of the plane of the blower.
De plus, il est souhaitable d'atténuer les bruits émis par le moteur en amont et en aval du plan de bridage et de maximiser la surface de la veine interne efficace acoustiquement, et notamment la surface acoustique de la virole d'entrée d'air.  In addition, it is desirable to attenuate the noise emitted by the engine upstream and downstream of the clamping plane and to maximize the surface of the acoustically effective internal vein, and in particular the acoustic surface of the air intake ferrule. .
Dans ce but, le document FR-A-2767560 décrit et représente un dispositif comportant une première bride en L solidaire du carter de soufflante et une seconde bride en L dont une embase axiale est rivetée sur la peau extérieure de la virole et dont une collerette radiale est fixée à la première bride.  For this purpose, the document FR-A-2767560 describes and represents a device comprising a first L-shaped flange integral with the fan casing and a second L-shaped flange, an axial base of which is riveted to the outer skin of the shell and a flange of which radial is attached to the first flange.
Ce type de dispositif présente notamment l'inconvénient de devoir lier la peau interne et la peau externe de la virole pour les associer en une seule à la zone de fixation de la seconde bride en L.  This type of device has the disadvantage of having to bind the inner skin and the outer skin of the ferrule to associate them in one to the attachment area of the second flange L.
De plus, l'emboîtement d'une portion amont du carter dans la virole est délicat à réaliser et peut provoquer une instabilité vibratoire de la portion amont du carter qui est en porte-à-faux. Il augmente également les risques d'endommagement d'extrémité des pièces lors de l'emboitement.  In addition, the interlocking of an upstream portion of the housing in the shell is difficult to achieve and can cause vibration instability of the upstream portion of the housing which is cantilevered. It also increases the risk of damage to the end of the parts during the interlocking.
On connaît aussi le document FR-A-2869360 qui propose une seconde bride en L rapportée fixée à la peau externe de la virole, ce type de dispositif présente l'inconvénient de perforer la peau externe. La qualité de pose des fixations est difficile à vérifier et la cavité acoustique entre peau externe et peau interne est altérée réduisant l'efficacité de la zone. Ce document propose aussi une bride en L directement collée ou réalisée au dos de la peau externe de la virole, cependant ce dispositif présente le risque de poinçonner le matériau alvéolaire reliant la peau interne et la peau externe lors des déformations mécaniques induites par le fonctionnement du turboréacteur.  Also known FR-A-2869360 which proposes a second L-shaped flange attached to the outer skin of the ferrule, this type of device has the disadvantage of perforating the outer skin. The quality of the fixation is difficult to verify and the acoustic cavity between the outer skin and inner skin is impaired reducing the efficiency of the area. This document also proposes an L-flange directly glued or made to the back of the outer skin of the ferrule, however this device has the risk of punching the cellular material connecting the inner skin and the outer skin during mechanical deformations induced by the operation of the turbojet.
On connaît aussi un dispositif décrit et représenté dans le document FR-A-2959726 qui comporte une première bride qui est solidaire du carter et une seconde bride qui est solidaire de la virole.  Also known device described and shown in FR-A-2959726 which comprises a first flange which is integral with the housing and a second flange which is integral with the ferrule.
Ce dispositif apporte des avantages en proposant une bride en L liée à la virole et qui est déportée au dos de la peau externe de la virole ce qui évite d'impacter le traitement acoustique de ladite virole, mais est difficile et coûteux à réaliser. This device provides advantages by proposing an L-flange bonded to the ferrule and which is offset to the back of the outer skin of the ferrule which avoids impacting the acoustic treatment of said shell, but is difficult and expensive to achieve.
La présente invention vise notamment à résoudre ces inconvénients et se rapporte pour ce faire à un dispositif pour la fixation d'une extrémité aval d'une entrée d'air sur un carter de soufflante d'une nacelle de turboréacteur d'aéronef, l'entrée d'air comportant une virole acoustique présentant une forme annulaire qui s'étend axialement d'amont en aval suivant un axe longitudinal et qui est délimitée radialement par une peau interne et une peau externe emprisonnant un panneau acoustique, le dispositif comportant une première bride qui est solidaire du carter, et une seconde bride de forme en L qui comprend une embase prévue pour être reliée à la virole, et une collerette prévue pour être reliée à la seconde bride, caractérisé en ce qu'il comporte une excroissance qui s'étend longitudinalement depuis un tronçon amont solidaire de la peau extérieure de la virole, jusqu'à un tronçon aval évasé qui délimite un espace radial avec la virole et qui est adapté pour être fixé sur l'embase de la seconde bride en L par des moyens de fixations sans altérer la peau extérieure de la virole.  The present invention aims in particular to solve these disadvantages and relates for this purpose to a device for fixing a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle, the air inlet comprising an acoustic ferrule having an annular shape which extends axially from upstream to downstream along a longitudinal axis and which is delimited radially by an internal skin and an external skin trapping an acoustic panel, the device comprising a first flange which is secured to the housing, and a second L-shaped flange which comprises a base adapted to be connected to the shell, and a flange adapted to be connected to the second flange, characterized in that it comprises a protrusion which s' extends longitudinally from an integral upstream section of the outer skin of the ferrule, to a flared upstream section which delimits a radial space with the ferrule and which is adapted é to be fixed on the base of the second L-shaped flange by fixing means without altering the outer skin of the ferrule.
Le dispositif selon l'invention est de conception simple et propose une solution fiable et peut coûteuse pour la fixation d'une virole sur un carter de soufflante.  The device according to the invention is of simple design and offers a reliable and costly solution for fixing a ferrule on a fan casing.
De plus, l'invention permet de ne pas altérer et de conserver l'intégrité la structure acoustique de la virole formée par la peau externe, la peau interne et le panneau acoustique de la virole.  In addition, the invention makes it possible not to alter and maintain the integrity of the acoustic structure of the ferrule formed by the outer skin, the inner skin and the acoustic panel of the ferrule.
De préférence, l'excroissance présente la forme d'une couronne annulaire qui s'étend autour de l'axe de la virole.  Preferably, the protuberance has the shape of an annular ring which extends around the axis of the ferrule.
De plus, le panneau acoustique de la virole s'étend longitudinalement de façon continue d'amont en aval au moins jusqu'au tronçon aval de l'excroissance.  In addition, the acoustic panel of the ferrule extends longitudinally continuously from upstream to downstream at least to the downstream portion of the protrusion.
La couronne et la seconde bride peuvent être réalisées chacune en un matériau distinct qui est choisi pour répondre au mieux aux sollicitations mécaniques et aux exigences de poids imposées.  The ring and the second flange can each be made of a separate material which is chosen to best meet the mechanical stress and imposed weight requirements.
De préférence, la seconde bride est réalisée en matériau métallique.  Preferably, the second flange is made of metallic material.
Ce type de matériau offre une résistance élastique supérieure à un matériau composite, permettant ainsi d'encaisser des efforts importants sans rompre. Selon un exemple de réalisation préféré, la seconde bride est réalisée en une pluralité de parties indépendantes qui sont agencées en anneau autour de l'axe de la virole. This type of material offers an elastic resistance greater than a composite material, thus allowing to absorb significant forces without breaking. According to a preferred embodiment, the second flange is made of a plurality of independent parts which are arranged in a ring around the axis of the ferrule.
De plus, la couronne est réalisée en matériau composite. Ce type de matériau offre un compromis poids/résistance adapté aux sollicitations mécaniques soumises à la couronne.  In addition, the crown is made of composite material. This type of material offers a weight / strength compromise adapted to the mechanical stresses subjected to the crown.
Avantageusement, la couronne présente une forme ondulée qui dessine une alternance de creux et de bosses réparties autour de l'axe de la virole, lesdites bosses formant chacune une surépaisseur radiale conçue pour favoriser la fixation de la seconde bride en L.  Advantageously, the ring has a wavy shape which draws an alternation of hollow and bumps distributed around the axis of the shell, said bumps each forming a radial extra thickness designed to promote the attachment of the second L-shaped flange.
Aussi, le panneau acoustique s'étend longitudinalement en aval au- delà du plan de la seconde bride en L.  Also, the acoustic panel extends longitudinally downstream beyond the plane of the second L-shaped flange.
La conception du dispositif selon l'invention permet de ne pas perforer le panneau acoustique par des moyens de fixation, préservant ainsi toutes les performances d'absorption acoustique du panneau.  The design of the device according to the invention makes it possible not to perforate the acoustic panel by fixing means, thus preserving all the acoustic absorption performance of the panel.
De plus, le dispositif comporte un coin qui est interposé radialement entre la peau extérieure de la virole et le tronçon aval évasé de la couronne.  In addition, the device comprises a wedge which is interposed radially between the outer skin of the ferrule and the flared downstream portion of the crown.
Selon une autre caractéristique, les moyens de fixation comportent une pluralité de liens métalliques qui raccordent le tronçon aval évasé de la couronne sur l'embase de la seconde bride en L.  According to another characteristic, the fastening means comprise a plurality of metal links which connect the flared upstream portion of the ring to the base of the second L-shaped flange.
L'invention concerne également un procédé pour la fabrication d'un dispositif pour la fixation d'une extrémité aval d'une entrée d'air sur un carter de soufflante d'une nacelle de turboréacteur d'aéronef, selon l'une quelconque des revendications précédentes, caractérisé en ce que l'excroissance est réalisée venue de matière avec la peau extérieure de la virole.  The invention also relates to a method for manufacturing a device for fixing a downstream end of an air intake on a fan casing of an aircraft turbojet engine nacelle, according to any one of the preceding claims, characterized in that the protrusion is made integrally with the outer skin of the ferrule.
D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée qui suit pour la compréhension de laquelle on se reportera aux dessins annexés dans lesquels :  Other features and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:
- la figure 1 est une vue schématique en section longitudinale, qui illustre une nacelle de turboréacteur d'aéronef ;  FIG. 1 is a schematic view in longitudinal section, which illustrates an aircraft turbojet engine nacelle;
- la figure 2 est une vue schématique en section longitudinale, qui illustre un dispositif pour la fixation de la virole d'entrée d'air sur un carter de soufflante de la nacelle de la figure 1 , selon l'invention ;  - Figure 2 is a schematic longitudinal sectional view, which illustrates a device for fixing the air intake ring on a fan casing of the nacelle of Figure 1, according to the invention;
- la figure 3 est une vue de détail avec arrachement en perspective, qui illustre la première bride et la seconde bride du dispositif de la figure 2 ; - la figure 4 est une vue de détail avec arrachement en perspective, qui illustre la première bride et la seconde bride du dispositif de la figure 2 selon une variante de réalisation ; FIG. 3 is a detail view broken away in perspective, which illustrates the first flange and the second flange of the device of FIG. 2; - Figure 4 is a detail view broken away in perspective, which illustrates the first flange and the second flange of the device of Figure 2 according to an alternative embodiment;
- la figure 5 est une vue de détail avec arrachement en perspective, qui illustre la couronne de liaison de la seconde bride sur la virole du dispositif de la figure 2 ;  - Figure 5 is a detail view with tear in perspective, which illustrates the connecting ring of the second flange on the ferrule of the device of Figure 2;
- la figure 6 est une vue de détail en section transversale, qui illustre la couronne de liaison de la seconde bride sur la virole du dispositif de la figure 2.  - Figure 6 is a detailed cross-sectional view, which illustrates the connecting ring of the second flange on the ferrule of the device of Figure 2.
Pour clarifier la description et les revendications, on adoptera à titre non limitatif la terminologie longitudinal, vertical et transversal en référence au trièdre L, V, T indiqué aux figures, dont l'axe L est parallèle à l'axe A de la nacelle.  To clarify the description and the claims, we adopt without limitation the longitudinal, vertical and transverse terminology with reference to the trihedron L, V, T indicated in the figures, whose axis L is parallel to the axis A of the nacelle.
De plus, on utilisera à titre non limitatif les expressions « supérieur », « inférieur » en référence à la partie supérieure et à la partie inférieure respectivement de la figure 2, et le termes « intérieur » et « extérieur » en référence à l'intérieur de la nacelle et à l'extérieur de la nacelle respectivement.  In addition, the terms "upper" and "lower" will be used without limitation with reference to the upper part and the lower part respectively of FIG. 2, and the terms "inside" and "outside" in reference to FIG. inside of the nacelle and outside the nacelle respectively.
A noter également que dans la présente demande de brevet, les termes « amont » et «aval » doivent s'entendre par rapport à la circulation du flux d'air à l'intérieur de l'ensemble propulsif formé par la nacelle et le turboréacteur, c'est-à-dire de la gauche vers la droite selon la figure 1 .  Note also that in the present patent application, the terms "upstream" and "downstream" must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet engine. , that is from left to right according to FIG.
Pour les différentes variantes de réalisation, les mêmes références pourront être utilisées pour des éléments identiques ou assurant la même fonction, par souci de simplification de la description.  For the different embodiments, the same references may be used for identical elements or providing the same function, for the sake of simplification of the description.
On a représenté à la figure 1 une nacelle 10 de turboréacteur 12 qui présente une structure tubulaire et qui s'étend suivant un axe A longitudinal d'amont en aval suivant le sens d'écoulement du flux d'air, de la gauche vers la droite selon la figure 1 .  FIG. 1 shows a nacelle 10 of a turbojet engine 12 which has a tubular structure and which extends along a longitudinal axis A from upstream to downstream in the direction of flow of the airflow, from the left to the right according to Figure 1.
La nacelle 10 comprend une entrée d'air 14 agencée en amont du turboréacteur 12, une section médiane 16 destinée à entourer une soufflante 18 du turboréacteur 12, une section aval 20 destinée à entourer la chambre de combustion du turboréacteur 12 et intégrant éventuellement des moyens d'inversion de poussée (non représentés), et une tuyère d'éjection 22.  The nacelle 10 comprises an air inlet 14 arranged upstream of the turbojet engine 12, a median section 16 intended to surround a fan 18 of the turbojet engine 12, a downstream section 20 intended to surround the combustion chamber of the turbojet engine 12 and possibly including means thrust reverser (not shown), and an ejection nozzle 22.
L'entrée d'air 14 comprend notamment une lèvre 24 d'entrée annulaire formant bord d'attaque, et une structure tubulaire aval formant virole 28 acoustique sur laquelle est rapportée la lèvre 24 pour canaliser l'air vers les aubes de la soufflante 18. The air inlet 14 comprises in particular an annular inlet lip 24 forming a leading edge, and a downstream tubular structure forming a ferrule 28 acoustics on which is reported the lip 24 for channeling the air towards the vanes of the blower 18.
La virole 28 acoustique est prolongée longitudinalement par un carter 30 de soufflante pour guider le flux d'air.  The acoustic ferrule 28 is extended longitudinally by a fan casing 30 to guide the flow of air.
Comme on peut le voir à la figure 2, la virole 28 présente une forme annulaire d'axe A, qui s'étend axialement d'amont en aval suivant l'axe A longitudinal de la nacelle 10 et qui est délimitée radialement par une peau interne 32 et une peau externe 34 qui emprisonne un panneau acoustique 70 alvéolaire.  As can be seen in FIG. 2, the ferrule 28 has an annular shape of axis A, which extends axially from upstream to downstream along the longitudinal axis A of the nacelle 10 and which is delimited radially by a skin internal 32 and an outer skin 34 which traps a cellular acoustic panel 70.
La peau interne 32 est acoustiquement perméable et est par exemple constituée d'une peau perforée permettant aux ondes sonores de la traverser.  The inner skin 32 is acoustically permeable and is for example constituted by a perforated skin allowing the sound waves to pass through it.
A l'inverse, la peau externe est étanche et acoustiquement imperméable.  Conversely, the outer skin is waterproof and acoustically impermeable.
Aussi, le panneau acoustique 70 est de préférence un matériau alvéolaire maintenant à distance la peau interne 32 et la peau externe 34, le panneau acoustique 70 formant une cavité conçue pour absorber et amortir les ondes sonores.  Also, the acoustic panel 70 is preferably a cellular material keeping the inner skin 32 and the outer skin 34 at a distance, the acoustic panel 70 forming a cavity designed to absorb and dampen the sound waves.
La nacelle 10 est équipée d'un dispositif 36 pour la fixation de l'entrée d'air 14 sur le carter 30 de soufflante, plus particulièrement pour la fixation de la virole 28 acoustique sur le carter 30.  The nacelle 10 is equipped with a device 36 for fixing the air inlet 14 on the fan casing 30, more particularly for fixing the acoustic shell 28 on the casing 30.
A cet effet, le dispositif 36 de fixation comporte une première bride 38 métallique qui est fixée sur une extrémité amont du carter 30, et une seconde bride 40 métallique de forme en L qui est fixée sur une extrémité aval de la virole 28.  For this purpose, the fixing device 36 comprises a first metal flange 38 which is fixed on an upstream end of the casing 30, and a second L-shaped metal flange 40 which is fixed on a downstream end of the ferrule 28.
La première bride 38 présente une embase 42 de forme annulaire qui s'étend globalement axialement suivant l'axe A longitudinal de la nacelle 10 et qui est fixée sur le carter 30 par un moyen de liaison mécanique (non représenté) comme un ensemble de vis et d'écrous par exemple, ou par tout autre moyen de fixation.  The first flange 38 has an annular base 42 extending generally axially along the longitudinal axis A of the nacelle 10 and which is fixed to the casing 30 by a mechanical connection means (not shown) as a set of screws. and nuts for example, or by any other means of attachment.
De plus, la première bride 38 présente une collerette 44 annulaire qui fait saillie radialement vers l'extérieur depuis l'embase 42 et qui délimite une première face de bridage 46 radiale agencée en regard de la seconde bride 40. De même, la seconde bride 40 présente une embase 48 de forme annulaire qui s'étend globalement axialement suivant l'axe A longitudinal de la nacelle 10 et une collerette 50 annulaire. In addition, the first flange 38 has an annular collar 44 projecting radially outwardly from the base 42 and defining a first radial clamping face 46 arranged opposite the second flange 40. Similarly, the second flange 40 has an annular base 48 which extends generally axially along the longitudinal axis A of the nacelle 10 and an annular flange 50.
La collerette 50 de la seconde bride 40 fait saillie radialement vers l'extérieur depuis l'embase 48 associée, la collerette 50 délimitant une seconde face de bridage 52 radiale prévue pour coopérer avec la première face de bridage 46 complémentaire de la première bride 38.  The flange 50 of the second flange 40 projects radially outwardly from the associated base 48, the flange 50 delimiting a second radial flange face 52 intended to cooperate with the first flange face 46 complementary to the first flange 38.
Dans ce but, la seconde face de bridage 52 et la première face de bridage 46 sont accolées suivant un plan P radial de bridage, et elles délimitent chacune une série de trous pour le passage de moyen de fixation, comme un ensemble de vis et d'écrous 54 par exemple, ou tout autre moyen de fixation.  For this purpose, the second clamping face 52 and the first clamping face 46 are contiguous along a radial clamping plane P, and they each delimit a series of holes for the passage of fastening means, such as a set of screws and bolts. nuts 54 for example, or any other means of attachment.
De préférence, la seconde bride 40 est réalisée en alliage métallique, et préférentiellement en alliage d'aluminium ou de titane.  Preferably, the second flange 40 is made of metal alloy, and preferably of aluminum alloy or titanium.
Ces alliages présentent des résistances et des allongements avant rupture élevés qui sont particulièrement adaptés pour la réalisation de ce type de bride qui doit supporter des déformations importantes imposées par le carter 30 dans les cas extrêmes de rupture d'une aube de la soufflante.  These alloys have high strengths and elongations before rupture which are particularly suitable for producing this type of flange which must withstand significant deformations imposed by the casing 30 in extreme cases of failure of a blade of the blower.
Selon une variante de réalisation, la seconde bride 40 peut être réalisée en composites parmi des technologies de thermocompression de fibres discontinues et continues, ou de moulage RTM de textures fibreuses.  According to an alternative embodiment, the second flange 40 may be made of composites among discontinuous and continuous fiber thermocompression technologies, or RTM molding of fibrous textures.
Les fibres sont choisies préférentiellement parmi les fibres de carbone, fibres de verre, et les matrices parmi les polymères époxydes thermodurcissables et les thermoplastiques de la famille des Polyaryletherketone.  The fibers are preferably chosen from carbon fibers, glass fibers, and matrices from thermosetting epoxy polymers and thermoplastics from the Polyaryletherketone family.
Aussi, pour réduire les défauts de planéité au droit du plan P de bridage, la collerette 50 de la seconde bride 40 et la collerette 44 de la première bride 38 peuvent être usinées.  Also, to reduce flatness defects to the right plane P clamping, the flange 50 of the second flange 40 and the flange 44 of the first flange 38 can be machined.
Selon un exemple de réalisation préféré représenté à la figure 3, la seconde bride 40 est réalisée en une pluralité de parties 55 en forme de secteurs, qui sont indépendantes et identiques et qui sont agencées en anneau autour de l'axe de la virole 28.  According to a preferred embodiment shown in FIG. 3, the second flange 40 is made of a plurality of sector-shaped portions 55 which are independent and identical and which are arranged in a ring around the axis of the ferrule 28.
Selon l'exemple représenté à la figure 3, chaque partie 55 délimite trois trous qui sont répartis de façon régulière autour de l'axe A et qui sont prévus pour le passage des moyens de fixation sur la première bride 38.  According to the example shown in FIG. 3, each part 55 delimits three holes which are uniformly distributed around the axis A and which are provided for the passage of the fastening means on the first flange 38.
Selon un autre exemple de réalisation représenté à la figure 4, la seconde bride 40 est réalisée d'un seul tenant de la forme d'un anneau. De plus, à titre non limitatif, la seconde bride 40 peut être réalisée en une pluralité de parties qui sont reliées mécaniquement entre elles par des moyens de liaisons rapportés. According to another exemplary embodiment shown in FIG. 4, the second flange 40 is made in one piece in the form of a ring. In addition, without limitation, the second flange 40 may be made of a plurality of parts which are mechanically interconnected by means of reported links.
Selon un autre aspect de l'invention, le dispositif 36 comporte une excroissance formant couronne 56 annulaire qui s'étend autour de l'axe A de la nacelle 10 et qui s'étend longitudinalement depuis un tronçon amont 58 solidaire de la peau externe 34 de la virole 28, jusqu'à un tronçon aval 60 qui est adapté pour être fixé sur l'embase 48 de la seconde bride 40 en L par des moyens de fixations 61 .  According to another aspect of the invention, the device 36 comprises an annular crown protrusion 56 which extends around the axis A of the nacelle 10 and which extends longitudinally from an upstream section 58 integral with the outer skin 34 from the shell 28, to a downstream section 60 which is adapted to be fixed on the base 48 of the second L-shaped flange 40 by means of fasteners 61.
On notera que la couronne 56 est indépendante de la seconde bride 40.  Note that the ring 56 is independent of the second flange 40.
Le tronçon aval 60 de la couronne 56 présente une forme évasée globalement tronconique de section radiale croissante suivant une direction axiale d'amont en aval, cette forme évasée permettant au tronçon aval 60 de délimiter un espace 62 radial, ou cavité, avec la peau externe 34 de la virole 28.  The downstream section 60 of the ring 56 has a globally frustoconical flared shape of increasing radial section in an axial direction from upstream to downstream, this flared shape allowing the downstream section 60 to delimit a radial space 62, or cavity, with the outer skin 34 of ferrule 28.
De plus, la couronne 56 est réalisée en matériau composite.  In addition, the ring 56 is made of composite material.
Selon un exemple de réalisation préféré, la couronne 56 est réalisée en une succession de peaux de tissu qui sont pré-imprégnées d'un liant, comme de la résine.  According to a preferred embodiment, the ring 56 is made of a succession of fabric skins which are pre-impregnated with a binder, such as resin.
Selon un exemple de réalisation préféré, la couronne 56 est réalisée en même temps que la peau externe 34 de la virole 28, par un empilement de couches de tissu et ou de fibres pouvant faire partiellement partie de la constitution de la peau externe 34.  According to a preferred embodiment, the ring 56 is made at the same time as the outer skin 34 of the collar 28, by a stack of layers of fabric and or fibers that can be part of the constitution of the outer skin 34.
Les couches de tissus et/ou de fibres sont imprégnées de résine et solidifiées par polymérisation.  The layers of fabrics and / or fibers are impregnated with resin and solidified by polymerization.
Aussi, les peaux de la couronne 56 peuvent être réalisées par procédé de placement de fibres pré-imprégnées de liant ou drapage de nappes pré-imprégnées de liant.  Also, the skins of the crown 56 can be made by placing process pre-impregnated fibers of binder or draping pre-impregnated sheets of binder.
La couronne 56 peut aussi être réalisée par moulage par injection, par exemple par un procédé d'injection de résine dans une préforme fibreuse agencée dans un moule, ce type de procédé est connu sous l'acronyme anglais RTM pour « resin transfer molding ».  The ring 56 can also be made by injection molding, for example by a resin injection process in a fiber preform arranged in a mold, this type of process is known by the acronym RTM for "resin transfer molding".
A la suite de sa fabrication, la couronne 56 peut être collée ou co- cuite avec les couches de fibres de la peau externe 34 de la virole 28. A titre non limitatif, la couronne peut être réalisée par tout autre type de procédé de fabrication de pièce en matériau composite. As a result of its manufacture, the crown 56 can be glued or co-fired with the fiber layers of the outer skin 34 of the ferrule 28. By way of non-limiting example, the ring may be made by any other type of process for manufacturing a part made of composite material.
Pour constituer l'espace 62 radial formé entre le tronçon aval 60 de la couronne 56 et la peau externe 34 de la virole 28, un élément d'outillage extractible (non représenté) peut être inséré pour le drapage et la polymérisation de l'ensemble.  To constitute the radial space 62 formed between the downstream portion 60 of the ring 56 and the outer skin 34 of the shell 28, an extractable tooling element (not shown) can be inserted for draping and polymerization of the assembly. .
Le tronçon aval 60 de la couronne 56, qui est déporté radialement de la virole 28 acoustique, présente l'avantage de ne pas altérer la forme géométrique de l'ensemble acoustique formé par la peau externe 34, la peau interne 32 et le panneau acoustique 70 de la virole 28 qui s'étend alors axialement en aval de façon continue au-delà de la couronne 56 et peut s'étendre jusqu'au plan P de bridage, et même éventuellement au-delà à l'intérieur du carter de soufflante 30.  The downstream portion 60 of the ring 56, which is radially offset from the acoustic shell 28, has the advantage of not altering the geometric shape of the acoustic assembly formed by the outer skin 34, the inner skin 32 and the acoustic panel. 70 of the shell 28 which then extends axially continuously downstream continuously beyond the ring 56 and can extend up to the plane P of clamping, and possibly even beyond inside the fan casing 30.
Selon une variante de réalisation de l'invention, le dispositif 36 comprend un coin 64 de section triangulaire, représenté à la figure 4, qui est interposé radialement entre la peau externe 34 de la virole 28 et le tronçon aval 60 évase de la couronne 56.  According to an alternative embodiment of the invention, the device 36 comprises a wedge 64 of triangular section, shown in Figure 4, which is interposed radially between the outer skin 34 of the ferrule 28 and the downstream portion 60 flares from the ring 56 .
Le coin 64 est par exemple réalisé en matériau composite et permet notamment d'éviter ou de limiter la déformation du tronçon aval 60 de la couronne 56, le coin 64 pouvant présenter la forme d'un anneau fermé ou ouvert ou formés de plusieurs secteurs angulaires.  The wedge 64 is for example made of composite material and in particular makes it possible to avoid or limit the deformation of the downstream section 60 of the ring 56, the wedge 64 possibly having the shape of a closed or open ring or formed of several angular sectors. .
En référence à la figure 2, les moyens de fixation 61 du tronçon aval 60 de la couronne 56 sur l'embase 48 de la seconde bride 40 comportent une pluralité de liens métalliques, comme un ensemble de vis et d'écrous et/ou un ensemble de rivets par exemple.  With reference to FIG. 2, the fixing means 61 of the downstream section 60 of the ring 56 on the base 48 of the second flange 40 comprise a plurality of metal links, such as a set of screws and nuts and / or a set of rivets for example.
Ces moyens de fixation ne sont pas représentés aux figures 3 à 5. These fastening means are not shown in FIGS. 3 to 5.
L'embase 48 de la seconde bride 40 délimite une série de trous 65 pour le passage des moyens de fixation 61 . The base 48 of the second flange 40 delimits a series of holes 65 for the passage of the fastening means 61.
Pour assurer une fixation fiable de la couronne 56 sur la seconde bride 40, les trous 65 sont répartis sur deux rangés, en quinconce comme illustré à la figure 4 ou en vis-à-vis comme illustré sur la figure 3.  To ensure reliable attachment of the ring 56 on the second flange 40, the holes 65 are distributed in two rows, staggered as shown in Figure 4 or vis-à-vis as shown in Figure 3.
En outre, le tronçon aval 60 de la couronne 56 peut être usiné si nécessaire pour favoriser la coopération entre le tronçon aval 60 de la couronne 56 et l'embase 48 de la seconde bride 40 associée.  In addition, the downstream portion 60 of the ring 56 can be machined if necessary to promote cooperation between the downstream section 60 of the ring 56 and the base 48 of the second flange 40 associated.
Selon un exemple de réalisation préféré de l'invention illustré aux figures 5 et 6, le tronçon aval 60 de la couronne 56 présente une forme ondulée qui dessine une alternance de creux 66 et de bosses 68 réparties autour de l'axe A de la virole 28. According to a preferred embodiment of the invention illustrated in FIGS. 5 and 6, the downstream section 60 of the ring 56 has a shape corrugated which draws an alternation of hollow 66 and bumps 68 distributed around the axis A of the ferrule 28.
Les bosses 68 forment chacune une surépaisseur radiale conçue pour favoriser la fixation de la couronne 56 sur la seconde bride 40 par les moyens de fixation 61 , comme on peut le voir à la figure 6.  The bumps 68 each form a radial excess thickness designed to promote the fixing of the ring 56 on the second flange 40 by the fastening means 61, as can be seen in FIG.
Enfin, en référence à la figure 1 , le panneau acoustique 70 s'étend longitudinalement au-delà du plan P de la seconde bride 40 en L.  Finally, with reference to FIG. 1, the acoustic panel 70 extends longitudinally beyond the plane P of the second flange 40 in L.
A titre non limitatif, le panneau acoustique 70 peut s'étendre seulement jusqu'au plan P de bridage, le carter 30 comportant alors un panneau acoustique supplémentaire agencé dans le prolongement.  By way of non-limiting example, the acoustic panel 70 may extend only to the clamping plane P, the casing 30 then comprising an additional acoustic panel arranged in the extension.
Avantageusement, le dispositif 36 de fixation selon l'invention est léger, de conception simple, robuste et fiable, et il permet de relier la virole 28 sur le carter 30 sans perforer le panneau acoustique 70, préservant ainsi toutes ses capacités d'absorption du bruit.  Advantageously, the fixing device 36 according to the invention is lightweight, simple in design, robust and reliable, and it enables the ferrule 28 to be connected to the casing 30 without perforating the acoustic panel 70, thus preserving all its absorption capacities of the noise.
L'invention concerne également un procédé pour la fabrication du dispositif 36 décrit précédemment.  The invention also relates to a method for manufacturing the device 36 described above.
Selon ce procédé, l'excroissance 56 est réalisée venue de matière avec la peau externe 34 de la virole 28.  According to this method, the protrusion 56 is made integrally with the outer skin 34 of the ferrule 28.
L'expression « réalisée venue de matière » signifie que l'excraissance 56 est réalisée simultanément avec la peau externe 34 de la virole 28, comme décrit précédemment.  The expression "made from material" means that the excrescence 56 is performed simultaneously with the outer skin 34 of the ferrule 28, as previously described.

Claims

REVENDICATIONS
1 . Dispositif (36) pour la fixation d'une extrémité aval d'une entrée d'air (14) sur un carter (30) de soufflante (18) d'une nacelle (10) de turboréacteur (12) d'aéronef, l'entrée d'air (14) comportant une virole (28) acoustique présentant une forme annulaire qui s'étend axialement d'amont en aval suivant un axe (A) longitudinal et qui est délimitée radialement par une peau interne (32) et une peau externe (34) emprisonnant un panneau acoustique (70), le dispositif (36) comportant une première bride (38) qui est solidaire du carter (30), et une seconde bride (40) de forme en L qui comprend une embase (48) prévue pour être reliée à la virole (28), et une collerette (50) prévue pour être reliée à la première bride (38), caractérisé en ce qu'il comporte une excroissance (56) qui s'étend longitudinalement depuis un tronçon amont (58) solidaire de la peau externe (34) de la virole (28), jusqu'à un tronçon aval (60) évasé qui délimite un espace (62) radial avec la virole (28) et qui est adapté pour être fixé sur l'embase (48) de la seconde bride (40) en L par des moyens de fixations (61 ) sans altérer la peau externe (34) de la virole (28). 1. Device (36) for fixing a downstream end of an air inlet (14) on a fan casing (30) (18) of a nacelle (10) of an aircraft turbojet (12), l air inlet (14) having an acoustic ferrule (28) having an annular shape which extends axially from upstream to downstream along a longitudinal axis (A) and which is delimited radially by an inner skin (32) and a outer skin (34) enclosing an acoustic panel (70), the device (36) having a first flange (38) which is integral with the housing (30), and a second L-shaped flange (40) which comprises a base ( 48) adapted to be connected to the ferrule (28), and a flange (50) adapted to be connected to the first flange (38), characterized in that it comprises a protuberance (56) which extends longitudinally from a upstream section (58) secured to the outer skin (34) of the ferrule (28), to a flared downstream section (60) which delimits a space (62) radial with the v irole (28) and which is adapted to be fixed on the base (48) of the second flange (40) L by means of fasteners (61) without altering the outer skin (34) of the ferrule (28).
2. Dispositif (36) selon la revendication 1 , caractérisé en ce que l'excroissance (56) présente la forme d'une couronne annulaire qui s'étend autour de l'axe (A) de la virole (28).  2. Device (36) according to claim 1, characterized in that the protrusion (56) has the shape of an annular ring which extends around the axis (A) of the shell (28).
3. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que le panneau acoustique (70) de la virole (28) s'étend longitudinalement de façon continue d'amont en aval au moins jusqu'au tronçon aval (60) de l'excroissance (56).  3. Device (36) according to any one of the preceding claims, characterized in that the acoustic panel (70) of the sleeve (28) extends longitudinally continuously from upstream to downstream at least to the downstream section. (60) of the protrusion (56).
4. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que la seconde bride (40) est réalisée en matériau métallique.  4. Device (36) according to any one of the preceding claims, characterized in that the second flange (40) is made of metallic material.
5. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que la seconde bride (40) est réalisée en une pluralité de parties (55) indépendantes qui sont agencées en anneau autour de l'axe (A) de la virole (28).  5. Device (36) according to any one of the preceding claims, characterized in that the second flange (40) is made of a plurality of independent portions (55) which are arranged in a ring around the axis (A) of the ferrule (28).
6. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que l'excroissance (56) est réalisée en matériau composite. 6. Device (36) according to any one of the preceding claims, characterized in that the protrusion (56) is made of composite material.
7. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que l'excroissance (56) présente une forme ondulée qui dessine une alternance de creux (66) et de bosses (68) réparties autour de l'axe (A) de la virole (28), lesdites bosses (68) formant chacune une surépaisseur radiale conçue pour favoriser la fixation de la seconde bride (40) en L sur l'excroissance (56). 7. Device (36) according to any one of the preceding claims, characterized in that the protrusion (56) has an undulating shape which draws an alternation of recesses (66) and bumps (68) distributed around the axis (A) the ferrule (28), said bosses (68) each forming a radial extra thickness designed to promote the attachment of the second flange (40) L on the protrusion (56).
8. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que le panneau acoustique (70) s'étend longitudinalement en aval au-delà du plan de la seconde bride (40) en L.  8. Device (36) according to any one of the preceding claims, characterized in that the acoustic panel (70) extends longitudinally downstream beyond the plane of the second flange (40) L.
9. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte un coin (64) qui est interposé radialement entre la peau externe (34) de la virole (28) et le tronçon aval (60) évasé de l'excroissance (56).  9. Device (36) according to any one of the preceding claims, characterized in that it comprises a wedge (64) which is interposed radially between the outer skin (34) of the shell (28) and the downstream section (60 ) flared out of the outgrowth (56).
10. Dispositif (36) selon l'une quelconque des revendications précédentes, caractérisé en ce que les moyens de fixation (61 ) comportent une pluralité de liens métalliques qui raccordent le tronçon aval (60) évasé de l'excroissance (56) sur l'embase (48) de la seconde bride (40).  10. Device (36) according to any one of the preceding claims, characterized in that the fastening means (61) comprise a plurality of metal links which connect the downstream section (60) flared out of the protrusion (56) on the base (48) of the second flange (40).
1 1 . Procédé pour la fabrication d'un dispositif (36) pour la fixation d'une extrémité aval d'une entrée d'air (14) sur un carter (30) de soufflante (18) d'une nacelle (10) de turboréacteur (12) d'aéronef, selon l'une quelconque des revendications précédentes, caractérisé en ce que l'excroissance (56) est réalisée venue de matière avec la peau externe (34) de la virole (28).  1 1. Method for manufacturing a device (36) for fixing a downstream end of an air inlet (14) on a fan casing (30) (18) of a turbojet engine nacelle (10) ( 12) of aircraft, according to any one of the preceding claims, characterized in that the protrusion (56) is made integral with the outer skin (34) of the shell (28).
EP15788468.5A 2014-09-18 2015-09-17 Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle Withdrawn EP3194749A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1458829A FR3026134B1 (en) 2014-09-18 2014-09-18 DEVICE FOR FIXING AN AIR INLET ON A BLOWER HOUSING OF AN AIRCRAFT TURBOJET AIRCRAFT
PCT/FR2015/052495 WO2016042271A1 (en) 2014-09-18 2015-09-17 Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle

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EP3194749A1 true EP3194749A1 (en) 2017-07-26

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US (1) US10415472B2 (en)
EP (1) EP3194749A1 (en)
CN (1) CN106715267A (en)
FR (1) FR3026134B1 (en)
WO (1) WO2016042271A1 (en)

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CN106715267A (en) 2017-05-24
FR3026134B1 (en) 2019-07-19
US20170184023A1 (en) 2017-06-29
WO2016042271A1 (en) 2016-03-24
FR3026134A1 (en) 2016-03-25
US10415472B2 (en) 2019-09-17

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