Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B32—LAYERED PRODUCTS
  • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
  • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
  • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • 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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
  • B64D33/06—Silencing exhaust or propulsion jets
• • 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
  • 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
  • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
• • 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
  • F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
• • 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
• • G—PHYSICS
  • G10—MUSICAL INSTRUMENTS; ACOUSTICS
  • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
  • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
  • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
  • G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—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
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2260/00—Function
  • F05B2260/30—Retaining components in desired mutual position
  • F05B2260/301—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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/36—Application in turbines specially adapted for the fan of 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
  • F05D2250/00—Geometry
  • F05D2250/20—Three-dimensional
  • F05D2250/28—Three-dimensional patterned
  • F05D2250/283—Three-dimensional patterned honeycomb
• • 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 present invention relates to an acoustic panel of the cellular panel type, in particular for a turbojet engine nacelle structure, said acoustic panel being equipped with attachment means.
• This panel is more particularly intended to equip a turbojet nacelle and more particularly a blower housing of the turbojet engine.
• aircraft turbojets are generators of significant noise pollution. There is a strong demand to reduce this pollution, especially as the turbojets used become more and more powerful.
• the design of the nacelle surrounding a turbojet contributes to a large extent to the reduction of this noise pollution.
• nacelles are equipped with acoustic panels to reduce the noise due to the circulation of air flows through the turbojet engine and vibrations of the structures of the nacelle.
• acoustic panels are generally arranged along a flow passage of the air flows generated by the turbojet engine, from the air inlet upstream to its outlet downstream.
• Acoustic panels are sandwich structures well known for absorbing these noises. These panels usually comprise one or more layers of honeycomb core structures (commonly called “honeycomb” structure). These layers can then be coated on their so-called outer face, that is to say the furthest away from the aerodynamic flow, of a skin impermeable to air, called “full”, and on top of it in this way. e, that is to say the most aerodynamic flow, a perforated skin permeable to air, called “acoustic”.
• the honeycomb core structure is made from joined alveolar unit (s) having generally hexagonal or elliptical shape cells.
• LDOF linear degree of freedom panels
• 2DOF double degree of freedom
• the present invention is not limited to a particular acoustic panel structure and will be compatible with these different structures.
• These screws can either pass through the panel at the level of the honeycomb core which is then locally reinforced, in particular by adding resin, a solid reinforcement or an insert, or pass through the panel at a area called back to the skin where the honeycomb is locally removed.
• Another possibility is to glue the panel or rivet on its full outer skin, as described for example in EP 1 020 845, but in this case, the panels are not removable. Furthermore, in the case of EP 1 020 845, it is found that the rivets always penetrate inside the panel, which always reduces the effective acoustic surface.
• the present invention aims to overcome these disadvantages and to provide a fastening system for removing panels without loss of acoustic surface.
• the present invention thus proposes an alternative solution answering these drawbacks and consists for this purpose in an acoustic panel comprising at least one cellular core disposed between at least one internal skin, and an outer skin, characterized in that said outer skin integrates at least fastening means adapted to cooperate in a manner removable with a complementary fastening means associated with a connecting structure.
• fasteners By integrating fastening means directly into the outer skin, no cell of the core is closed or destroyed by the fastening means. The acoustic performances are thus preserved.
• the fasteners being mounted on the back of the panel, they allow great adaptability to the wall along which the panel must be fixed. This method of attachment also respects the space allocated to the panel.
• fastening means are at least partially embedded or incorporated in the outer skin, and in particular inserted into the folds in the case of a skin made of composite material.
• the fastening means is a screw and the complementary fastening means is a nut or vice versa.
• the fastening means and the complementary fastening means form a quarter-turn fast fastener.
• the fastening means is a nut and the complementary fastening means is a screw
• the fixing means is integrated into the outer skin by molding and in particular during a molding step of at least a portion of the panel.
• the fastening means is integrated into the outer skin by bonding or welding on the outer skin.
• the fixing means is fixed in the outer skin by riveting.
• the fastening means is integrated into the outer skin via a base.
• the acoustic panel comprises a plurality of fixing means, at least a portion of which is oriented in a direction substantially parallel to a direction of installation of the panel.
• the outer skin of the acoustic panel has a curved surface.
• the integration of the fastening means in the outer skin has swiveling properties around at least one pivot axis.
• FIG. 1 is a schematic longitudinal sectional view of a nacel the tu rboréactor whose inner air flow channel is covered with acoustic panels according to the invention.
• FIG. 2 is a general schematic representation of an acoustic panel as used in the nacelles.
• FIGS. 3 and 4 are partial views in longitudinal section of a rear skin of a first embodiment of an acoustic panel according to the invention.
• FIG. 5 is a partial longitudinal sectional view of a rear skin of a third embodiment of an acoustic panel according to the invention.
• FIG. 6 to 8 illustrate the case of a curved acoustic panel and comprising suitable fasteners according to the invention.
• FIG. 1 is a diagrammatic representation in section of a nacelle 1 of a turbojet engine 2.
• This nacelle 1 has a substantially tubular external structure surrounding the turbojet engine 2 and defining around the latter a vein 3 for circulating air flow.
• FIG. 1 also schematically shows propagation paths of the sound waves (hatched arrow zones), in particular generated by vanes of a fan 4 of the turbojet engine 2.
• the nacelle 1 is equipped, in particular from an air inlet and along the air circulation duct 3, with acoustic panels 5 covering one or more internal walls of the nacelle 1.
• FIG. 2 A typical acoustic panel structure 5 is shown in FIG. 2.
• Such an acoustic panel 5 typically comprises a core 51 made of honeycomb between an inner skin 52, perforated and intended to be oriented towards the inside of the nacelle 1. in order to receive the sound waves to be absorbed, and a solid external skin 53 intended to allow the acoustic panel 5 to be fixed.
• such an acoustic panel 5 is able to be attached to the nacelle by means of fasteners integrated into the outer skin 53.
• Figures 3 to 5 show different embodiments of such integrated fastening means.
• FIG. 3 shows a first embodiment of a fastening means fitted to an acoustic panel 5.
• This fixing means is in the form of a screw 61 comprising a threaded rod 61 1 extending from a plate 612 towards outside the panel.
• the screw 61 is integrated with the outer skin 53 of the acoustic panel 5 by molding said outer skin 53 around the plate 612.
• the plate 612 will be arranged between one or more internal plies 53b of the outer skin 53 and one or more outer plies 53a of the outer skin 53.
• the threaded rod 61 1 is intended to pass through a corresponding orifice 7 formed in a wall 8 to which the acoustic panel 5 must be attached and to receive a corresponding nut 9 so as to secure the fastener while allowing its disassembly.
• FIG. 5 shows a second embodiment of the screw 61 fitted to the rear skin 53 of the acoustic panel 5.
• the screw 61 is fixed in the rear skin by placing rivets 10 through the plate 612.
• Figures 6 to 8 are interested in the case of a curved acoustic panel 500.
• the fastening means in this case screws 61, will advantageously be oriented according to a unidirectional reflection of the panel 500 and not systematically in a direction normal to the panel. 500.
• the screws 61 can be fixedly mounted in this direction or with swiveling properties making them orientable.
• 61 is mounted movably within a fixed portion 90 fixed in the rear skin 53, in particular by molding between folds 53a, 53b of the rear skin 53, having a substantially spherical bearing surface.
• FIG. 8 illustrates the step of attaching the acoustic panel to the wall of the nacelle 1.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Physics & Mathematics (AREA)
• Acoustics & Sound (AREA)
• Multimedia (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Connection Of Plates (AREA)
• Soundproofing, Sound Blocking, And Sound Damping (AREA)
• Vehicle Interior And Exterior Ornaments, Soundproofing, And Insulation (AREA)
• Building Environments (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=43735942

Family Applications (1)

Country Status (8)

Families Citing this family (9)

Family Cites Families (16)

• 2010
  • 2010-07-27 FR FR1056136A patent/FR2963469B1/fr active Active
• 2011
  • 2011-07-07 WO PCT/FR2011/051628 patent/WO2012022869A2/fr active Application Filing
  • 2011-07-07 CN CN201180036251.XA patent/CN103003872B/zh not_active Expired - Fee Related
  • 2011-07-07 EP EP11741643.8A patent/EP2599078A2/de not_active Withdrawn
  • 2011-07-07 BR BR112013000154A patent/BR112013000154A2/pt not_active IP Right Cessation
  • 2011-07-07 CA CA2803746A patent/CA2803746A1/fr not_active Abandoned
  • 2011-07-07 RU RU2013107955/06A patent/RU2579785C2/ru not_active IP Right Cessation
• 2013
  • 2013-01-24 US US13/749,215 patent/US8579078B2/en not_active Expired - Fee Related

Non-Patent Citations (1)

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