WO2010103302A1 - Organe d'atténuation acoustique d'aéronef et procédé de formation dudit organe - Google Patents

Organe d'atténuation acoustique d'aéronef et procédé de formation dudit organe Download PDF

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Publication number
WO2010103302A1
WO2010103302A1 PCT/GB2010/050365 GB2010050365W WO2010103302A1 WO 2010103302 A1 WO2010103302 A1 WO 2010103302A1 GB 2010050365 W GB2010050365 W GB 2010050365W WO 2010103302 A1 WO2010103302 A1 WO 2010103302A1
Authority
WO
WIPO (PCT)
Prior art keywords
cell
cells
attenuation
less
depth
Prior art date
Application number
PCT/GB2010/050365
Other languages
English (en)
Inventor
Julian Rishton
Ian Taylor
Original Assignee
Aircelle Limited
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 Aircelle Limited filed Critical Aircelle Limited
Priority to GB1115385A priority Critical patent/GB2480208A/en
Priority to CA2754782A priority patent/CA2754782A1/fr
Priority to CN2010800111466A priority patent/CN102349101A/zh
Priority to EP10707649A priority patent/EP2406786A1/fr
Publication of WO2010103302A1 publication Critical patent/WO2010103302A1/fr

Links

Classifications

    • 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
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/40—Sound or heat insulation, e.g. using insulation blankets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/26—Ground or aircraft-carrier-deck installations for reducing engine or jet noise; Protecting airports from jet erosion
    • 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
    • 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
    • F02C7/24—Heat or noise insulation
    • 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
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • 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
    • 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

Definitions

  • the present invention relates to an aircraft acoustic attenuation member, an aircraft acoustic attenuation assembly, an aircraft engine core fairing and a method of forming an aircraft attenuation member.
  • Noise emitting from aircraft is a problem.
  • the noise is at a peak during take off when engines are at full thrust.
  • core fairings are located around the engine with sound attenuation material being included.
  • An inner thermal and fire protection layer surrounds the engine.
  • a middle layer surrounds the inner layer.
  • the middle layer is formed by welding adjacent faces of metallic, such as aluminium, or paper based sheets at spaced locations. These locations subsequently form the contacting faces of the honeycomb. The moulded aluminium sheet is then pulled to expand to form the honeycomb.
  • edges of the inner surface of the honeycomb are adhered to an inner layer.
  • the edges of the outer layer are adhered to a 4-ply perforated outer layer.
  • honeycomb The fabrication of the honeycomb and the attachment of the honeycomb to adjacent layers is a complicated and time consuming method.
  • supports for the engine that come from the fan case have to pass through the honeycomb layer.
  • bolts have to pass through the layer.
  • the honeycomb is extremely weak in the direction between the walls that form the honeycomb. Thus when the walls are disturbed by the supports and bolts, foaming adhesive is used to fill relevant cells of the honeycomb. Alternate strengthening method may also be used.
  • the use of the resin is time consuming as the resin is not an easy material to work with.
  • there is an associated weight penalty because cells are filled that are not needed to be filled to ensure that sufficient strength is present in the required areas and to ensure that parts passing at an angle through the layer have adequate support from the cells that they pass through.
  • Another problem with the aluminium honeycomb is that only a single depth is afforded and there are locations where greater depths are required for optimum sound attenuation.
  • Figure 1 is a perspective view of a core fairing
  • Figure 2 is a section of part of the core fairing in a direction around the fairing
  • Figure 3 is a plan view of the cellular structure alone used with the fairing
  • Figure 4 is a plan view of a cellular structure that has yet to be curved
  • Figure 5 is a side cross sectional view of a cellular structure affording an opening for a support for the engines to run through;
  • Figure 6 is a view showing a fastener extending through the fairing.
  • Figure 7 is a view showing an attachment at the forward edge of the fairing.
  • the core fairing 10 is made up of six or more separate sections 12, 14, 16, 18, 20 and 22. Each segment has sound attenuation. Each segment is connected to adjacent segments or is able to move relative to an adjacent segment. There may be three fairings, for instance, located along the length of the engine.
  • the fairing section is formed with the conventional inner thermal protector and fire barrier 24, a middle layer 26 comprising an injection moulded cellular structure that includes an inwardly facing wall 28 with square cells 30 extending outwardly from the wall 28, and a conventional perforated outer skin 32.
  • the inner layer 24 may be attached to the wall 28 of the middle layer by mechanical fixings or by bonding.
  • the outer layer may be attached to the free ends of the walls defining the cells by mechanical fixings or bonding.
  • the middle layer is able to be injection moulded from plastics such as PEEK, PBI (polybenzimdazole) or other injection moulded material as the thermal barrier inner layer shields the middle layer from most of the heat such that the maximum temperature that the middle layer will experience is 18O 0 C.
  • the thickness of the walls at the cells 30 is 1 mm and the distance between opposed walls of the cells is 18mm.
  • the height of the cells is 50mm. However, it will be appreciated that any of these dimensions can be varied.
  • the wall 28 may be formed on the outer wall with the open ends of the cells facing inwardly.
  • the inner walls of the cells may be attached to the barrier layer 24.
  • the wall 28 may be formed with perforations in which case the skin 32 may not be required.
  • middle layer 26 has been described as having a wall 28 in any of the embodiments referred to herein, it is possible that the wall may extend over part of the extent of the layer or that the wall 28 may be omitted.
  • FIG 3 shows the junction of four of the walls that define the cells herein formed with an opening 34.
  • the walls extending from that opening are thickened over part of their extent as indicated by arrow 36 to provide reinforcement.
  • the inner wall 28 is thickened as shown by arrow 38. Accordingly, a fastener such as a bolt can be passed through the opening 34 and the inner and outer walls with the middle layer being designed to provide the optimum support.
  • a fastener such as a bolt can be passed through the opening 34 and the inner and outer walls with the middle layer being designed to provide the optimum support.
  • the middle layer is injection moulded there is no need to modify a uniformly formed honeycomb layer by adding resin and then drilling through the resin, for instance in order to accommodate a bolt.
  • the cells are shown as being of square cross section. However, the cells may have any cross section.
  • the cells may be circular cells 40, rectangular cells 42, hexagonal cells 43, or there may be a combination of any such formed cells. In this way the sound absorption features of the middle layer may be optimised.
  • the moulding may be a substantially planar moulding which may subsequently be made into a curved member or an arc.
  • the moulding may be in the form of a curve or arc.
  • Figure 5 is a cross section of the middle layer where a pipe has to cross the middle layer at an angle.
  • the layer can be formed with a channel 44 with the walls of the channel being thicker than the walls of the cells. Again with the moulded inner layer there is no need to fabricate such a channel from the conventional honeycomb structure such as by filling a certain number of cells with the foamed glue, waiting for the glue to dry and then drilling the channel.
  • the depth of the middle section is shown as constant it is possible for the depth to vary. For instance, some cells may have a greater depth than others.
  • the depth change may be a step change. Alternatively, the change may be in the form of a straight line or a curved line in the direction of depth change.
  • Figure 6 shows a bracket 46 that is attached to the fairing.
  • the fairing has a hollow insert 48 pushed through with a flange 50 at the insert bearing against one side and with a threaded washer 52 holding the insert in place.
  • a bolt 54 extends through the insert and the bracket 46 with a nut 56 holding the bracket in place.
  • the walls 58 of the middle layer may be thicker in the region of the insert.
  • Figure 7 shows a bracket 60 being fastened to a spigot 62 towards the end of the fairing
  • the spigot is connected to the forwards end by being rotated to cooperate with a nut 64 on the inner side of a wall 67. It is possible that the wall 67 or the wall and the nut could be moulded with the middle section. Again no fabrication will be required to provide the means to attach the spigot.
  • honeycomb type structure will also act as a strengthener.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Vehicle Interior And Exterior Ornaments, Soundproofing, And Insulation (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)

Abstract

Un organe d'atténuation acoustique d'aéronef comprend un carénage conique (10) comportant une couche thermique interne (24), une structure alvéolaire moulée par injection comportant une paroi tournée vers l'intérieur (28) et des alvéoles carrées (30), et un revêtement externe perforé (32).
PCT/GB2010/050365 2009-03-09 2010-03-02 Organe d'atténuation acoustique d'aéronef et procédé de formation dudit organe WO2010103302A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB1115385A GB2480208A (en) 2009-03-09 2010-03-02 Aircraft acoustic attenuation member and method for forming said member
CA2754782A CA2754782A1 (fr) 2009-03-09 2010-03-02 Organe d'attenuation acoustique d'aeronef et procede de formation dudit organe
CN2010800111466A CN102349101A (zh) 2009-03-09 2010-03-02 飞机消声构件和用于形成所述构件的方法
EP10707649A EP2406786A1 (fr) 2009-03-09 2010-03-02 Organe d'atténuation acoustique d'aéronef et procédé de formation dudit organe

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0903999.1 2009-03-09
GB0903999A GB2468484A (en) 2009-03-09 2009-03-09 An acoustic attenuation member for an aircraft

Publications (1)

Publication Number Publication Date
WO2010103302A1 true WO2010103302A1 (fr) 2010-09-16

Family

ID=40600718

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2010/050365 WO2010103302A1 (fr) 2009-03-09 2010-03-02 Organe d'atténuation acoustique d'aéronef et procédé de formation dudit organe

Country Status (5)

Country Link
EP (1) EP2406786A1 (fr)
CN (1) CN102349101A (fr)
CA (1) CA2754782A1 (fr)
GB (2) GB2468484A (fr)
WO (1) WO2010103302A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11460048B2 (en) 2020-12-18 2022-10-04 Rohr, Inc. Attachable acoustic panels and method of making same

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2979829B1 (fr) * 2011-09-09 2013-09-27 Astrium Sas Bouclier pare flamme perfectionne
FR2995360B1 (fr) 2012-09-12 2018-06-15 Snecma Procede de montage d'un panneau acoustique dans un carter d'une turbomachine et turbomachine comportant un panneau acoustique
JP6674658B2 (ja) * 2016-03-11 2020-04-01 株式会社リコー 吸音装置、電子機器及び画像形成装置

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4782913A (en) * 1986-05-06 1988-11-08 Dr. Alois Stankiewicz Gmbh Constructional element with acoustic properties
US5151311A (en) 1987-11-02 1992-09-29 Grumman Aerospace Corporation Acoustic attenuating liner and method of making same
EP0636780A1 (fr) 1993-06-25 1995-02-01 Nordam Couche pour supprimer le bruit des réacteurs d'avion
WO1999061221A1 (fr) * 1998-05-22 1999-12-02 Rieter Automotive (International) Ag Procede de fabrication d'un composant a double paroi a absorbeurs lambda/4 integre
US20030031556A1 (en) * 2001-08-11 2003-02-13 Mulcaire Thomas G. Guide vane assembly
US20040045766A1 (en) 2002-09-10 2004-03-11 Airbus France Acoustically resistive layer for an acoustical attenuation panel, panel using such a layer
US20040045765A1 (en) 2002-09-10 2004-03-11 Alain Porte Tubular acoustic attenuation piece for an aircraft jet engine air intake
US20080083210A1 (en) 2006-10-04 2008-04-10 Spirit Aerosystems, Inc Monolithic thrust reverser components
WO2008152259A2 (fr) 2007-04-30 2008-12-18 Airbus France Panneau acoustique a caracteristique acoustique variable

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4782913A (en) * 1986-05-06 1988-11-08 Dr. Alois Stankiewicz Gmbh Constructional element with acoustic properties
US5151311A (en) 1987-11-02 1992-09-29 Grumman Aerospace Corporation Acoustic attenuating liner and method of making same
EP0636780A1 (fr) 1993-06-25 1995-02-01 Nordam Couche pour supprimer le bruit des réacteurs d'avion
WO1999061221A1 (fr) * 1998-05-22 1999-12-02 Rieter Automotive (International) Ag Procede de fabrication d'un composant a double paroi a absorbeurs lambda/4 integre
US20030031556A1 (en) * 2001-08-11 2003-02-13 Mulcaire Thomas G. Guide vane assembly
US20040045766A1 (en) 2002-09-10 2004-03-11 Airbus France Acoustically resistive layer for an acoustical attenuation panel, panel using such a layer
US20040045765A1 (en) 2002-09-10 2004-03-11 Alain Porte Tubular acoustic attenuation piece for an aircraft jet engine air intake
US20080083210A1 (en) 2006-10-04 2008-04-10 Spirit Aerosystems, Inc Monolithic thrust reverser components
WO2008152259A2 (fr) 2007-04-30 2008-12-18 Airbus France Panneau acoustique a caracteristique acoustique variable

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11460048B2 (en) 2020-12-18 2022-10-04 Rohr, Inc. Attachable acoustic panels and method of making same

Also Published As

Publication number Publication date
EP2406786A1 (fr) 2012-01-18
GB201115385D0 (en) 2011-10-19
CA2754782A1 (fr) 2010-09-16
CN102349101A (zh) 2012-02-08
GB0903999D0 (en) 2009-04-22
GB2468484A (en) 2010-09-15
GB2480208A (en) 2011-11-09

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