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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D29/00—Power-plant nacelles, fairings or cowlings
• • 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
  • 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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement 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
  • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
• • 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0206—Arrangement 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0266—Arrangement 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—Arrangement 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
  • F05D2230/00—Manufacture
  • F05D2230/60—Assembly methods
  • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
• • 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
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T137/00—Fluid handling
  • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

• the present invention relates to an air intake structure for a turbojet engine nacelle.
• an aircraft propulsion unit conventionally comprises a turbojet engine housed inside a nacelle.
• the nacelle generally has an annular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of said turbojet engine and its casing, and a downstream section intended to surround the combustion chamber of the turbojet engine and sheltering as the case may be. thrust reverser means.
• the air intake structure serves to optimize the air intake necessary to supply the fan of the turbojet engine and to channel it towards this fan.
• An air intake structure comprises in particular upstream a leading edge structure commonly called "lip" air inlet.
• the air intake lip ensures the capture of air and is attached to the rest of the air intake structure which ensures the channeling of the air captured to the turbojet engine.
• the remainder of the air intake structure has a substantially annular structure comprising an outer panel providing external aerodynamic continuity of the nacelle and an inner panel ensuring the aerodynamic continuity of the nacelle internally, particularly with the housing of blower at the middle section.
• the air inlet lip ensures the junction between these two walls and can in particular be integrated into the outer panel.
• Such nacelles comprising an air intake lip integrated in the outer panel are called “laminar” and the outer panel / air inlet lip assembly can be mounted to move in translation in a longitudinal direction of the nacelle, to allow its upstream opening.
• laminar Such a nacelle is described in documents FR 2 906 568 and EP 2 344 385, for example.
• the inner surface of the air intake structure is exposed to a large air flow and is located near the blades of the blower. It is therefore located in a zone of significant noise.
• the inner panel of the air intake section is equipped with an acoustic attenuation structure.
• This acoustic attenuation structure is in the form of a honeycomb core sandwich panel having a pierced outer skin, called acoustic skin, intended to be exposed to noise, and a solid inner skin ensuring in particular the mechanical strength of the panel.
• the alveolar soul thus constitutes a resonator capable of trapping sound waves.
• the air intake lip may also be equipped with an acoustic attenuation structure on an internal portion thereof.
• the air intake lip and the inner panel are equipped with connecting flanges, latch means for example, aerodynamic continuity bibs, bumpers, etc.
• This junction causes a loss of available acoustic surface related to the volume required for the establishment of these joints, bibs and bumpers, among others.
• the bumpers serve as a centering device between the lip and the inner panel and its attached to the air inlet lip panel by means of screws, with a nut-side access inside a C of closing.
• the same assembly principle is used for the aerodynamic bib.
• the lip flange is also used as a support for the installation of a peripheral seal and also serves as a support for the bumpers and the aerodynamic bib. All these functions impact the beginning of the acoustic zone on either side of said junction zone. There is therefore a need for a solution for centering and maintaining such a structure to reduce the non-equipable junction area with an acoustic attenuation structure.
• the present invention relates to an air inlet structure for a turbojet engine nacelle comprising at least one inner panel intended to be attached to a fan casing of the turbojet and thus to constitute a fixed part of said air intake.
• air and at least one outer panel movable in translation in a substantially longitudinal direction of the nacelle and incorporating an air inlet lip portion adapted to ensure a junction between the fixed inner panel and the outer panel, said portion of air intake lip and said fixed inner panel being each equipped at least at a junction end with an acoustic attenuation structure, characterized in that at least one of the junction ends is equipped with at least one radial knocker adapted to come into contact with a corresponding junction flange presented by the other end junction when the movable outer panel is positi closing.
• the hob is integrated with the acoustic panel of its junction end.
• the knocker may be reported, in particular by gluing.
• the corresponding flange is integrated with the acoustic panel of its junction end.
• it may also be reported, especially by gluing.
• the structure comprises several knockers distributed over a circumference of the junction end.
• At least one of the contact surfaces of the knocker and the flange is equipped with a coating with a low coefficient of friction. It may especially be a Teflon type coating.
• Such a coating, Teflon tape or other, provides a low friction coating which can be used as a wear part.
• the junction of acoustical panels is equipped with at least one aerodynamic flange seal.
• the junction is equipped with at least one seal.
• the seal is located between an acoustic panel, and the flange.
• FIG. 1 is a partial schematic representation in longitudinal section of a so-called “laminar” air intake structure equipped with a centering device according to the prior art
• FIGS. 2 and 3 are partial diagrammatic representations in longitudinal section of a junction between an inner panel and an air intake lip portion equipped with a centering system according to the invention
• FIGS. 4a, 4b, 5a, 5b and 6a to 6d are partial schematic representations of the steps of setting up an aerodynamic flange seal
• FIGS. 7 and 8 are diagrammatic representations in longitudinal section of an alternative embodiment of the invention.
• FIG. 9 is a schematic cross-sectional representation corresponding to the air intake structure of FIGS. 7 and 8,
• FIGS. 10a to 10d are partial diagrammatic representations of the installation of the aerofoil flange gasket
• the present invention more particularly applies to so-called "laminar" nacelles having an air inlet structure 1, an outer wall 2 of which is mounted to move in translation in a longitudinal direction of the nacelle and incorporates a lip portion 2a of air inlet.
• such an air intake structure for a turbojet engine nacelle comprises at least one inner panel 3 intended to be attached to a fan casing (not visible) of the turbojet engine and thus to constitute a fixed part of said air intake.
• air 1 and at least one outer panel 2 movable in translation in a substantially longitudinal direction of the nacelle and incorporating an air intake lip portion 2a adapted to provide a junction A0 between the fixed inner panel 3 and the outer panel 2.
• said air inlet lip portion 2a and said fixed inner panel 3 are each equipped at least at a junction end with an acoustic attenuation structure in the form of a panel 5, 6 honeycomb sandwiches.
• the centering of the outer wall 2 and the air inlet lip 2a with the inner panel 3 is provided at a junction A0 between said portion of air inlet lip 2a and said inner wall 3 by means of knockers 7 fixed in the lip-side acoustic panel 2a by means of a screw 7a with a nut-side access inside a C closing 7b.
• An aerodynamic bib 8 to optimize the flow of air flow at the junction between the panels is set according to the same principle.
• a flange 9 fixed in the inner panel 3 comes, during the closing of the outer panel 2, against a seal 10 carried by a corresponding flange 1 1 of the lip portion 2a of air inlet to ensure the l sealing of the interior of the air intake structure 1.
• This flange also allows support for the knockers 7 and 8 aerodynamic bib.
• the acoustic panel 6 of the inner panel 3 has a junction end equipped with a radial knocker 81 on which is able to rest a corresponding junction flange 91 fitted to one end joining the acoustic panel 5 of the air intake lip portion 2a when the latter is in the closed position.
• the knocker 81 carries a coating strip 82 of Teflon type with a low coefficient of friction.
• the coating strip 82 with a low coefficient of friction may be carried by the flange 91 junction.
• This coating strip has a dual function, namely reduction of friction during closing of the air inlet, and wear part.
• the coating strip may be disposed either on the knocker side 81, or fixed under the flange 91, or be present on both elements.
• the connecting flange 91 has an end return 91a carrying a seal 10 adapted to cooperate with a flange 92d. corresponding seal carried by the inner panel ( Figure 2).
• a seal 101 may be mounted at the junction end of the inner panel 3 and come into contact with the connecting flange 91 to ensure sealing closer to said junction A0.
• the seal 101 may be integrated or attached to the connecting flange 91 in particular to abut against the inner panel 3 during closing.
• junction flange 91 and the flange 92 of the inner panel 3 can then be used for the introduction of axial stops 20 and / or locks between the lip portion 2a / outer panel 2 and the inner panel 3.
• the seal 1 0, 1 01 will equip the entire circumference of the structure.
• the knockers 81 will also advantageously be arranged along the circumference of the structure 1 and preferentially distributed discretely, advantageously uniformly. Of course, it may also be a continuous knocker 81 describing substantially the entire circumference.
• the beginnings of the acoustic surfaces of the air intake lip portion 2a and of the inner panel 3 are as close as possible to the A0 junction between these two panels, which improves the acoustic treatment of the entire air intake structure 1.
• junction AO between the air intake lip portion 2a and the inner panel 3 may also be equipped with an aerodynamic flange seal 102.
• the aerodynamic flap 102 has a flexible elastic structure mounted on an upper skin of an acoustic panel 5 of the lip portion 2a of air inlet.
• the flap 102 extends along the thickness of said acoustic panel 5 at its junction end A0 and has a lower return 102a extending on either side of said junction A0, both on the lip portion. 2a of air intake only on the inner panel (not shown in Figures 4a, 4b, 5a, 5b), thus providing an aerodynamic recovery of the junction.
• Figures 4a and 5a are cross-sectional front views of said aerodynamic bib seal 102.
• a lower part of the flap deviates from the acoustic panel and allows the mounting of the acoustic panel belonging to the inner panel.
• FIGS 7 to 9 and 10a to 10d are views of a second embodiment of an air intake structure 1 10 according to the invention in which the knockers 81 belong to the acoustic panel 5 of the portion of lip 2a and the connecting flange 91 belongs to the acoustic panel 6 of the inner panel 3.
• Figure 7 is in longitudinal sectional view taken substantially at locking means 21 (or axial stops 20).
• Figure 8 is a longitudinal sectional view taken in current section.
• Figure 9 is a cross sectional view of the face in current section.
• Figures 10a to 10d are substantially equivalent to Figures 6a to 6d and illustrate the establishment of the seal 102 aerodynamic flap. Note also that in this embodiment, the seal 102 also performs the function of the seal 10 and 101 by means of an upper tab 104 which comes into contact against the connecting flange 91 when closing the structure (closing direction represented by the arrow in Figure 10c).
• the translatable air inlet generally forms an adjustable removable sleeve on a conduit formed by the base structure of the nacelle.
• the centering and sealing system object of the present invention can be applied generally to any type of removable sleeve that would be desired to centrally position and sealed on one end of a conduit.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Aviation & Aerospace Engineering (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (8)

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Family Cites Families (13)

• 2012
  • 2012-03-29 FR FR1252815A patent/FR2988778B1/fr active Active
• 2013
  • 2013-03-21 EP EP13715366.4A patent/EP2831393A1/fr not_active Withdrawn
  • 2013-03-21 BR BR112014024025A patent/BR112014024025A8/pt not_active IP Right Cessation
  • 2013-03-21 CN CN201380017920.8A patent/CN104220728A/zh active Pending
  • 2013-03-21 WO PCT/FR2013/050610 patent/WO2013144485A1/fr active Application Filing
  • 2013-03-21 RU RU2014142817A patent/RU2014142817A/ru not_active Application Discontinuation
  • 2013-03-21 CA CA 2868146 patent/CA2868146A1/fr not_active Abandoned
• 2014
  • 2014-09-25 US US14/496,518 patent/US9938897B2/en active Active

Non-Patent Citations (1)

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