Classifications

• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
  • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• • 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
  • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
  • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating

Definitions

• the present invention relates to a turbojet engine nacelle element, in particular a thrust reverser.
• An aircraft is driven by several turbojets each housed in a nacelle also housing a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped.
• These ancillary actuating devices comprise in particular a mechanical system for actuating thrust reversers.
• a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing a thrust reverser means and intended to surround the combustion chamber of the turbojet engine. , and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
• the modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle.
• the two air flows are ejected from the turbojet engine from the rear of the nacelle.
• the role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine.
• the inverter obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
• an inverter comprises displaceable movable covers, generally via sleeves or guides receiving a guide shaft, between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deviated flow, and secondly, a position retraction in which they close this passage.
• These covers can perform a deflection function or simply activation other means of deflection.
• a thrust reverser is required to perform its function in a wide range of atmospheric conditions, especially at very high temperatures of up to 55 ° C.
• frost or frost may still be present in the sleeves or guiding slides of the movable covers of the thrust reversers, and brake or block the actuation of the thrust reversers.
• turbojet engine nacelle element comprising movable hoods pivoting or in translation relative to a fixed nacelle element structure.
• the present invention aims to avoid these disadvantages, and consists of a turbojet engine nacelle element, comprising at least one movable cowl pivotally mounted or sliding in a substantially longitudinal direction of the nacelle, between an extended position and a closed position relative to to a fixed structure of the nacelle element, by means of at least one pivoting or translating guide sleeve receiving a guide shaft, and in which a heating electric defrosting device is arranged inside the the guide shaft, or forms an interface between the guide shaft and the guide sleeve.
• the electric heating defrosting device is disposed on an interface sheath, in particular made of a material plastic or organic, and mounted on an inner wall of the guide sleeve.
• the de-icing device is preferably disposed on a surface of the predetermined interface sleeve so as to be weakly solicited by the movement of the guide shaft in the sleeve.
• the deicing device disposed inside the guide shaft, is connected to electrical supply means, provided at the fixed structure of the nacelle element, via an electrically conductive and elastically deformable element whose deformation aims to compensate for the displacement of the guide shaft relative to the fixed structure of the nacelle element.
• the deicing device may comprise a metal or organic base.
• the defrosting device comprises for example a reflective strip for concentrating the heat generated by the defrosting device between the guide shaft and the guide sleeve.
• the activation of the defrosting device can be controlled according to a signal from a temperature or frost detector.
• the activation of the deicing device is triggered automatically from the beginning of the thrust reversal.
• the nacelle element may be a thrust reverser.
• the activation of the deicing device can be triggered automatically from the beginning of the thrust reversal.
• the nacelle element is for example a thrust reverser with grids in which the guide sleeve is a slide and the guide shaft is a slide.
• FIG. 1 is a partial schematic cross-sectional view of a turbojet nacelle element element according to a first embodiment of the invention.
• Figure 2 is an enlarged view of a detail of Figure 1.
• Figure 3 is a partial longitudinal sectional view along the arrow III of Figure 2.
• Figure 4 illustrates the structure of defrosting devices equipping the previous nacelle element.
• Figure 5 is an enlarged view of a detail of Figure 2.
• FIG. 6 represents a deicing device of FIG.
• FIG. 7 is a view similar to Figure 2 of an alternative embodiment of the invention.
• FIG. 8 represents a defrosting device of FIG. 7.
• Figure 9 is a view similar to Figures 2 and 7 of another embodiment of the invention.
• FIG. 10 is a partial view in longitudinal section along the arrow X of FIG. 9.
• FIG. 1 represents an example of a turbojet engine nacelle element according to the invention, here produced in the form of a thrust reverser 1 to FIG. grids.
• the thrust reverser 1 comprises, on the one hand, deflection grids (not shown) of a portion of an air flow of the turbojet engine (not shown) and on the other hand, two covers 2 movable in translation in a substantially longitudinal direction of the nacelle and adapted to pass alternately from a closed position, in which they provide the aerodynamic continuity of the nacelle and cover the deflection grids, at an opening position, in which they open a passage in the nacelle and discover the deflection grids.
• Complementary locking doors activated by the sliding of the cowling 2, generally allow a closure of the vein downstream of the grids so as to optimize the reorientation of the cold flow.
• the movable covers 2 are slidably mounted on load-bearing fittings 3 arranged in the lower and upper parts of a fixed structure of the inverter 1.
• Each carrier fitting 3 comprises a substantially cylindrical primary guide slide 4 and designed to receive a primary guide slide 5 of a cover 2.
• each cover 2 has a secondary guide rail 7 of substantially rectangular profile and adapted to receive a secondary guide slide 6 of the corresponding carrier fitting 3.
• a heated electric defrosting device 9 is disposed on a sleeve 8 forming a interface between each slide 5 and the corresponding guiding slide 4.
• the interface sheath 8 is made here of a material such as Teflon, and it is mounted on an inner wall of the guiding slide 4.
• the electric defrosting device 9 comprises a wired metallic base (see FIG. 4) affixed on a reflective strip (not shown), and electrically connected at 11 to a power supply box (not shown) at an upstream fixed structure 10 of the inverter 1.
• the reflective strip makes it possible to concentrate the heat generated by the deicing device 9 towards a zone between the slide 5 and its guide slide 4, and thus to save energy.
• a second deicing device 13 similar to the device 9 presented above, is arranged on an interface sleeve 12 mounted on an inner wall of the secondary guide rail 7.
• the interface sheaths 8 and 12 could also be integrated with the guide rails 4 and 7 corresponding.
• the carrier fitting 103 comprises a primary guide rail 104 with a 'D' shaped profile open in its curved part.
• the interface sleeve 108 has an identical profile and encloses a primary guide slide 105 having a complementary profile.
• Figure 10 is a schematic view on which slide 204 has not been shown for clarity.
• the defrosting device 209 is disposed on a tubular inner wall of the guide slide 205. As previously, the deicing device 209 is electrically connected, at 211, to a power supply box (not shown) at a structure fixed upstream 210 of the inverter 1.
• this electrical connection is here carried out by means of an electrically conductive element 214 elastically deformable provided to ensure electrical continuity between the deicing device 209, which is now movable in translation since associated with the guide slider 205, and the power supply circuit 211, fixed on the upstream fixed structure 210 of the inverter 1.
• the elastic deformation of the electrically conductive element 214 makes it possible to compensate for the positioning tolerances with the defrosting device 209 that is mobile in translation following the displacement. This embodiment does not require an interface sleeve since the defrosting device 209 here provides heating of the single slide 205.
• the activation of the de-icing devices 9, 13, 109 or 209 may be systematic, especially from the beginning of the thrust reversal, and / or controlled (via an electronic control system). control and / or power of the inverter) according to a signal from a temperature or frost detector (not shown) in the environment of the corresponding slide 4, 7, 104 or 204.

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

Applications Claiming Priority (2)

Publications (1)

Family

ID=37980102

Family Applications (1)

Country Status (8)

Families Citing this family (11)

Family Cites Families (8)

• 2006
  • 2006-11-03 FR FR0609608A patent/FR2908109B1/fr not_active Expired - Fee Related
• 2007
  • 2007-09-27 RU RU2009120114/11A patent/RU2009120114A/ru unknown
  • 2007-09-27 CN CNA2007800391056A patent/CN101528542A/zh active Pending
  • 2007-09-27 CA CA002666747A patent/CA2666747A1/fr not_active Abandoned
  • 2007-09-27 US US12/513,432 patent/US20100064660A1/en not_active Abandoned
  • 2007-09-27 WO PCT/FR2007/001580 patent/WO2008053088A1/fr not_active Ceased
  • 2007-09-27 EP EP07848291A patent/EP2084063A1/de not_active Withdrawn
  • 2007-09-27 BR BRPI0717965-0A patent/BRPI0717965A2/pt not_active Application Discontinuation

Non-Patent Citations (1)

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