Classifications

• • 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
  • F02K1/56—Reversing jet main flow
  • F02K1/566—Reversing jet main flow by blocking the rearward discharge by means of a translatable member
• • 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
• • 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 a thrust reversal device with flow deflection grids.
• An airplane is driven by several turbojets each housed in a nacelle housing, also, a set of ancillary actuators related to its operation and providing various functions when the turbojet engine is in operation or stopped.
• This nacelle is intended to house a turbofan engine capable of generating by means of blades of a rotating fan a flow of hot air from the combustion chamber of the turbojet engine, and a cold air flow which circulates outside the turbojet engine through an annular vein of cold airflow.
• the thrust reverser device obstructs the flow of cold air flow and directs the latter upstream of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
• Another object of the present invention is to provide a nacelle in which the space available for the deflection gates in the thrust reverser device is optimized.
• Such a rear frame optimizes the maximum length of the deflection grids and thus participates in improving the aerodynamic performance of the device.
• FIG. 4 is a perspective view of the deflection grid / rear frame assembly of FIG. 3 assembled
• FIG. 5 is a perspective view of the deflection grid / rear frame assembly of FIG. 3 mounted on a fixed structure of the thrust reverser device according to the present invention.
• the terms upstream and downstream used hereafter are defined with respect to the direction of the flow passing through the thrust reverser device.
• This device 1 00 comprises a movable cover 30 mounted in translation, in a direction substantially parallel to a longitudinal axis of the nacelle, relative to a fixed structure of the nacelle comprising at least one front frame 20.
• This cover 30 is also extended by at least one ejection nozzle section 60 for channeling the ejection of the cold flow, mounted at a downstream end of said cover 30.
• the cap 30 comprises an outer shell 31 and an inner shell 32 which is in continuity with the front frame 20 and is intended to delimit, in a direct jet position of the turbojet engine, an external wall of the vein 1 in which flows the cold flow.
• the hood 30 is able to pass alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle with the front frame 20 and covers first deflection grids 40, to an open position, in downstream of the nacelle, in which it opens a passage in the nacel and discovers the first deflection grids 40.
• Figure 1 illustrates the cover 30 in the closed position.
• upstream deflection grids 40 of the thrust reverser device 100 are arranged circumferentially along the periphery of the cover 30 facing the reversing well so that the deflected flow passes, at least in part, through them.
• these upstream deflection grids 40 are fixed with respect to the fixed structure of the nacelle and, more particularly, with respect to the frame. before 20 and with respect to the upper and lower longitudinal beams (not shown) of the fixed structure. In an alternative embodiment, they may, however, be movable in translation along the longitudinal axis of the nacelle with the cover 30 and / or the nozzle 60 or independently of the latter.
• the flux deflecting vanes 42 are of the curved fin type, spaced along the segment 41 and, in this embodiment, along the longitudinal axis of the nacelle, these fins being adapted to redirect the flow upstream of the nacelle. device for realizing the inversion of thrust when the latter in the inverted jet position.
• each of the upstream deflection grids 40 may be fixed, at its upstream end, removably by means adapted to the fixed structure of the nacelle and, more particularly, to a structural element of the front frame 20. and at its downstream end, by means adapted to a rear frame 70, itself housed in the thickness of the cover 30.
• the deflection grids 80 of the rear frame 70 each have a single series of blades 82 which extend angularly over a distance identical to that of two series of adjoining vanes 42 of an upstream deflection grid. 40.
• the cover 30 slides downstream of the platform in the open position, revealing Jors of its displacement, in the first place the grids upstream deflection 40 and then the rear frame 80 and its downstream deflection grids 80.

Landscapes

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

Applications Claiming Priority (2)

Publications (1)

Family

ID=46639574

Family Applications (1)

Country Status (8)

Families Citing this family (15)

Family Cites Families (7)

• 2011
  • 2011-08-08 FR FR1157227A patent/FR2978990A1/fr active Pending
• 2012
  • 2012-07-05 WO PCT/FR2012/051580 patent/WO2013021110A1/fr active Application Filing
  • 2012-07-05 CA CA2842749A patent/CA2842749A1/fr not_active Abandoned
  • 2012-07-05 BR BR112014002212A patent/BR112014002212A2/pt not_active IP Right Cessation
  • 2012-07-05 CN CN201280038800.1A patent/CN103732900A/zh active Pending
  • 2012-07-05 RU RU2014108514/06A patent/RU2014108514A/ru not_active Application Discontinuation
  • 2012-07-05 EP EP12744048.5A patent/EP2742228A1/de not_active Withdrawn
• 2014
  • 2014-02-10 US US14/176,236 patent/US20140154064A1/en not_active Abandoned

Non-Patent Citations (1)

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