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
  • F02K1/64—Reversing fan flow
  • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
• • 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
• • 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
  • F05D2260/00—Function
  • F05D2260/30—Retaining components in desired mutual position
  • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

• Thrust reverser with doors for turbojet engine Thrust reverser with doors for turbojet engine.
• a thrust reverser with doors for a turbojet engine.
• a thrust reverser with doors comprises, as shown in Figures 1 and 2 appended hereto, at least two doors 1a, 1b each pivotally mounted about an axis 3 between a closed position ( position shown in Figure 2) corresponding to a normal operation of the turbojet, and an open position (not shown) by means of which the air flow flowing in the vein 5 may be deflected outwards and upstream of the inverter, thus enabling a counter-thrust contributing to the braking of the aircraft 7 (upstream and downstream are defined with respect to the direction of airflow in the turbojet engine, from left to right on the Figures 1 and 2).
• a first system locks the upstream portion of each door 1a, 1b
• a second system locks actuating cylinder 9 of this door
• a third system locks a side edge from this door.
• a malfunction of the locking system of the cylinder 9 is difficult to detect from the outside, during maintenance operations.
• the present invention is intended to overcome these problems.
• This object of the invention is achieved with a thrust reverser comprising at least two movable gates each between a closed position and an open position, characterized in that these two doors are adjacent and in that they comprise mutual blocking means. disposed on the adjacent edges of these doors and preventing the opening of one of said doors while the other is closed.
• These mutual blocking means constitute a very simple locking system, for retaining a first door in the closed position through a second adjacent door, in the event of rupture of the other two locking systems of the first door.
• said mutual blocking means are arranged on at least a part of the length of the adjacent edges of said doors;
• said mutual blocking means comprise a groove disposed on the edge of one of said doors, and a blade disposed on the adjacent edge of the other door;
• said mutual blocking means are arranged in a pointwise manner on the adjacent edges of said doors;
• said mutual blocking means are arranged upstream of said doors;
• said mutual blocking means comprise a housing disposed on the edge of one of said doors, and a pin disposed on the adjacent edge of the other door;
• said mutual blocking means have a fair play sufficient to allow the opening of said doors: such a clearance makes it possible, in the event of failure of the locking systems of a door, to keep it flush with the outer casing of the door; Platform ;
• said mutual blocking means are shaped so as to keep said doors integral with one another during part of their opening: this makes it possible, in the event of failure of the locking systems of a door, to limit the mad course; of this door during the opening of the other door, and thus reduce the abutment shock at the end of the opening stroke of this idle door;
• said mutual blocking means are integrated with said doors; - said mutual blocking means are reported on said doors;
• said thrust reverser comprises a beam disposed between said doors, extending under said mutual blocking means when said doors are closed; said thrust reverser comprises an actuating cylinder for each door.
• the present invention also relates to a turbojet engine nacelle equipped with a thrust reverser according to the above.
• FIG. 1 represents a nacelle for an aircraft turbojet, equipped with a thrust reverser with gates of the prior art, mentioned in the preamble of the present description,
• FIG. 2 represents one of the doors of this thrust reverser of the prior art, seen in longitudinal section
• FIG. 3 shows in perspective half of a thrust reverser with doors according to the present invention, these doors being in the closed position
• FIG. 4 represents this thrust reverser with its doors open
• FIG. 5 represents a cross-sectional view of this thrust reverser, the doors being in the closed position
• FIG. 6 represents a detailed view of the zone V1 of FIG. 5;
• FIGS. 7 and 8 are views similar to that of FIG. 6 and respectively correspond to situations where the locking systems of one or on the other, doors fail,
• FIG. 9 is a view similar to that of FIG. 6, the two doors being shown at the beginning of their opening stroke
• FIG. 10 is a view similar to that of FIG. 6 of another embodiment of FIG. embodiment according to the invention.
• the two openings 13a, 13b released by the two doors 1a, 1b are separated from each other by a longitudinal beam 15, which is covered by the edges 11a, 11b when the doors 1a, 1b are in the closed position (see FIGS. 3 and 5).
• the beam 15 may have a substantially trapezoidal section, and that the edges 11a, 11b of the doors 1a, 1b respectively define a groove
• This groove 17 and this blade 19 may be disposed locally upstream of the edges 11a, 11b of the doors 1a, 1b, or preferably extend over substantially the entire length of these edges.
• a clearance J is provided between each of the faces of the blade 19 and the corresponding faces of the groove 17, this clearance being just sufficient to allow the outlet of the blade 19 of the groove 17 during the pivoting of the two doors with respect to their axes. respective 3a, 3b. If it is assumed that the locking systems of the door 3b become inoperative following an incident such as a dawn break of the turbojet, this door 3b goes crazy, that is to say, free of rotate about its axis 3b.
• the blade 19 and the housing 17 constitute mutual blocking means of the two doors 1a, 1b, for retaining one or the other of these doors which would go mad as a result of a failure of its systems locking.
• This housing 17 and this blade 19 therefore constitute for each door a line of defense of extremely simple design, which comes add to the other lines of defense constituted by the locking systems of each of these doors.
• FIG. 9 shows the two doors 1a, 1b being opened: thanks to the games J represented in FIG. 6, the blade 19 can be progressively extracted from the housing 17.
• This particular arrangement makes it possible to ensure that a door that becomes crazy as a result of a failure of its locking systems can not separate from its adjacent door when these two doors arrive almost at the end of the opening stroke, minimizing thus the stop shock at the opening of the crazy door.
• FIG. 10 represents another embodiment of the invention, in which the mutual blocking of the doors 1a and 1b is obtained by means of a pin 21 cooperating with a housing 23, these members being preferably arranged near the upstream edge doors 1a, 1b.
• the fact of providing that the edges 11a, 11b protrude circumferentially from the body of the doors 1a, 1b, as is visible on all the Figures 4 to 9, increases the wind resistance of these doors when they are in the open position, which contributes to the braking action of the aircraft.
• the principle of the doors that lock each other in the closed position could be extended to more than two doors, for example three or four doors mutually cooperating with each other.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Wing Frames And Configurations (AREA)
• Hinges (AREA)
• Power-Operated Mechanisms For Wings (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=39512820

Family Applications (1)

Country Status (8)

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Family Cites Families (9)

• 2008
  • 2008-01-08 FR FR0800083A patent/FR2926112A1/fr not_active Withdrawn
  • 2008-10-01 US US12/811,318 patent/US20100281849A1/en not_active Abandoned
  • 2008-10-01 CA CA2705361A patent/CA2705361A1/fr not_active Abandoned
  • 2008-10-01 RU RU2010132307/06A patent/RU2010132307A/ru not_active Application Discontinuation
  • 2008-10-01 EP EP08870411A patent/EP2232040A2/de not_active Withdrawn
  • 2008-10-01 WO PCT/FR2008/001364 patent/WO2009087282A2/fr not_active Ceased
  • 2008-10-01 BR BRPI0822149-9A patent/BRPI0822149A2/pt not_active IP Right Cessation
  • 2008-10-01 CN CN2008801234292A patent/CN101910598A/zh active Pending

Non-Patent Citations (1)

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