Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
  • F01D25/243—Flange connections; Bolting arrangements
• • 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
  • B64D29/00—Power-plant nacelles, fairings, or cowlings
  • B64D29/08—Inspection panels for power plants
• • 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—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• • 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
  • F02K1/76—Control or regulation of thrust reversers
  • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• • 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
  • F05D2230/80—Repairing, retrofitting or upgrading methods
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16H—GEARING
  • F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
  • F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions
  • F16H25/20—Screw mechanisms
  • F16H2025/2037—Actuator supports or means for fixing piston end, e.g. flanges
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16H—GEARING
  • F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
  • F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions
  • F16H25/20—Screw mechanisms
  • F16H2025/2062—Arrangements for driving the actuator
  • F16H2025/2075—Coaxial drive motors
• • 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 an actuator for an aircraft jet engine nacelle having a rear part, in particular a single-piece annular part.
• the rear part A defining, with the fairing C of the turbojet engine (often referred to as "IFS" or "fixed internal structure"), the flow vein cold V, is in the form of a one-piece ferrule: it is commonly referred to as "O-Duct" type boat.
• the rear part of nacelle A is slidably mounted on a top beam S by means of rails R, between the operating position visible in FIG. 1, and a maintenance position visible in FIG. 2, in which the rear portion of the nacelle is spaced towards the rear of the nacelle, thus allowing access to the turbojet T for maintenance operations.
• NFS C can be opened towards the outside of the nacelle, by pivoting the two halves that compose it around substantially parallel axes. to the axis of the nacelle.
• the sliding movement of the rear part of the nacelle towards its maintenance position can be carried out manually, or by means of electric or hydraulic actuators.
• FIG. 1 An example of such an actuator of the prior art is shown in FIG. 1
• such an actuator comprises a worm 1 on which is screwed a nut 3, itself secured to an actuating tube 5 whose free end terminates in an eyelet or ball 7 .
• balls 8 are interposed between the threads of the screw 1 and those of the nut 3, so as to reduce friction, so that this type of actuator is commonly referred to as a "ball screw”.
• the screw 1 comprises, at its end opposite to that of the ball 7, a pinion 9 with oblique teeth cooperating with a pinion master 1 1 itself driven directly or indirectly by an electric motor. Under the action of this electric motor, one can rotate the screw 1 in one direction or the other, and thus translate the nut 3 in one direction or the other, and thus lengthen or retract the tube 5.
• the present invention thus aims to overcome the aforementioned drawbacks.
• an actuator for a jet engine nacelle comprising a rear part, in particular a single-piece annular, comprising:
• a set of screws comprising a translating screw without rotation engaged with said nut and a ball joint at one end of said screw to be fixed to said rear portion.
• the screw which thus passes through the nut, can be translated by rotating the nut: this screw can pass from a position where the fixing ball is substantially in contact with the nut. at a position where it is distant from this nut a length substantially equal to the length of the screw.
• the actuator according to the invention can reduce substantially by half, compared to the aforementioned prior art, the cantilever when it is in full extension position.
• said motor assembly comprises a support and a casing adapted to be fixed on this support and to enclose said nut;
• said actuator comprises a protection tube fixed on said support, suitable for containing said screw when the actuator is in the retracted position: this tube makes it possible to protect the screw from particles capable of seizing the actuator, and to limit the movements of vibration of the screw.
• the present invention also relates to a single-piece annular aircraft turbojet engine nacelle comprising a plurality of actuators in accordance with the foregoing, disposed between a fixed part of this nacelle and said rear nacelle part.
• this nacelle comprises a top beam and said nacelle rear part is slidably mounted on rails disposed on either side of the beam, an actuator according to the above being mounted on each side of the beam.
• this beam in the vicinity of said rails: in such a nacelle, because of the character of the rear part, it can be satisfied with two actuators; the fact of providing that they are close to the rails limits the tilting moments printed by these actuators to the rear part of nacel when it opens, and therefore the risk of jamming;
• the present invention also relates to a propulsion unit, comprising a nacelle according to the above, and a turbojet engine placed inside this nacelle.
• FIG. 1 is a view of an "O-Duct" nacelle of the prior art, as described in the preamble of the present description, in normal operating configuration;
• FIG. 2 is a view of this nacel the maintenance configuration
• FIG. 3 is a view in axial section of an actuator of the surrounding technology, evoked in the preamble of the present description
• FIGS. 4 and 5 are perspective views of a propulsion assembly comprising a nacelle according to the invention, comprising a rear part represented respectively in normal operating and maintenance positions
• FIG. 6 is a perspective view of the system. actuating the rear part of the nacelle of Figures 4 and 5, and
• FIG. 7 is a side view of one of the actuators of the actuating system of FIG. 6.
• upstream and downstream must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet, that is, from the left to the right of Figures 4 and 5.
• a propulsion system for aircraft comprising on the one hand a turbojet 15, and on the other hand a nacelle 17 enveloping the turbojet engine.
• FIGS. 4 and 5 only the rear part A of the nacelle is shown, but it must of course be understood that in fact the nacelle is intended to completely cover the turbojet engine 15.
• the turbojet engine 15 comprises in particular an upstream part 21 forming a fan casing, and a downstream part 23 forming the engine strictly speaking, in which the compression, combustion and ejection of the gases allowing the propulsion of the aircraft are carried out.
• the rear part of nacelle 25 may incorporate a thrust reversal function, for example of the grid type.
• the rear portion of nacelle 25 is slidably mounted between a normal operating position shown in Figure 4, and a maintenance position shown in Figure 5, for performing ground maintenance operations: in this position, an operator can access in particular to the motor 23.
• the nacelle rear part 25 is monobloc, that is to say it is formed in one piece, and is slidably mounted by rails on a top beam 27.
• this is commonly referred to as an "O-Duct" type thrust reverser, as opposed to a “D-Duct” type thrust reverser, in which there has two rear half-parts each mounted sliding on an upper beam and a lower beam.
• the top beam 27 allows in particular the attachment of the propulsion unit to a suspension pylon, d isposé under the wing of an aircraft.
• two actuators 29a and 29b are positioned on either side of the top beam 27, and each interposed between the fan casing 21 and the nacelle rear part 25. .
• each actuator 29 comprises a support 33 on which a housing 35 is fixed.
• This nut is rotatably mounted inside the housing 35, but immobile in translation, as opposed to the actuator of the prior art.
• the actuator 29 further comprises a worm 37 (37a,
• the actuator according to the invention comprises a protective tube 45 fixed on the support 33, able to accommodate the entire length of the worm 39.
• the actuator according to the invention can be fixed substantially on the upstream edge of the rear part of nacelle 25, thus interfering with the structure of the latter at a minimum: this limits the interference of the actuator especially with the regions of this rear part of nacelle which are encumbered by other organs.
• the protection tube 45 serves to protect the worm 39 of the actuator, as well as to limit the vibrations when it is in the retracted position shown in FIG.
• the ball 43 thus drives the rear part of nacelle 25 towards its downstream position, being observed that in the position of maximum extension shown in FIG. 5, the distance separating the support 33 from the point of attachment of the worm 39 to the rear part of nacelle 25 is at most equal to the length of this screw, and not twice the length of this screw, unlike the actuator of the prior art mentioned in the preamble of the present description.

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

Applications Claiming Priority (2)

Publications (1)

Family

ID=47291115

Family Applications (1)

Country Status (8)

Families Citing this family (7)

Family Cites Families (9)

• 2011
  • 2011-11-24 FR FR1103589A patent/FR2983173B1/fr active Active
• 2012
  • 2012-11-12 BR BR112014012125A patent/BR112014012125A2/pt not_active IP Right Cessation
  • 2012-11-12 RU RU2014124908/11A patent/RU2014124908A/ru not_active Application Discontinuation
  • 2012-11-12 WO PCT/FR2012/052597 patent/WO2013093256A1/fr active Application Filing
  • 2012-11-12 CA CA2856210A patent/CA2856210A1/fr not_active Abandoned
  • 2012-11-12 EP EP12795520.1A patent/EP2782831A1/de not_active Withdrawn
  • 2012-11-12 CN CN201280057612.3A patent/CN103958349B/zh not_active Expired - Fee Related
• 2014
  • 2014-05-27 US US14/287,845 patent/US10047634B2/en active Active

Non-Patent Citations (1)

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