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
  • F02K1/06—Varying effective area of jet pipe or nozzle
  • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
  • F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed structure
• • 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
  • 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
• • 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
  • F02K1/06—Varying effective area of jet pipe or nozzle
  • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
• • 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

Definitions

• the invention relates to a nacelle for a turbojet engine of an aircraft comprising in downstream section a fixed internal structure intended to surround a part of the turbojet engine and an external structure at least partially surrounding the fixed internal structure so as to delimit an annular vein.
• 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 thrust reverser actuation system.
• a nacelle generally has a tubular structure along a longitudinal axis 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 thrust reversal means and intended to surround the chamber combustion of the turbojet engine.
• the tubular structure is generally terminated by an ejection nozzle whose outlet 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 hot air flow (also called “primary flow”) from the combustion chamber of the rboreactant. r, and a cold air flow (“secondary flow”) flowing outside the turbojet through an annular passage, also called “annular vein”.
• a turbofan engine capable of generating, through the blades of the rotating fan, a hot air flow (also called “primary flow”) from the combustion chamber of the rboreactant. r, and a cold air flow (“secondary flow”) flowing outside the turbojet through an annular passage, also called “annular vein”.
• downstream is understood here to mean the direction corresponding to the direction of the flow of cold air entering the turbojet engine.
• upstream refers to the opposite direction.
• Said annular vein is formed in downstream section by an external structure, called Outer Fixed Structure (OFS) and a concentric internal structure, called Inner Fixed Structure (IFS), surrounding the structure of the engine itself downstream of the fan.
• OFS Outer Fixed Structure
• IFS Inner Fixed Structure
• the internal and external structures belong to the downstream section.
• the outer structure may comprise one or more sliding hoods along the longitudinal axis of the nacelle the inter n u position allowing the escape of the inverted air flow and a position preventing such an exhaust.
• variable nozzle is formed of sliding movable elements and configured so as to allow a reduction of the ejection section of the air flow at the exit of the annular vein in order to optimize the section of the latter in depending on the flight phase in which the aircraft is located.
• said movable elements do not make it possible to obtain good aerodynamic quality of the secondary vein. Poor aerodynamic quality leads to an increase in the specific consumption and the noise of the propulsion unit comprising the turbojet engine and the nacelle.
• An object of the present invention is therefore to provide a nacelle whose ejection section of the cold air flow is variable by means not having the aforementioned drawbacks.
• the subject of the present invention is a nacelle for a turbojet engine of an aircraft comprising in downstream section a fixed internal structure intended to surround a part of the turbojet engine and an external structure surrounding at least one in part the internal structure fixed so as to define an annular vein, the external structure comprising at least one inner flap disposed facing the annular vein, an outer flap not in contact with the annular vein overlying at least partially each inner flap in continuity aerodynamic with the rest of the external structure, and an intermediate flap disposed between each inner flap and each outer flap, said intermediate flap being movable in translation so as to enlarge or reduce the section of the annular vein, and each inner flap and each outer flap being movable in rotation so as to remain in constant contact with the v olet intermediate in all positions of the latter.
• Each intermediate flap is mounted inside the external structure between an inner flap and an outer flap.
• the intermediate flap is deployable between a nominal position corresponding to the normal operating position of the nacelle, an extended position corresponding to the position enlarging the section of the annular vein and a retracted position corresponding to the position decreasing the section of the annular vein .
• the outer flap remains in constant contact with the intermediate flap.
• the association of the intermediate and outer movable flaps while remaining in constant contact makes it possible to vary the outlet section of the ejection nozzle by changing the shape of the trailing edge of the downstream part of the external structure of the secondary vein. .
• the secondary vein then has a very good aerodynamic quality.
• the nacelle of the invention comprises one or more of the following optional features considered alone or according to all the possible combinations:
• At least one intermediate flap is movable in translation through a slide or rollers cooperating with a rail system belonging to a frame supporting said intermediate flap which allows to move simply and reliably each intermediate flap;
• At least one intermediate flap is set in motion by one or more electric or hydraulic cylinders which allows a simple and effective way to set in motion each intermediate flap;
• the frame associated with an intermediate flap is movable relative to the external structure which allows to drive all the intermediate flap and reduce the effort to the frame;
• the frame is movable in translation by means of one or more cylinders along an axis substantially collinear with a longitudinal axis of the nacelle and the translational movement is transmitted to the intermediate flap by a connecting rod system;
• the frame is rotatable by means of one or more cylinders about an axis substantially collinear with a longitudinal axis of the nacelle and the movement is transmitted to the intermediate flap via a hinge system, in particular one or more horns;
• each inner flap and each outer flap are in permanent contact with the intermediate flap by means of a rail system or a spring system which allows permanent and reliable contact of the intermediate flap with the outer and inner flaps;
• each inner flap, each outer flap and each intermediate flap comprise contact surfaces coated with an anti-friction coating, which makes it possible to avoid wear of the flaps.
• FIG. 1 is a partial schematic section of an embodiment of a nacelle of the invention
• FIG. 2 is a diagrammatic longitudinal section of a downstream section of an embodiment of a nacelle of the invention in which the inner, outer and intermediate flaps are in the nominal position;
• FIG. 3 is a perspective view of the embodiment of FIG. 2;
• FIG. 4 is a perspective view of the rear of the nacelle according to the embodiment of Figure 2;
• FIG. 5 is a schematic longitudinal section of a downstream section of an embodiment of a nacelle of the invention wherein the inner, outer and intermediate flaps are in the retracted position;
• FIG. 6 is a perspective view of the embodiment of FIG. 5;
• FIG. 7 is a perspective view of the rear of the nacelle according to the embodiment of Figure 5;
• FIG. 8 is a schematic longitudinal section of a downstream section of an embodiment of a nacelle of the invention wherein the inner, outer and intermediate flaps are in the deployed position;
• Fig. 9 is a perspective view of the embodiment of Fig. 8.
• FIG. 10 is a perspective view of the rear of the nacelle according to the embodiment of FIG. 8;
• FIG. 1 1 is a schematic section of an embodiment of the actuation of the intermediate flap of the nacelle of the invention
• FIG. 12 is a diagrammatic section of a variant of the embodiment of FIG.
• a nacelle 1 As represented in FIG. 1, a nacelle 1 according to the invention has a substantially tubular shape along a longitudinal axis ⁇ .
• the nacelle of the invention 1 comprises an upstream section 2 with an inlet lip 13 of air forming an air inlet 3, a median section 4 surrounding a fan 5 of a turbojet engine 6 and a downstream section 7
• the downstream section 7 comprises an internal structure 8 (generally called "IFS") surrounding the the upstream part of the turbojet engine 6, an external structure (OFS) 9 capable of supporting a movable cowl comprising means of thrust reversal.
• IFS internal structure surrounding the upstream part of the turbojet engine 6
• OFFS external structure
• IFS 8 and OFS 9 defines an annular vein 10 allowing the passage of an air flow 12 penetrating the nacelle 1 of the invention at the level of the air inlet 3.
• the nacelle 1 of the invention ends with an ejection nozzle 21 comprising an external module 22 and an internal module 24.
• the internal and external modules 24 24 define a flow channel of a hot air flow 25 exiting turbojet engine 6.
• the OFS 9 comprises at least one inner flap 101 arranged facing the annular vein 10, an external flap 103 not in contact with the annuliary vein 10 at least partially covering each flap internal 101 in aerodynamic continuity with the rest of the OFS 9.
• An intermediate flap 105 is disposed between each inner flap 101 and each outer flap 1 03. Said intermediate flap 105 is movable in translation so as to enlarge or reduce the section of the annular vein 1 0.
• the outer flap 103 and the inner louver 1 01 associated with it are rotatable so as to remain in permanent contact with the intermediate flap 105 in all positions thereof.
• the nacelle 1 of the invention comprises as many internal flaps 101 as external flaps 103 and intermediate flaps 105.
• the nacelle 1 of the invention may thus comprise a plurality of internal flaps 101 each associated with an outer flap 103 and to an intermediate flap 105.
• the flaps 101, 103, and 105 are distributed over the circumference of said nacelle 1.
• Each outer flap 1 03 pivots about a pivot axis
• pivot axis 109 fixed relative to the OFS 9, said pivot axis 109 being contained in a radial plane substantially perpendicular to the longitudinal axis ⁇ of the nacelle 1 of the invention
• Each inner flap 101 rotates relative to the OFS 9 around an axis substantially collinear with the pivot axis 109 of the outer flap.
• Each intermediate flap 105 is movable along a trajectory indicated in dotted line 1 07 in FIGS. 2, 5 and 8.
• said trajectory 1 07 of the intermediate flap is substantially collinear with the longitudinal direction of the vein an n ul 1 0.
• "Longitudinal direction" here means the direction substantially collinear with the IFS 8 when it extends from upstream to downstream to the zone of the widest IFS 8.
• Each intermediate flap 105 is deployable between a nominal position (FIGS. 2 to 4) corresponding to the normal operating position of the nacelle 1 of the invention, an extended position corresponding to the position enlarging the section of the annular duct 10 (see FIGS.
• each outer flap 103 remains in permanent contact with the intermediate flap 105 associated therewith.
• the association of the intermediate flaps 105, internal 110 and outer 103 moving while remaining in constant contact allows to vary the outlet section of the exhaust nozzle by changing the shape of the trailing edge of the downstream portion of SFO 9 of the secondary vein.
• the secondary vein 10 then has a very good aerodynamic qual ity i u i can improve the specific consumption and reduce the noise generated by the propellant comprising the turbojet engine 6 and nacelle 1 of the invention.
• the intermediate flap 105 is in nominal position corresponding to the configuration of the downstream section of the OFS 9 when the nacelle 1 of the invention is in the cruising position, namely not at the landing, takeoff or acceleration phase.
• the section of the annular vein 10 has a nominal height h 0 .
• the intermediate section 105 is in the retracted position corresponding to the reduction configuration of the section of the annular passage 10.
• the cross r h height of the annular flow path 10 is less than at nominal height h 0 .
• This position corresponds to the configuration where the powertrain generates a high thrust, especially when the aircraft is downhill.
• the outer flap 101 and the inner flap 101 rest at their free end 120 and 1 21 on the surface of the intermediate shutter 105, close to or on the free end 122 of said intermediate flap. 105.
• the outer flap 1 03 and the inner flap 1 01 pivot about their axis 109 concomitantly with the movement downstream of the intermediate flap 105 out of the OFS 9.
• the intermediate section 105 is in the deployed position corresponding to the configuration of increasing the section of the annular passage 10.
• the cross r h height of the annular flow path 10 is greater than the nominal height h 0 .
• This position corresponds to the configuration where the nacelle 1 of the invention has an output section of the maximum annular vein 10 corresponding to a strong thrust of the propulsion unit, especially at takeoff.
• the outer flap 101 and the inner flap 101 are at their free end 120 and 211 on the surface of the intermediate shutter 105, long distance from the free end 122 of said intermediate flap.
• outer flap 101 and the inner flap 101 pivot about their axis 109 concomitantly with the displacement upstream of the intermediate flap 105 towards the inside of the OFS 9.
• the intermediate flap 105 may be movable in translation by means of a slideway 130 or rollers co-operating with a system of rails 132 belonging to a frame 134 supporting said intermediate flap 105, which makes it possible to simply and reliably move each intermediate flap 105 (see figures 3, 6 and 9).
• the rail has a direction substantially collinear to the trajectory 107 of the intermediate flap.
• the position of the slide or the roller in the rail allows an advance of the intermediate flap 105 or a decline of the latter along the path 107.
• the frame 1 34 of the intermediate flap can be fixed on the OFS 9, in particular on a fixed flap 101.
• the intermediate flap 105 can be moved in a simple and effective way and autonomously by one or more electric or hydraulic cylinders (not shown).
• the associated frame 134 to one or intermediate flaps 105 may also be movable relative to the OFS 9 which allows to drive the or all the intermediate flaps 105.
• the frame 134 can be movable in translation by means of one or more cylinders 140 along an axis substantially collinear with a longitudinal axis ⁇ of the nacelle 1 of the invention and the movement of translation is transmitted to the associated intermediate flap 105 by a connecting rod system 142.
• the frame 1 34 may be rotatable by means of one or more jacks 150 about an axis substantially collinear with a longitudinal axis ⁇ of the nacelle 1 of the invention and the movement is transmitted to the flap intermediate 105 associated via a hinge system, including one or more puppets 152.
• Each inner flap 1 01 and each outer flap 103 is in permanent contact with the intermediate flap 105 associated via a rail system or a spring system (not shown) which allows i permanent and reliable contact flap intermediate with the inner and outer flaps.
• Means for ensuring the permanent contact of said inner flaps 1 01 and outer 1 03 movable with the intermediate flap 1 05 may be to install one or more springs type torsion bar in the joint of each inner flap 1 01 and external 1 03 moving in rotation. These springs generate a strong continuous pressure of the inner and outer flaps 101 and 103 on the intermediate flap 105.
• the inner flap 101, the outer flap 103 and the intermediate flap 105 may comprise contact surfaces coated with an anti-friction coating which makes it possible to avoid wear of the two flaps 105 and 103.
• An anti-friction coating is PTFE (called “Teflon”) or the like.
• the section of the annular duct 10 has a height h 0 allowed by the position of each intermediate flap 105 whose free end 122 exceeds that of the inner flaps 110 and external 01 03 that i i lu associates.
• the intermediate flap 105 is set in motion along the path 107 downstream of the flaps 101 and 103 so that the free end 122 passes further. that of the inner shutters 1 01 and external 103 associated with it. Each intermediate flap 105 is therefore in the deployed position.
• the intermediate shutter 1 05 is set in motion along the path 1 07 upstream of the flaps 1 01 and 1 03 to the inside of the OFS 9 so that the free end 122 is near or under that of the outer panel 103 associated with it.
• Each intermediate flap 105 is in the retracted position.

Landscapes

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

Applications Claiming Priority (2)

Publications (1)

Family

ID=44115615

Family Applications (1)

Country Status (8)

Families Citing this family (4)

Family Cites Families (10)

• 2010
  • 2010-11-16 FR FR1059393A patent/FR2967399B1/fr active Active
• 2011
  • 2011-10-28 WO PCT/FR2011/052543 patent/WO2012066210A2/fr active Application Filing
  • 2011-10-28 RU RU2013126749/06A patent/RU2013126749A/ru not_active Application Discontinuation
  • 2011-10-28 BR BR112013010648A patent/BR112013010648A2/pt not_active IP Right Cessation
  • 2011-10-28 EP EP11831835.1A patent/EP2640952A2/de not_active Withdrawn
  • 2011-10-28 US US13/640,119 patent/US9243587B2/en not_active Expired - Fee Related
  • 2011-10-28 CA CA2816255A patent/CA2816255A1/fr not_active Abandoned
  • 2011-10-28 CN CN201180055102.8A patent/CN103210200B/zh not_active Expired - Fee Related

Non-Patent Citations (1)

Also Published As

Similar Documents

Legal Events