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
  • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
  • B64D33/04—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• • 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
  • F02K1/06—Varying effective area of jet pipe or nozzle
  • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
• • 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
  • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
  • F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
• • 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
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T137/00—Fluid handling
  • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Definitions

• the invention relates to a jet engine nacelle for an aircraft.
• 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 may comprise in particular a mechanical system for actuating thrust reversers.
• a nacelle generally has a tubular structure comprising an air inlet in front of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a rear section housing 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.
• Modern nacelles are often 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 turbojet engine.
• a nacelle generally has an external structure, called Outer Fixed Structure (OFS), which defines, with a concentric internal structure of the rear section, called Inner Fixed Structure (IFS), surrounding the structure of the turbojet itself behind the fan, an annular flow channel, also called a secondary vein, for channeling a cold air flow, said secondary, which circulates outside the turbojet engine.
• OFS Outer Fixed Structure
• IFS Inner Fixed Structure
• the object of the present invention aims to remedy this problem, and consists of a turbojet engine nacelle comprising a rear section having an internal structure intended to surround a rear part of a engine compartment and to delimit, with a ejection nozzle, a calibrated outlet section of the ventilation of the engine compartment by means of spacing means arranged in the outlet section, characterized in that the spacing means are decomposed into rigid spacing means designed to ensure a constant spacing, and compensation means designed to be able to adapt to the relative movements of the turbojet relative to the nacelle.
• the compensation means are designed to form a valve.
• the spacing means can thereby adapt to an increased pressure occurring in the engine compartment.
• the compensation means may be arranged to disappear under the action of this increased pressure, so that an additional passage will be opened to increase the ejected air flow.
• the rigid spacing means are fixed in the internal structure.
• the rigid spacing means are fixed in the ejection nozzle.
• the rigid spacing means comprise a plurality of U-shaped elements forming spacers distributed over the periphery of the outlet section.
• the second free end of each element is pressed against the ejection nozzle.
• the second free end of each element is pressed against the internal structure.
• the present invention also relates to an aircraft, characterized in that it comprises at least one nacelle according to the invention.
• Figure 1 is a schematic longitudinal sectional view of a nacelle according to the invention in the closed state
• Figure 3 is an enlarged schematic view of the exit section from the rear of the nacelle shown in Figure 2;
• Figure 4 is a partial schematic view from the front of the outlet section shown in Figure 3;
• Figure 6 is a schematic view similar to Figure 5, during an increase in pressure in the combustion chamber of the turbojet engine.
• a nacelle 1 of an aircraft according to the invention comprises, in a manner known per se, a front air intake section 2, a median section 3 intended to surround the fan 4, and a rear section 5 for surrounding a motor compartment (not shown) and terminated by an ejection nozzle 6 whose output is located behind the turbojet engine.
• This nacelle 1 comprises an external structure 7, called OFS, which defines an annular flow channel 8 with a concentric internal structure 9, called IFS, surrounding the structure of the turbojet itself behind the fan 4.
• OFS external structure 7
• IFS concentric internal structure 9
• the internal structure 9 and the ejection nozzle 6 delimit an outlet section 10 of the ventilation of the engine compartment which can be used to recovering part of the thrust lost by the air taken from the annular channel 8 by the geometric control of the air flow passage surface.
• spacing means made of metal, in particular of titanium, are arranged in the outlet section 10.
• spacing means are decomposed into rigid spacing means 11, 12 designed to ensure a constant spacing, and compensation means 13 designed to be able to adapt to the relative movements of the turbojet engine relative to the platform 1 .
• the rigid spacing means 11, 12 are made using a plurality of U-shaped elements in section, and forming spacers.
• the rigid spacing means 11 are arranged in such a way that the free branches of the U are parallel to the axis 14 of the nacelle 1, and directed towards the front.
• the rigid spacing means 12 are positioned in such a way as to be positioned in a plane transverse to the axis 14 of the nacelle 1.
• the rigid spacing means 11, 12 are uniformly distributed in the same plane on the periphery of the outlet section 10, so that a rigid spacing means 12 is interposed between two rigid spacing means 11, as more specifically shown in Figures 3 and 4.
• the rigid spacing means 11, 12 are each fixed by riveting in the internal structure 9, as shown schematically in FIG. 5 under the reference 20.
• the spaces between the different rigid spacing means 11, 12 thus define passages allowing calibrated ventilation at the outlet section 10.
• each rigid spacing means 12 which also defines a passage allowing calibrated ventilation at the outlet section 10.
• the compensation means 13 are made in the form of a ring 15 comprising a plurality of longitudinal slots 16 forming longitudinal fingers 17 parallel to the axis 14.
• This ring 15 is fixed by means of rivets 18 in each of the rigid spacing means 11, 12 at the front end of each finger 17, and the free rear end thereof is resting on the outer face of the ejection nozzle 6.
• the spacing means 11 have in particular the function of making stops in case of strong relative displacements of the motor relative to the nacelle 1, in addition to maintaining the front end of each finger 17.
• the spacing means 12 have their function to maintain the front end of each finger 17, while not obstructing the ventilation outlet 10.
• This finger 17 is designed so that, once the ring 15 fixed in the rigid spacing means 11, 12, it is necessary to radially spread the second portion 17b in order to be able to press against the nozzle of ejection 6. Each finger 17 is then constantly under tension, the second portion 17b tends to recover its rest position shown schematically in phantom in Figure 5.
• these fingers 17 are designed to form a valve. This is a considerable advantage insofar as the compensation means 13 can thus adapt to an increase in pressure occurring in the engine compartment, as shown in FIG. 6. Indeed, the second portion 17b of each finger 17 may deviate radially from the ejection nozzle 6 under the action of this increased pressure, so that an additional passage, marked by the arrow, is open to increase the flow of ejected air.

Landscapes

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

Applications Claiming Priority (2)

Publications (1)

Family

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Family Applications (1)

Country Status (8)

Families Citing this family (10)

Family Cites Families (33)

• 2007
  • 2007-08-20 FR FR0705920A patent/FR2920146B1/fr not_active Expired - Fee Related
• 2008
  • 2008-06-19 US US12/674,237 patent/US8875518B2/en not_active Expired - Fee Related
  • 2008-06-19 RU RU2010109801/11A patent/RU2469923C2/ru not_active IP Right Cessation
  • 2008-06-19 EP EP08828022A patent/EP2181041A1/de not_active Withdrawn
  • 2008-06-19 CN CN200880102592.0A patent/CN101784449B/zh not_active Expired - Fee Related
  • 2008-06-19 WO PCT/FR2008/000859 patent/WO2009024660A1/fr not_active Ceased
  • 2008-06-19 BR BRPI0813603 patent/BRPI0813603A2/pt not_active IP Right Cessation
  • 2008-06-19 CA CA2696792A patent/CA2696792C/fr not_active Expired - Fee Related

Non-Patent Citations (2)

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