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
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
• • 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
  • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
  • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
  • B64D15/04—Hot gas application
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
  • F02C7/047—Heating to prevent icing
• • 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
  • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B64D2033/0233—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
• • 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

• Air intake structure adapted to be mounted upstream of a medial nacelle structure for an aircraft engine, and nacelle equipped with such an air intake structure
• the present invention relates to an air intake structure capable of being mounted upstream of a median nacelle structure for an aircraft engine, and to a nacelle equipped with such an air intake structure.
• a nacelle 1 for an aircraft engine comprising an air intake structure 3 capable of being mounted upstream of a median structure 5, said air inlet structure 3 comprising in particular:
• At least one defrost collector 15 extending into said compartment 13, and
• Document FR2757823 discloses the principle of a hot air supply pipe of a de-icing compartment, comprising a part mounted on the fixed median structure of the nacelle, and a portion mounted on the movable air inlet structure, these two parts of tubing being connected in a disconnectable manner to one another.
• this device of the prior art has the disadvantage of substantially increase the mobile part of the air intake structure.
• the present invention aims to reduce all of the aforementioned disadvantages.
• an air intake structure capable of being mounted upstream of a median nacelle structure for an aircraft engine, said air intake structure comprising in particular:
• At least one hot air supply duct of said collector able to be fixedly connected to said median structure, structure in which said partition is sealingly secured inside said lip, and said supply duct; is connected to said collector by means of disconnectable waterproof means, this structure being remarkable in that said disconnectable sealed means are located in the immediate vicinity of said partition.
• the partition ensures a perfect seal of the deicing compartment
• the disconnectable sealed means provide a sealed fluid communication between the hot air supply duct and the collector, and because of the immediate proximity of these sealing means disconnectable with the partition, the length of the hot collector is reduced to a minimum, so that the overweight brought by this collector to the movable part (outer wall + defrost collector + partition) of the air inlet structure, is also minimal.
• the replacement cost of this movable part of the air intake structure is also minimal.
• the internal face of said air intake structure is able to be fixedly mounted on said median structure: this particular embodiment corresponds to that described in the above-mentioned patent application, in which this internal face is in fact a cylindrical wall provided with a noise absorption structure;
• this particular embodiment also corresponds to one of those described in said patent application, and allows an easy movement of the internal structure between its rear positions (operation normal) and before (maintenance);
• disconnectable sealed means comprise male and female collector and feed pipe ends, or vice versa, and sealing means such as at least one seal mounted on or inside these ends: these male ends and females allow quick connection / disconnection of the supply line to the defrost collector without adjustment of diameter and length dimensions. This allows a good tolerance to manufacturing differences of the different parts involved;
• said female end has a funnel shape: this particular shape makes it possible to guide the male end into the female end during the connection;
• this particular embodiment is of a particularly simple design
• said partition defines a housing around said collector end, sealing means such as seals being interposed on the one hand between this collector end and the end of said supply duct, and on the other hand between said partition and this end of the supply duct: in the event of leakage of the sealing means interposed between the collector end and the end of the supply duct, the hot air remains confined in the housing and therefore does not spread not downstream of the partition;
• said partition defines an orifice traversed in a non-leakproof manner by said collector end, sealing means such as seals being interposed on the one hand between this collector end and the end of said supply duct, and on the other hand between the edges of said orifice and this end of the supply duct: in the event of leakage of the sealing means interposed between the collector end and the end of the supply duct, the hot air remains confined in the deicing compartment, and therefore does not spread not downstream of the partition;
• said supply duct comprises a double wall: such a double wall makes it possible to prevent the hot air circulating in the duct from escaping into the zone located downstream of the partition in the event of bursting of the internal wall; of this conduit;
• said feed duct comprises at its end at least one communication orifice between said housing and the space situated between the two duct walls: this orifice makes it possible to avoid the pressurization of this housing in the event of leakage by the means of sealing located between the end of the collector and the end of the supply duct, and thus to avoid the risk of leakage by the sealing means located between the housing and the end of the supply duct;
• this air intake structure comprises an air leakage detector disposed in the space between the two walls of the supply duct: this detector makes it possible to signal any hot air leakage at the means of sealing located between the end of the collector and the end of the supply duct.
• the present invention also relates to an aircraft engine nacelle, remarkable in that it comprises an air intake structure according to the foregoing.
• FIG. 1 represents in perspective a nacelle of the state of the art, described in the preamble of the present description, suspended under an aircraft wing 23 by means of a pylon 24,
• FIGS. 2 and 3 show views in axial section, that is to say taken along the plane P of FIG. 1, of the upper part of the air intake structure of this nacelle of the state. of the art, in respective positions of normal operation and maintenance, FIGS. 4 and 5 are views similar to FIGS. 2 and 3 of a first embodiment of an air intake structure according to the invention,
• FIG. 6 is a partial view of a supply duct of this air intake structure
• FIGS. 7 and 8 are views similar to FIGS. 2 and 3 of a second embodiment of an air structure according to the invention.
• FIG. 9 is a view similar to that of FIG. 7 of a variant of this second embodiment.
• FIGS. 10 and 11 are similar views respectively to FIGS. 2 and 3 of a third embodiment of an air structure according to the invention.
• FIGS. 12 and 13 are views similar respectively to FIGS. 2 and 3 of a fourth embodiment of an air intake structure according to the invention.
• FIG. 14 is an axial view of the method of attaching a defrost collector end to a partition of the air intake structure shown in FIGS. 12 and 13.
• the air intake structure according to the invention comprises an external wall 7 incorporating a lip 9.
• the lip 9 is the part of the air inlet structure located furthest upstream, that is to say the part of this air intake structure which constitutes in a way the leading edge. .
• the assembly formed by the outer wall 7 and its lip 9 is slidably mounted between a rear position shown in FIG. 4 and a front position represented in FIG. 5, with respect to a structure fixed median 5 of the nacelle (not visible in Figures 4 and 5).
• the normal operating configuration is that of FIG. 4, the configuration of FIG. 5 being a maintenance configuration making it possible to access in particular the stationary median structure 5 of the nacelle.
• the air intake structure according to the invention also comprises an internal wall 25, mounted in a fixed manner on the median structure 5.
• the fixed inner wall 25 comprises an acoustic treatment, that is to say that it can be covered by a honeycomb structure capable of reducing noise emissions.
• a defrost collector 15 able to circulate inside this lip of the hot air from a supply duct 17 itself connected to a source of heat. hot air mounted fixed relative to the median structure 5.
• a partition 11 defines the de-icing compartment 13, inside which the manifold 15 extends.
• This partition is sealed, for example by riveting, inside the lip 9.
• the collector 15 comprises at least one end 27 passing through the partition 11 in a sealed manner, this end 27 being able for example to be welded at its periphery to the partition 11.
• This end 27 comprises sealing means 29, and is able to penetrate inside a funnel-shaped female portion 31 forming the end of the hot air supply duct 17.
• sealing means used in the context of this invention refers to any sealing system capable of resisting the high temperatures of the hot air flowing in the duct 17 (typically of the order of 500 0 C), and sliding tolerant.
• These sealing means may in particular be formed by seals made of suitable materials.
• the male end 27 of the collector 15 is disengaged from the female end 31 of the duct 17.
• the conduit 17 preferably comprises an inner wall 17a and an outer wall 17b, so as to limit the risk of hot air escaping inside the cavity 21 in the event of explosion of the diaphragm 7a .
• the funnel shape of the end 31 of the duct 17 can be formed on the outer wall 17b of the duct 17, thus allowing a gain in duct diameter as well as by weight .
• the partition 11 defines a housing 33 around the end 31 of the conduit 17, the second sealing means 35 sealing this housing with respect to the cavity 21, when the air intake structure is in normal operating configuration.
• This particular arrangement makes it possible to contain inside the housing 33 a possible hot air leakage due to a poor sealing of the sealing means 29.
• This orifice 37 makes it possible to avoid the pressurization of the housing 33 in the event of leakage by the sealing means 29; this makes it possible to limit the risk of leakage of this air by the second sealing means 35 towards the cavity 21.
• FIGS. 10 and 11 differs from the previous ones in that it is the end 27 of the collector 15 which has a funnel-shaped shape, the end 31 of the duct 17 presenting in turn a straight shape: in this embodiment, the ends 27 of the manifold 15 and 31 of the duct 17 respectively constitute the female and male parts of this disconnectable leaktight connection.
• the sealing means 29 sealing this connection are in this case preferably arranged around the end 31 of the duct ⁇
• the end 27 of the collector 5 is no longer connected to the partition 11, but passes in an unsealed manner through an orifice 45 formed in this partition 11.
• the end 27 of the manifold 15 may be connected to the partition 11 by brackets 47 or adjustable tie rods arranged at 120 °, as shown in FIG.
• First sealing means 29 are interposed between the male end 27 of the manifold 15 and the female end 31 of the conduit 17, and second sealing means 35 are interposed between this female end 31 and a return 47 formed in the partition 11.
• connection zone between the end 27 of the collector 15 and the end 31 of the conduit 17 is preferably located at immediate proximity, or even in the plane of the partition 11: this allows to limit the overall weight of the moving parts, that is to say parts likely to move with the outer wall 7, during its movement between its position of normal operation and its maintenance position.
• the disconnectable nature of the connection between the male and female ends (or vice versa) of the collector 15 and the duct 17 makes it possible to dispense with a dimension adjustment in diameter and in length: this therefore allows a good tolerance to manufacturing differences in the different parts involved.
• the present invention is not limited to the embodiments described and shown, provided as a simple example.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Aviation & Aerospace Engineering (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
• Centrifugal Separators (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=39400863

Family Applications (1)

Country Status (8)

Families Citing this family (18)

Family Cites Families (6)

• 2007
  • 2007-10-08 FR FR0707049A patent/FR2921901B1/fr not_active Expired - Fee Related
• 2008
  • 2008-08-28 EP EP08846454A patent/EP2197743A2/de not_active Withdrawn
  • 2008-08-28 BR BRPI0818497 patent/BRPI0818497A2/pt not_active IP Right Cessation
  • 2008-08-28 CN CN200880108535A patent/CN101855135A/zh active Pending
  • 2008-08-28 CA CA2700087A patent/CA2700087A1/fr not_active Abandoned
  • 2008-08-28 US US12/681,994 patent/US8800258B2/en not_active Expired - Fee Related
  • 2008-08-28 RU RU2010117280/11A patent/RU2486106C2/ru not_active IP Right Cessation
  • 2008-08-28 WO PCT/FR2008/001208 patent/WO2009060137A2/fr not_active Ceased

Non-Patent Citations (1)

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