US20140086678A1 - Assembly for an aircraft nacelle - Google Patents
Assembly for an aircraft nacelle Download PDFInfo
- Publication number
- US20140086678A1 US20140086678A1 US14/093,761 US201314093761A US2014086678A1 US 20140086678 A1 US20140086678 A1 US 20140086678A1 US 201314093761 A US201314093761 A US 201314093761A US 2014086678 A1 US2014086678 A1 US 2014086678A1
- Authority
- US
- United States
- Prior art keywords
- flange
- reinforcing plate
- beveled
- plate
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 76
- 239000002131 composite material Substances 0.000 claims description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 239000010936 titanium Substances 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims description 3
- 239000011324 bead Substances 0.000 description 8
- 230000007704 transition Effects 0.000 description 5
- 239000004744 fabric Substances 0.000 description 3
- 239000000835 fiber Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000001413 cellular effect Effects 0.000 description 2
- 238000001802 infusion Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000004005 microsphere Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000001721 transfer moulding Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/70—Treatment or modification of materials
- F05D2300/702—Reinforcement
-
- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
- F16B2200/50—Flanged connections
-
- 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
- FIG. 1 Such a shroud is illustrated in FIG. 1 and designated by reference 10 .
- This inner shroud 10 of the air inlet structure is traditionally treated to form a sound attenuation structure 11 for the sound wave.
- the connecting flange 30 comprises a first part 31 extending in a radial direction and a second part 32 extending in the longitudinal direction of the turbojet engine, such that the longitudinal section of the flange 30 is L-shaped.
- the second connecting part 32 of the flange 30 corresponding to the inner shroud 10 of the air inlet structure is intended to be fixed on said shroud 10 .
- the flange 30 is generally made by draping pre-impregnated fabrics with autoclave curing, in dry fabrics or with a woven preform with injection of the Resin Transfer Molding type or by infusion.
- a reinforcing plate 33 may be connected on one and/or the other of the flanges, here the flange 30 corresponding to the inner shroud 10 .
- This reinforcing plate 33 makes it possible to meet the structural strength requirements of the connecting flange 30 .
- This bead 320 forms an abrupt local thickness variation, typically 0.5 mm, which causes a variation in the fiber level and the orientation of those fibers of the composite material forming the flange 30 .
- the stiffness variation between the flange part 30 and the shroud 10 may, in the case of a radial force applied on the flange 30 , create a weak spot at the shroud part at the flange 30 /shroud 10 transition.
- the present disclosure provides an assembly for an aircraft nacelle, comprising:
- a bead is prevented from being created on the second part of the flange, and the physical health of the composite is thereby improved.
- this beveled shape allows a less abrupt stiffness transition between the flange and the shroud on which it rests and improves the mechanical strength of the shroud in the junction area with the flange under radial bias.
- the assembly according to the present disclosure may comprise one or more of the following features, considered alone or in any technically possible combination:
- FIG. 1 is a partial cross-sectional view of an assembly of an air inlet structure and fan casing according to the prior art
- FIG. 2 is a partial cross-sectional view of the assembly of FIG. 1 at the interface between a flange of the assembly and a reinforcing plate of that flange;
- FIG. 4 is a partial cross-sectional view of a flange according to a second form of the present disclosure, said flange being able to be used in an assembly as shown in FIG. 1 ;
- FIG. 5 is a partial cross-sectional view of a flange according to a third form of the present disclosure, said flange being able to be used in an assembly as shown in FIG. 1 ;
- the present disclosure relates to an assembly for an aircraft nacelle comprising:
- a first form of the present disclosure is described with the help of FIG. 3 .
- the reinforcing plate 330 comprises a beveled end part 331 , which is in direct contact with the second part 32 of the flange 30 .
- the reinforcing plate 332 may be manufactured in the same way as the reinforcing plate 330 of the first form and comprise identical components.
- the intermediate plate 36 typically has a thickness comprised between 0.1 and 3 mm.
Abstract
An assembly for an aircraft nacelle includes a reinforcing plate and a flange that includes one first portion and one second portion. The first portion of the flange is attached to another flange, and the second portion extends transversely relative to the first portion and is attached onto a panel of the assembly. In particular, the reinforcing plate is attached directly, or optionally indirectly, onto the flange via an intermediate plate attached between the reinforcing plate and the flange. The reinforcing plate has a beveled portion opposite the second portion of the flange.
Description
- This application is a continuation of International Application No. PCT/FR2012/051123, filed on May 21, 2012, which claims the benefit of
FR 11/54685, filed on May 30, 2011. The disclosures of the above applications are incorporated herein by reference. - The present disclosure relates to an assembly including a flange and a reinforcing plate of that flange, intended for an aircraft nacelle.
- The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.
- An aircraft turbojet engine nacelle has a structure comprising an air inlet, a metal structure surrounding a fan of the turbojet engine, and a downstream section surrounding the turbojet engine and generally housing a thrust reverser system.
- Such an assembly can be used, non-limitingly, in mounting the air inlet and the midsection of the nacelle, as illustrated more particularly in
FIG. 1 . - The air inlet structure of the nacelle is divided into two zones, i.e. on the one hand an annular air inlet lip with an aerodynamic profile suitable for allowing optimal capture toward the turbojet engine of the air necessary to supply the fan and inner compressors of the turbojet engine, and on the other hand a downstream structure comprising an annular inner shroud and an annular outer cowl radially spaced away from the inner shroud, on which inner shroud the lip is attached and intended to channel the air suitably toward the fan.
- Such a shroud is illustrated in
FIG. 1 and designated byreference 10. Thisinner shroud 10 of the air inlet structure is traditionally treated to form asound attenuation structure 11 for the sound wave. - It may include an air-permeable inner skin, an air-impermeable outer skin and a honeycomb cellular core.
- Other alternatives can be considered, such as replacing the cellular core with porous foam or microspheres.
- In reference to
FIG. 1 as well, the midsection comprises aninner casing 20 surrounding the fan of the turbojet engine (not shown) extending theinner shroud 10 of the air inlet structure on the one hand, and an outer fairing structure (not shown) of the casing extending the outer shroud of the air inlet structure on the other hand. - The
inner shroud 10 is intended to be fixed to thefan casing 20 in a junction plane designated by the letter A, using peripheral connectingflanges inner shroud 10 and the upstream end of thefan casing 20, respectively. - In one form, the connecting
flange 30 comprises afirst part 31 extending in a radial direction and asecond part 32 extending in the longitudinal direction of the turbojet engine, such that the longitudinal section of theflange 30 is L-shaped. - The second connecting
part 32 of theflange 30 corresponding to theinner shroud 10 of the air inlet structure is intended to be fixed on saidshroud 10. - The
flange 30 is generally made by draping pre-impregnated fabrics with autoclave curing, in dry fabrics or with a woven preform with injection of the Resin Transfer Molding type or by infusion. - The connecting
flange 30 of theinner shroud 10 may be connected by any known fastening means and/or centering means making it possible to ensure centering of the two structures to be fixed together (not shown inFIG. 1 ) to the connectingflange 40 of thecasing 20 at the junction plane A, through theorifice 35. - Traditionally, a
reinforcing plate 33 may be connected on one and/or the other of the flanges, here theflange 30 corresponding to theinner shroud 10. - This reinforcing
plate 33 makes it possible to meet the structural strength requirements of the connectingflange 30. - It is suitable for shaping the corresponding flange, and in particular for defining the curve radius of the latter.
- It is also suitable for defining the stiffness of the
flange 30 over its entire circumference. - It also avoids unfolding of the plies of the
flange 30 in the radius when theshroud 10 is subjected to traction forces and damps the strains generated by the tightening of the fastening means. - However, as can be seen in
FIG. 2 , when thereinforcing plate 33 is attached to theflange 30, it generates abead 320 in theflange 30, situated at the side of thereinforcing plate 33. - This
bead 320 forms an abrupt local thickness variation, typically 0.5 mm, which causes a variation in the fiber level and the orientation of those fibers of the composite material forming theflange 30. - In extreme loading cases, this is detrimental to the mechanical strength of the
flange 30. - Furthermore, the stiffness variation between the
flange part 30 and theshroud 10 may, in the case of a radial force applied on theflange 30, create a weak spot at the shroud part at theflange 30/shroud 10 transition. - The present disclosure provides an assembly for an aircraft nacelle, comprising:
-
- a flange including at least one first part intended to be fixed to another flange and one second part extending transversely relative to the first part and intended to be fixed on a panel of said assembly, and
- a reinforcing plate attached directly on the flange or, optionally, indirectly using an intermediate plate fixed between the reinforcing plate and the flange, said reinforcing plate having a beveled part across from the second part of the flange.
- Owing to the present disclosure, a bead is prevented from being created on the second part of the flange, and the physical health of the composite is thereby improved.
- Furthermore, this beveled shape allows a less abrupt stiffness transition between the flange and the shroud on which it rests and improves the mechanical strength of the shroud in the junction area with the flange under radial bias.
- According to specific forms of the present disclosure, the assembly according to the present disclosure may comprise one or more of the following features, considered alone or in any technically possible combination:
-
- the beveled part of the reinforcing plate is an end part of that reinforcing plate, in contact with the second part of the flange;
- the beveled end part of the reinforcing plate assumes the form of an elongated bevel extending along the second part of the flange;
- the assembly comprises an intermediate plate, fixed between the flange and the reinforcing plate;
- the intermediate plate extends, at its end in contact with the second part of the flange, beyond the end part of the reinforcing plate;
- the intermediate plate is made from a composite material or a metal material, such as aluminum or titanium;
- the intermediate plate has a thickness comprised between 0.1 mm and 3 mm;
- the beveled part of the reinforcing plate is an end part of that plate;
- the reinforcing plate comprises:
- a first part attached against the first part of the flange,
- a second part, situated in the extension of the first part of the reinforcing plate and forming the beveled part of that reinforcing plate, said second part of the reinforcing plate being attached against the second part of the flange, and
- a third part, situated in the extension of the beveled part of the reinforcing plate and attached against the second part of the flange.
- the third part of the reinforcing plate has a thickness comprised between 0.1 mm and 3 mm.
- Further areas of applicability will become apparent from the description provided herein. It should be understood that the description and specific examples are intended for purposes of illustration only and are not intended to limit the scope of the present disclosure.
- In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:
-
FIG. 1 is a partial cross-sectional view of an assembly of an air inlet structure and fan casing according to the prior art; -
FIG. 2 is a partial cross-sectional view of the assembly ofFIG. 1 at the interface between a flange of the assembly and a reinforcing plate of that flange; -
FIG. 3 is a partial cross-sectional view of a flange according to a first form of the present disclosure, said flange being able to be used in an assembly as shown inFIG. 1 ; -
FIG. 4 is a partial cross-sectional view of a flange according to a second form of the present disclosure, said flange being able to be used in an assembly as shown inFIG. 1 ; -
FIG. 5 is a partial cross-sectional view of a flange according to a third form of the present disclosure, said flange being able to be used in an assembly as shown inFIG. 1 ; and -
FIG. 6 is a partial cross-sectional view of a flange according to a fourth form of the present disclosure, said flange being able to be used in an assembly as shown inFIG. 1 . - The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.
- The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.
- In general, and as shown in
FIGS. 3 to 6 appended hereto, the present disclosure relates to an assembly for an aircraft nacelle comprising: -
- a
flange 30 including at least afirst part 31 intended to be fixed to anotherflange 40 and asecond part 32 extending transversely relative to thefirst part 31 intended to be fixed on a panel of said assembly, and - a reinforcing
plate flange 30 or, optionally, indirectly by means of an intermediate plate 36 fixed between the reinforcingplate flange 30, said reinforcingplate second part 32 of theflange 30.
- a
- In another form, the
part 32 may be fixed on an acoustic panel of said assembly. - The beveled part of the reinforcing
plate flange 30, as shown inFIG. 2 , or to avoid the formation of such a bead. - The beveled shape further allows a better transition in the stiffness between the
flange 30 and the shroud panel on which it is fixed. - A first form of the present disclosure is described with the help of
FIG. 3 . - According to this first form, the reinforcing
plate 330 comprises abeveled end part 331, which is in direct contact with thesecond part 32 of theflange 30. - The fact that the
beveled end 331 of the reinforcingplate 330 is in contact with thesecond part 32 of theflange 30 limits the dimension of the bead as shown inFIG. 2 , that bead being able to be formed on thepart 32 when the reinforcingplate 330 is attached directly on theflange 30 and exerts pressure on theflange 30 to shape and define its radius of curvature. - The beveled shape allows a more gradual stiffness transition between the shroud and the
flange 30 and increases the mechanical strength in the transition area between theflange 30 and the shroud; - It should be noted that this reinforcing
plate 330 may be made from a composite material, independently from theflange 30. - To that end, the reinforcing
plate 330 may be produced by RTM injection, infusion or autoclave curing. - It is generally pre-cured, then attached on the
flange 30 on the plies of the flange that are not yet polymerized. - In non-limiting alternative forms, this reinforcing
plate 330 may comprise pre-impregnated plies, dry fabric, woven preforms or short fibers. - The reinforcing
plate 30 may also be metallic. - The reinforcing
plate 330 thus has a stiffness allowing it to perform its reinforcing function of theflange 30. - A second form of the present disclosure is described with the help of
FIG. 4 . - In the second form, the reinforcing
plate 332 has an end part that is also beveled, assuming the form of anelongated bevel 333 extending over the majority of the length of thesecond part 32 of theflange 30, or over the entire length of thesecond part 32 of theflange 30, directly in contact with theflange 30. - This
elongated shape 333 is advantageous inasmuch as it makes it possible to better distribute the effect of the pressure on thesecond part 32 of theflange 30, relative to the first form, the bead that may be formed when the reinforcingplate 332 is attached directly on theflange 30 is smaller, or is even eliminated. - The reinforcing
plate 332 may be manufactured in the same way as the reinforcingplate 330 of the first form and comprise identical components. - A third form of the present disclosure is described with the help of
FIG. 5 . - In this third form, the reinforcing
plate 330, which is identical to the reinforcing plate described in the first form, is no longer directly attached against theflange 30. - In fact, in this form, an intermediate plate 36 is provided, fixed between the
flange 30 and the reinforcingplate 330. - This intermediate plate 36 is an alternative form of the preceding solution, which may, depending on the materials chosen to produce the plate, be easier to produce.
- In this case, the intermediate plate 36 makes it possible to smooth the pressure applied on the plies of the
part 32 of theflange 30 by the reinforcing plate 330-331 during curing. - Advantageously, and as illustrated in
FIG. 5 , this intermediate plate 36 is attached against thefirst part 31 of the flange and extends at its end in contact with thesecond part 32 of theflange 30 beyond thebeveled end part 331 of the reinforcingplate 330. - This makes it possible to still better distribute the forces applied to the
flange 30, in this case to thesecond part 32 of theflange 30, by the reinforcingplate 330. - Thus, the intermediate plate 36 limits, or even eliminates, any punching phenomenon of the
flange 30 that could occur when the assembly formed by the intermediate plate 36 and the reinforcingplate 330 is attached on theflange 30. - In fact, the reinforcing
plate 330 and the intermediate plate 36 will generally be manufactured, then assembled to each other, before being attached together on theflange 30. - The intermediate plate 36 can be made from a composite material, for example with components identical to those of the reinforcing
plate 330. - In another form, this intermediate plate 36 may be made from a metal material such as aluminum or titanium.
- Furthermore, the intermediate plate 36 typically has a thickness comprised between 0.1 and 3 mm.
- A fourth form of the present disclosure is described with the help of
FIG. 6 . - This fourth form offers the advantages of the third form.
- However, in this fourth form, the reinforcing
part 334 has a shape comparable to the shape obtained, for the third form, once the reinforcingplate 330 and the intermediate plate 36 have been assembled. - Thus, the reinforcing
plate 334 comprises: - a
first part 335 attached against thefirst part 31 of theflange 30, - a
second part 336, situated in the extension of thefirst part 335 of the reinforcingplate 334 and forming the beveled part of that reinforcingplate 334, saidsecond part 336 of the reinforcingplate 334 being attached against thesecond part 32 of theflange 30, and - a
third part 337, situated in the extension of thebeveled part 336 of the reinforcingplate 334 and attached against thesecond part 32 of theflange 30. - Furthermore, the
third part 337 of the reinforcingplate 334 can have a thickness smaller than that of the first 335 and second 336 parts of the reinforcingplate 334. - Its thickness may be comprised between 0.1 and 3 mm, as is the case of the thickness of the intermediate plate 36 described in the third form.
- The reinforcing
plate 334 can be made in the same way as the reinforcingplate 330 of the first form and comprise the same components. - Of course, the present disclosure is in no way limited to the forms described and shown, provided purely as an example.
- Thus, for example, irrespective of the considered form, it should be noted that the present disclosure is not limited to L-shaped flanges, but may apply to other flanges having at least two parts that extend transversely relative to one another. This is for example the case of T-shaped flanges.
Claims (11)
1. An assembly for an aircraft nacelle, comprising:
a flange including at least one first part fixed to another flange and one second part extending transversely relative to the first part, the second part being fixed on a panel of said assembly; and
a reinforcing plate attached to the flange, said reinforcing plate having a beveled part across from the second part of the flange.
2. The assembly according to claim 1 , wherein the beveled part of the reinforcing plate is an end part of that reinforcing plate, in contact with the second part of the flange.
3. The assembly according to claim 2 , wherein the beveled end part of the reinforcing plate assumes a form of an elongated bevel extending along the second part of the flange.
4. The assembly according to claim 1 , wherein it further comprises an intermediate plate, fixed between the flange and the reinforcing plate.
5. The assembly according to claim 4 , wherein the intermediate plate extends, at its end in contact with the second part of the flange, beyond the end part of the reinforcing plate.
6. The assembly according to claim 4 , wherein the intermediate plate is made from a composite material or a metal material.
7. The assembly according to claim 6 , wherein the intermediate plate is made from aluminum or titanium.
8. The assembly according to claim 4 , wherein the intermediate plate has a thickness comprised between 0.1 mm and 3 mm.
9. The assembly according to claim 4 , wherein the beveled part of the reinforcing plate is an end part of that plate.
10. The assembly according to claim 1 , wherein the reinforcing plate comprises:
a first part attached against the first part of the flange;
a second part, situated in an extension of the first part of the reinforcing plate and forming the beveled part of that reinforcing plate, said second part of the reinforcing plate being attached against the second part of the flange; and
a third part, situated in an extension of the beveled part of the reinforcing plate and attached against the second part of the flange.
11. The assembly according to claim 10 , wherein the third part of the reinforcing plate has a thickness comprised between 0.1 mm and 3 mm.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1154685 | 2011-05-30 | ||
FR1154685A FR2975970B1 (en) | 2011-05-30 | 2011-05-30 | TOGETHER FOR AN AIRCRAFT NACELLE |
PCT/FR2012/051123 WO2012164197A1 (en) | 2011-05-30 | 2012-05-21 | Assembly for an aircraft nacelle |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/051123 Continuation WO2012164197A1 (en) | 2011-05-30 | 2012-05-21 | Assembly for an aircraft nacelle |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140086678A1 true US20140086678A1 (en) | 2014-03-27 |
Family
ID=46321144
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/093,761 Abandoned US20140086678A1 (en) | 2011-05-30 | 2013-12-02 | Assembly for an aircraft nacelle |
Country Status (8)
Country | Link |
---|---|
US (1) | US20140086678A1 (en) |
EP (1) | EP2714517B1 (en) |
CN (1) | CN103582597A (en) |
BR (1) | BR112013027790A2 (en) |
CA (1) | CA2837439A1 (en) |
FR (1) | FR2975970B1 (en) |
RU (1) | RU2013157084A (en) |
WO (1) | WO2012164197A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20150007905A1 (en) * | 2012-03-22 | 2015-01-08 | Aircelle | Method for manufacturing a one-piece preform for a composite structure |
EP3434597A1 (en) * | 2017-07-26 | 2019-01-30 | United Technologies Corporation | Nacelle |
US10767596B2 (en) | 2017-07-26 | 2020-09-08 | Raytheon Technologies Corporation | Nacelle |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110821583B (en) * | 2019-12-05 | 2022-06-17 | 中国航发四川燃气涡轮研究院 | Edge connecting structure of cartridge receiver barrel and cartridge receiver |
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- 2012-05-21 BR BR112013027790A patent/BR112013027790A2/en not_active IP Right Cessation
- 2012-05-21 CA CA2837439A patent/CA2837439A1/en not_active Abandoned
- 2012-05-21 WO PCT/FR2012/051123 patent/WO2012164197A1/en active Application Filing
- 2012-05-21 CN CN201280025806.5A patent/CN103582597A/en active Pending
- 2012-05-21 RU RU2013157084/11A patent/RU2013157084A/en not_active Application Discontinuation
- 2012-05-21 EP EP12728720.9A patent/EP2714517B1/en active Active
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US20150007905A1 (en) * | 2012-03-22 | 2015-01-08 | Aircelle | Method for manufacturing a one-piece preform for a composite structure |
EP3434597A1 (en) * | 2017-07-26 | 2019-01-30 | United Technologies Corporation | Nacelle |
US10767596B2 (en) | 2017-07-26 | 2020-09-08 | Raytheon Technologies Corporation | Nacelle |
US11046445B2 (en) | 2017-07-26 | 2021-06-29 | Raytheon Technologies Corporation | Nacelle |
US11408369B2 (en) | 2017-07-26 | 2022-08-09 | Raytheon Technologies Corporation | Nacelle |
US11548652B2 (en) | 2017-07-26 | 2023-01-10 | Raytheon Technologies Corporation | Nacelle |
Also Published As
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CA2837439A1 (en) | 2012-12-06 |
FR2975970B1 (en) | 2013-05-17 |
BR112013027790A2 (en) | 2017-01-10 |
WO2012164197A1 (en) | 2012-12-06 |
EP2714517A1 (en) | 2014-04-09 |
CN103582597A (en) | 2014-02-12 |
RU2013157084A (en) | 2015-07-10 |
FR2975970A1 (en) | 2012-12-07 |
EP2714517B1 (en) | 2017-08-02 |
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