U.S. patent application number 14/093761 was filed with the patent office on 2014-03-27 for assembly for an aircraft nacelle.
This patent application is currently assigned to AIRCELLE. The applicant listed for this patent is AIRCELLE. Invention is credited to Xavier CAZUC, John Moutier, Christophe Thorel.
Application Number | 20140086678 14/093761 |
Document ID | / |
Family ID | 46321144 |
Filed Date | 2014-03-27 |
United States Patent
Application |
20140086678 |
Kind Code |
A1 |
CAZUC; Xavier ; et
al. |
March 27, 2014 |
ASSEMBLY FOR AN AIRCRAFT NACELLE
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.
Inventors: |
CAZUC; Xavier; (Le Havre
Rouelles, FR) ; Thorel; Christophe; (Le Havre,
FR) ; Moutier; John; (Le Havre, FR) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
AIRCELLE |
Gonfreville L'Orcher |
|
FR |
|
|
Assignee: |
AIRCELLE
Gonfreville L'Orcher
FR
|
Family ID: |
46321144 |
Appl. No.: |
14/093761 |
Filed: |
December 2, 2013 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
PCT/FR2012/051123 |
May 21, 2012 |
|
|
|
14093761 |
|
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Current U.S.
Class: |
403/335 |
Current CPC
Class: |
Y02T 50/60 20130101;
B64D 29/00 20130101; F16B 2200/50 20180801; B64D 2033/0286
20130101; F02C 7/04 20130101; F05D 2300/702 20130101; Y02T 50/672
20130101; F04D 29/52 20130101; B64D 29/06 20130101 |
Class at
Publication: |
403/335 |
International
Class: |
F04D 29/52 20060101
F04D029/52 |
Foreign Application Data
Date |
Code |
Application Number |
May 30, 2011 |
FR |
1154685 |
Claims
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.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] 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.
FIELD
[0002] The present disclosure relates to an assembly including a
flange and a reinforcing plate of that flange, intended for an
aircraft nacelle.
BACKGROUND
[0003] The statements in this section merely provide background
information related to the present disclosure and may not
constitute prior art.
[0004] 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.
[0005] 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.
[0006] 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.
[0007] 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.
[0008] It may include an air-permeable inner skin, an
air-impermeable outer skin and a honeycomb cellular core.
[0009] Other alternatives can be considered, such as replacing the
cellular core with porous foam or microspheres.
[0010] In reference to FIG. 1 as well, the midsection comprises an
inner casing 20 surrounding the fan of the turbojet engine (not
shown) extending the inner 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.
[0011] The inner shroud 10 is intended to be fixed to the fan
casing 20 in a junction plane designated by the letter A, using
peripheral connecting flanges 30, 40 placed on the downstream end
of the inner shroud 10 and the upstream end of the fan casing 20,
respectively.
[0012] In one form, 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.
[0013] 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.
[0014] 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.
[0015] The connecting flange 30 of the inner 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 in FIG. 1) to the connecting flange 40 of
the casing 20 at the junction plane A, through the orifice 35.
[0016] Traditionally, 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.
[0017] This reinforcing plate 33 makes it possible to meet the
structural strength requirements of the connecting flange 30.
[0018] It is suitable for shaping the corresponding flange, and in
particular for defining the curve radius of the latter.
[0019] It is also suitable for defining the stiffness of the flange
30 over its entire circumference.
[0020] It also avoids unfolding of the plies of the flange 30 in
the radius when the shroud 10 is subjected to traction forces and
damps the strains generated by the tightening of the fastening
means.
[0021] However, as can be seen in FIG. 2, when the reinforcing
plate 33 is attached to the flange 30, it generates a bead 320 in
the flange 30, situated at the side of the reinforcing plate
33.
[0022] 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.
[0023] In extreme loading cases, this is detrimental to the
mechanical strength of the flange 30.
[0024] Furthermore, 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.
SUMMARY
[0025] The present disclosure provides an assembly for an aircraft
nacelle, comprising: [0026] 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 [0027] 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.
[0028] 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.
[0029] 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.
[0030] 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: [0031] the beveled part of the
reinforcing plate is an end part of that reinforcing plate, in
contact with the second part of the flange; [0032] the beveled end
part of the reinforcing plate assumes the form of an elongated
bevel extending along the second part of the flange; [0033] the
assembly comprises an intermediate plate, fixed between the flange
and the reinforcing plate; [0034] the intermediate plate extends,
at its end in contact with the second part of the flange, beyond
the end part of the reinforcing plate; [0035] the intermediate
plate is made from a composite material or a metal material, such
as aluminum or titanium; [0036] the intermediate plate has a
thickness comprised between 0.1 mm and 3 mm; [0037] the beveled
part of the reinforcing plate is an end part of that plate; [0038]
the reinforcing plate comprises: [0039] a first part attached
against the first part of the flange, [0040] 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 [0041] a third part, situated in the
extension of the beveled part of the reinforcing plate and attached
against the second part of the flange. [0042] the third part of the
reinforcing plate has a thickness comprised between 0.1 mm and 3
mm.
[0043] 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.
DRAWINGS
[0044] 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:
[0045] FIG. 1 is a partial cross-sectional view of an assembly of
an air inlet structure and fan casing according to the prior
art;
[0046] 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;
[0047] 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 in FIG. 1;
[0048] 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;
[0049] 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; and
[0050] 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 in FIG. 1.
[0051] The drawings described herein are for illustration purposes
only and are not intended to limit the scope of the present
disclosure in any way.
DETAILED DESCRIPTION
[0052] 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.
[0053] In general, and as shown in FIGS. 3 to 6 appended hereto,
the present disclosure relates to an assembly for an aircraft
nacelle comprising: [0054] a flange 30 including at least a first
part 31 intended to be fixed to another flange 40 and a second part
32 extending transversely relative to the first part 31 intended to
be fixed on a panel of said assembly, and [0055] a reinforcing
plate 330, 332, 334 directly attached on the flange 30 or,
optionally, indirectly by means of an intermediate plate 36 fixed
between the reinforcing plate 330, 332, 334 and the flange 30, said
reinforcing plate 330, 332, 334 having a beveled part across from
the second part 32 of the flange 30.
[0056] In another form, the part 32 may be fixed on an acoustic
panel of said assembly.
[0057] The beveled part of the reinforcing plate 330, 332, 334
makes it possible to limit the dimension of a bead in the flange
30, as shown in FIG. 2, or to avoid the formation of such a
bead.
[0058] The beveled shape further allows a better transition in the
stiffness between the flange 30 and the shroud panel on which it is
fixed.
[0059] A first form of the present disclosure is described with the
help of FIG. 3.
[0060] According to this first form, the reinforcing plate 330
comprises a beveled end part 331, which is in direct contact with
the second part 32 of the flange 30.
[0061] The fact that the beveled end 331 of the reinforcing plate
330 is in contact with the second part 32 of the flange 30 limits
the dimension of the bead as shown in FIG. 2, that bead being able
to be formed on the part 32 when the reinforcing plate 330 is
attached directly on the flange 30 and exerts pressure on the
flange 30 to shape and define its radius of curvature.
[0062] 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 the flange 30 and the
shroud;
[0063] It should be noted that this reinforcing plate 330 may be
made from a composite material, independently from the flange
30.
[0064] To that end, the reinforcing plate 330 may be produced by
RTM injection, infusion or autoclave curing.
[0065] It is generally pre-cured, then attached on the flange 30 on
the plies of the flange that are not yet polymerized.
[0066] In non-limiting alternative forms, this reinforcing plate
330 may comprise pre-impregnated plies, dry fabric, woven preforms
or short fibers.
[0067] The reinforcing plate 30 may also be metallic.
[0068] The reinforcing plate 330 thus has a stiffness allowing it
to perform its reinforcing function of the flange 30.
[0069] A second form of the present disclosure is described with
the help of FIG. 4.
[0070] In the second form, the reinforcing plate 332 has an end
part that is also beveled, assuming the form of an elongated bevel
333 extending over the majority of the length of the second part 32
of the flange 30, or over the entire length of the second part 32
of the flange 30, directly in contact with the flange 30.
[0071] This elongated shape 333 is advantageous inasmuch as it
makes it possible to better distribute the effect of the pressure
on the second part 32 of the flange 30, relative to the first form,
the bead that may be formed when the reinforcing plate 332 is
attached directly on the flange 30 is smaller, or is even
eliminated.
[0072] The reinforcing plate 332 may be manufactured in the same
way as the reinforcing plate 330 of the first form and comprise
identical components.
[0073] A third form of the present disclosure is described with the
help of FIG. 5.
[0074] 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 the flange 30.
[0075] In fact, in this form, an intermediate plate 36 is provided,
fixed between the flange 30 and the reinforcing plate 330.
[0076] 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.
[0077] In this case, the intermediate plate 36 makes it possible to
smooth the pressure applied on the plies of the part 32 of the
flange 30 by the reinforcing plate 330-331 during curing.
[0078] Advantageously, and as illustrated in FIG. 5, this
intermediate plate 36 is attached against the first part 31 of the
flange and extends at its end in contact with the second part 32 of
the flange 30 beyond the beveled end part 331 of the reinforcing
plate 330.
[0079] This makes it possible to still better distribute the forces
applied to the flange 30, in this case to the second part 32 of the
flange 30, by the reinforcing plate 330.
[0080] 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 reinforcing
plate 330 is attached on the flange 30.
[0081] 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 the flange 30.
[0082] The intermediate plate 36 can be made from a composite
material, for example with components identical to those of the
reinforcing plate 330.
[0083] In another form, this intermediate plate 36 may be made from
a metal material such as aluminum or titanium.
[0084] Furthermore, the intermediate plate 36 typically has a
thickness comprised between 0.1 and 3 mm.
[0085] A fourth form of the present disclosure is described with
the help of FIG. 6.
[0086] This fourth form offers the advantages of the third
form.
[0087] However, in this fourth form, the reinforcing part 334 has a
shape comparable to the shape obtained, for the third form, once
the reinforcing plate 330 and the intermediate plate 36 have been
assembled.
[0088] Thus, the reinforcing plate 334 comprises:
[0089] a first part 335 attached against the first part 31 of the
flange 30,
[0090] a second part 336, situated in the extension of the first
part 335 of the reinforcing plate 334 and forming the beveled part
of that reinforcing plate 334, said second part 336 of the
reinforcing plate 334 being attached against the second part 32 of
the flange 30, and
[0091] a third part 337, situated in the extension of the beveled
part 336 of the reinforcing plate 334 and attached against the
second part 32 of the flange 30.
[0092] Furthermore, the third part 337 of the reinforcing plate 334
can have a thickness smaller than that of the first 335 and second
336 parts of the reinforcing plate 334.
[0093] 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.
[0094] The reinforcing plate 334 can be made in the same way as the
reinforcing plate 330 of the first form and comprise the same
components.
[0095] Of course, the present disclosure is in no way limited to
the forms described and shown, provided purely as an example.
[0096] 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.
* * * * *