U.S. patent application number 12/995344 was filed with the patent office on 2011-04-14 for casing comprising a peripheral shroud for a turbomachine rotor.
This patent application is currently assigned to AIRCELLE. Invention is credited to Pierre Andre Marcel Baudu, Guy Bernard Vauchel.
Application Number | 20110085897 12/995344 |
Document ID | / |
Family ID | 40184857 |
Filed Date | 2011-04-14 |
United States Patent
Application |
20110085897 |
Kind Code |
A1 |
Vauchel; Guy Bernard ; et
al. |
April 14, 2011 |
CASING COMPRISING A PERIPHERAL SHROUD FOR A TURBOMACHINE ROTOR
Abstract
The present invention relates to a casing (5) for a rotor of a
turbomachine, more particularly for a fan (1) of a turbojet engine
(2), comprising a peripheral shroud (6) designed to form a clamping
collar around the casing, characterized in that the shroud has at
least one fitting (12, 13) or flange for the attachment of
equipment.
Inventors: |
Vauchel; Guy Bernard;
(Harfleur, FR) ; Baudu; Pierre Andre Marcel;
(Criquetot L'Esneval, FR) |
Assignee: |
AIRCELLE
GONFREVILLE L'ORCHER
FR
|
Family ID: |
40184857 |
Appl. No.: |
12/995344 |
Filed: |
March 30, 2009 |
PCT Filed: |
March 30, 2009 |
PCT NO: |
PCT/FR09/00366 |
371 Date: |
November 30, 2010 |
Current U.S.
Class: |
415/182.1 |
Current CPC
Class: |
F01D 25/28 20130101;
Y02T 50/60 20130101; Y02T 50/672 20130101; F01D 25/24 20130101;
F02C 7/04 20130101; F01D 21/045 20130101; F05D 2300/603
20130101 |
Class at
Publication: |
415/182.1 |
International
Class: |
F04D 29/42 20060101
F04D029/42 |
Foreign Application Data
Date |
Code |
Application Number |
Jun 6, 2008 |
FR |
08/03156 |
Claims
1. A casing for a turbomachine rotor, more particularly for a
turbojet engine fan, comprising a peripheral shroud designed to
form a clamping collar around the casing, wherein the shroud has at
least one fitting or a flange for the attachment of equipment.
2. The casing according to claim 1, wherein the shroud is made from
a strip that can be closed on itself.
3. The casing according to claim 1, wherein the shroud is made from
at least two partially peripheral strips that are able to be joined
to each other.
4. The casing according to claim 3, wherein the shroud is made from
two substantially half-peripheral strips.
5. The casing according to claim 1, wherein the shroud is primarily
metal.
6. The casing according to claim 1, wherein the shroud is primarily
made of a composite material in particular from woven composite
fibers.
7. The casing according to claim 1, further comprising stops
situated on either side of the shroud so as to ensure positioning
and centering thereof and/or stops able to prevent any rotational
movement of the latter part.
8. The casing according to claim 1, wherein the shroud is glued on
the casing.
9. The casing according to claim 1, further comprising, at least at
the shroud, a surface having a coefficient of friction with at
least part of a surface of the shroud sufficient to limit or even
prevent the rotation of the shroud around the casing.
10. The casing according to claim 1, further comprising at least
two shrouds capable of each retaining at least one base of at least
one fitting, said base being introduced between the shroud and the
casing.
11. The casing according to claim 1, wherein the shroud is retained
on the casing by at least one discrete fastening means.
12. A propulsion assembly comprising a turbojet engine housed in a
nacelle, wherein it comprises a fan casing according to claim 1.
Description
TECHNICAL FIELD
[0001] The present invention concerns a casing for a turbomachine
rotor, and more particularly a casing for a turbojet engine
fan.
BACKGROUND
[0002] An airplane is moved by several turbojet engines each housed
in a nacelle also housing a set of connected actuating devices
related to its operation and performing various functions when the
turbojet engine is in operation or stopped, such as, for example, a
thrust reverser system.
[0003] More precisely, a nacelle generally has a tubular structure
comprising an air inlet upstream of the engine, a middle section
designed to surround a fan of the turbojet engine, and a downstream
section housing thrust reverser means and designed to surround the
combustion chamber of the turbojet engine and housing thrust
reverser means.
[0004] The fan of the turbojet engine is essentially made up of a
rotary shaft carrying a plurality of vanes. At their radial ends,
the blades are circumferentially surrounded by a casing.
[0005] The fan casings are generally machined metal elements.
[0006] Such an embodiment makes it possible to easily add
circumferential structural reinforcing flanges on a shroud between
the two ends of the casing, said flanges then being able to serve
also to support engine or nacelle equipment.
[0007] For reasons related to trying to save mass, and these
casings being situated in an area considered to be cold, they can
be made of a composite material, in particular of carbon
fibers.
[0008] Such an embodiment then no longer allows, or allows at
prohibitive costs, integrating flanges having the same geometric
configuration as for a metal casing. Generally, these components
therefore cannot be used to suspend engine or nacelle
equipment.
BRIEF SUMMARY
[0009] The present invention aims to offset the aforementioned
drawbacks, and to that end comprises a casing for a turbomachine
rotor, more particularly for a turbojet engine fan, comprising a
peripheral shroud designed to form a clamping collar around the
casing, characterized in that the shroud has at least one fitting
or flange for the attachment of equipment.
[0010] Thus, by providing a peripheral shroud surrounding the fan
casing, the latter can be used to support the fastening elements
and flanges of accessories of a nacelle or of turbojet engines
intended to be fastened to said casing.
[0011] The casing can thus be designed from the beginning to
receive determined and adapted fastening means of the shroud and
will not need to be modified to directly integrate the fittings and
flanges of the accessories.
[0012] Moreover, in case of addition of fittings or flanges, the
latter parts can easily be added on the shroud without risk of
damaging the integrity of the casing by adding new fixtures.
[0013] It will also be noted that in case of damage or wear of the
shroud, fittings or flanges, the replacement of these elements is
greatly facilitated.
[0014] Preferably, the shroud is made from a strip that can be
closed on itself.
[0015] Alternatively, the shroud is made from at least two strips
that are partially peripheral and able to be joined to each
other.
[0016] Advantageously, the shroud is made from two substantially
half-peripheral strips.
[0017] Preferably, the shroud is primarily metal. The installation
of fittings or flanges can then be done as in the prior art.
[0018] Alternatively, the shroud is made primarily of a composite
material, in particular from woven composite fibers.
[0019] Advantageously, the casing comprises stops, situated on
either side of the shroud so as to ensure the positioning and
centering thereof, and/or stops able to prevent any rotational
movement by the latter.
[0020] Preferably, the shroud is glued on the casing.
[0021] Also preferably, the casing has, at least at the shroud, a
surface having a coefficient of friction with at least part of a
surface of the shroud sufficient to limit or even prevent the
rotation of the shroud around the casing.
[0022] According to one particular embodiment of the invention, the
casing comprises at least two shrouds each able to retain at least
one base of at least one fitting, said base being introduced
between the shroud and the casing.
[0023] Advantageously, the shroud is retained on the casing by at
least one discrete fastening means.
[0024] The present invention also concerns a propulsion assembly
comprising a turbojet engine housed in a nacelle, characterized in
that it comprises a fan casing according to the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0025] The present invention will be better understood using the
detailed description that follows in reference to the appended
drawing, in which:
[0026] FIG. 1 is a diagrammatic longitudinal cross-sectional
illustration of a casing surrounding a fan of the turbojet
engine.
[0027] FIG. 2 is an enlarged partial view in transverse
cross-section of a fastening of a shroud according to the invention
around the casing of FIG. 1.
[0028] FIG. 3 is a diagrammatic illustration of a fitting mounted
on the shroud of FIG. 2, said fitting being oriented perpendicular
to the shroud.
[0029] FIG. 4 is a diagrammatic illustration of a fitting mounted
on the shroud of FIG. 2, said fitting being oriented in the plane
of the shroud.
[0030] FIG. 5 is a partial enlarged view in partial cross-section
of the shroud of FIG. 2 associated with a retaining stop of the
casing.
[0031] FIG. 6 is a partial diagrammatic view in longitudinal
cross-section of a shroud arranged in a groove present in the
casing.
[0032] FIG. 7 is a diagrammatic illustration in longitudinal
cross-section of a fitting maintained on the casing using two
shrouds according to the invention.
[0033] FIG. 8 is a partial diagrammatic illustration in
longitudinal cross-section of two shrouds retained on the casing
using discrete fastening means.
DETAILED DESCRIPTION
[0034] FIG. 1 shows a fan 1 of a turbojet engine 2, said fan 1
comprising a rotary shaft 4 supporting a set of peripheral vanes 3.
At their radial ends, the vanes are circumferentially surrounded by
a casing 5 ensuring the internal aerodynamic continuity of an air
intake structure (not visible) and an inner wall of a downstream
section (not visible) of a nacelle.
[0035] As shown in FIG. 2, the casing 5 is surrounded by a
peripheral shroud 6 like a clamping collar.
[0036] The shroud 6 illustrated in FIG. 2 is made from a strip that
can be closed on itself around said casing 5 having, to that end,
two ends 7, 8 brought, in the closing position, opposite each other
preferably at a longitudinal median plane of the casing 5.
[0037] The shroud 6 is kept closed around the casing 5 by a screw
9/nut 10 system. Such a fastening system makes it possible to
easily adapt the gripping of the shroud 6 on the casing 5.
[0038] FIGS. 3 and 4 each show a fitting 12, 13 supported by the
shroud 6.
[0039] The fitting 12 has a foot 12a fastened in the shroud 6 using
fastening means 12b of the nut type. The fitting 12 is mounted
perpendicular to the shroud 6.
[0040] The fitting 13 has a foot 13a fastened in the shroud 6 using
fastening means 13b of the nut type. The fitting 13 is mounted in
the axis at the shroud 6.
[0041] FIGS. 3 and 4 illustrate the fact that the number, size,
position, orientation and shape of the fittings can vary on a same
shroud 6, and their fastening therefore does not result from the
production of particular fastening means on the casing.
[0042] Indeed, a metal fan casing being a part taken up in
revolution, this means that the fittings and fixtures are all in a
same circumferential direction and require fittings with a complex
configuration to adapt to the equipment to be supported. In the
case of mounting on a shroud, the attached fittings can assume
different orientations allowing a simple design, since it does not
depend on the connecting area.
[0043] As shown in FIG. 5, the shroud 6 is kept in position using
stops formed on the casing 5. In the case in point, FIG. 5 shows a
stop 15 situated between the ends 7, 8 of the shroud 6, at the
closing means 9, 10 thereof, and aims to prevent any rotation of
the shroud 6 around the casing.
[0044] Any longitudinal movements of the shroud 6 along the casing
5 are also prevented by the placement of lateral stops 16, 17.
[0045] Of course, it is also possible to use closing flanges, or
connecting flanges with an air intake section or a downstream
section, as stop aiming to prevent the longitudinal movement of the
shroud 6.
[0046] As shown in FIG. 6, these lateral stops 16, 17 are formed by
making a peripheral groove 18 in the casing 5, the shroud 6 being
positioned inside said groove 18. The peripheral groove 18 is
preferably made by machining in a local overthickness of the casing
5.
[0047] FIG. 7 illustrates another method of fastening a fitting 21
using two shrouds 6.
[0048] In the case in point, the fitting 21 has a mounting foot 21a
extending on either side of said fitting 21 along a longitudinal
axis of the casing 5. The foot 21a thus has an upstream extension
and a downstream extension that are each maintained by a shroud 6
on the casing 5.
[0049] FIG. 8 is an example of distribution of shrouds 6 along a
fan casing 5, the shrouds 6 being fastened in the casing using
discrete fastening means distributed around the casing 5.
[0050] Although the invention has been described with specific
embodiments, it is obviously in no way limited thereto and
encompasses all technical equivalents of the means described as
well as combinations thereof if they are within the scope of the
invention.
* * * * *