• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an aeronautical turbomachine fan casing (10) comprising an upstream flange (12), a downstream flange (14), and a barrel extending axially between said flanges, said barrel comprising: a first portion (16) extending axially on a portion of said barrel located at a distance from the flanges, said first portion having an internal face (16a) covered by an abradable coating (18) and being intended to be positioned facing the vertices of the blades (11) of the blower (1), and a second portion (20) located between the first portion and a flange, an acoustic coating (22) being present on said second portion (20), characterized in that the acoustic coating is present on an outer face (22a) of the second portion, and in that all or part of said second portion comprises perforations (24). The invention also relates to a method of manufacturing such a housing.
    公开号:FR3059044A1
    申请号:FR1661359
    申请日:2016-11-22
    公开日:2018-05-25
    发明作者:Bernard Serge Most Vincent；Jean Marie Fabre Hubert；Jean Francois Techer Marc-Emmanuel
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY © Publication number:
    (to be used only for reproduction orders) (© National registration number
    059 044
    61359
    COURBEVOIE © Int Cl 8 : F 01 D 25/24 (2017.01), F 02 C 7/24, F 04 D 29/02, B 29 C 70/30, 70/48
    A1 PATENT APPLICATION
    ©) Date of filing: 22.11.16. © Applicant (s): SAFRAN AIRCRAFT ENGINES (© Priority: Simplified joint stock company - FR. @ Inventor (s): MOST VINCENT, BERNARD, SERGE, FABRE HUBERT, JEAN, MARIE and TECHER MARC- (43) Date of public availability of the EMMANUEL, JEAN, FRANÇOIS. request: 25.05.18 Bulletin 18/21. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ® Holder (s): SAFRAN AIRCRAFT ENGINES Company related: by simplified actions. ©) Extension request (s): © Agent (s): CABINET BEAU DE LOMENIE.
    AERONAUTICAL TURBOMACHINE BLOWER HOUSING.
    FR 3 059 044 - A1 (£ /) The invention relates to an aeronautical turbomachine fan casing (10) comprising an upstream flange (12), a downstream flange (14), and a barrel extending axially between said flanges, said barrel comprising: a first portion (16) extending axially over a part of said barrel located at a distance from the flanges, said first portion having an internal face (16a) covered by an abradable coating (18) and being intended to be positioned in look at the tops of the blades (11) of the fan (1), and a second portion (20) located between the first portion and a flange, an acoustic coating (22) being present on said second portion (20), characterized in that that the acoustic coating is present on an external face (22a) of the second portion, and in that all or part of said second portion comprises perforations (24). The invention also relates to a method of manufacturing such a casing.
    Invention background
    The invention relates to the general field of gas turbine casings, and more particularly, but not exclusively, to fan casings of aeronautical gas turbines.
    In an aeronautical gas turbine engine, the fan casing performs several functions. It defines in particular the air intake duct in the engine, possibly supports an abradable material opposite the tops of the fan blades and / or a structure for absorbing sound waves, or acoustic coating, for acoustic treatment. at the engine inlet, and incorporates or supports a retention shield.
    Previously made of metallic material, the casings, such as that of the blower, are now made of composite material, that is to say from a fiber preform densified by an organic matrix, which allows parts to be produced. having a lower overall mass than these same parts when they are made of metallic material while having a mechanical resistance at least equivalent if not greater. A method of manufacturing a fan casing made of an organic matrix composite material in which acoustic panels are integrated on an internal face of the casing is for example described in document US2014 / 150262.
    There is however still a need for a fan casing of reduced mass compared to known casings.
    Subject and summary of the invention
    The object of the present invention is therefore to propose a fan casing, for example made of metallic material or of composite material with an organic matrix, which has a reduced mass compared with known architectures.
    This object is achieved, according to a first aspect, by an aeronautical turbomachine fan casing comprising an upstream flange, a downstream flange, and a barrel extending axially between said flanges, said barrel comprising:
    a first portion extending axially over a part of said barrel located at a distance from the flanges, said first portion having an internal face covered by an abradable coating and being intended to be positioned facing the tops of the blades of the fan, and a second portion located between the first portion and a flange, an acoustic coating being present on said second portion.
    According to the invention, the acoustic coating is present on an external face of the second portion, and all or part of said second portion comprises perforations.
    As the acoustic coating is present on an external face of an axial portion of the casing of the casing according to the invention, the average diameter of this portion can be reduced compared to the casings in which this coating is present on the internal face. Indeed, a reduction in diameter on at least a portion of the barrel of the casing results in a reduction of the overall mass of the casing. In addition, the invention makes it possible to reduce the cost of manufacturing the casing because the quantity of raw material necessary to manufacture it is reduced. The diameter of the casing can for example, where the acoustic coating is present, be reduced by at least twice the thickness of said coating. The perforations in the casing of the casing allow the passage of sound waves in the acoustic coating, and thus their absorption by the latter.
    Advantageously, the abradable coating can be directly in contact with the internal face of the first portion. This arrangement further reduces the overall mass of the housing. In effect, this eliminates the use of an abradable coating support panel, arranged for example between the abradable coating and the first portion of the casing barrel, which makes it possible to reduce the diameter of the casing at this first portion .
    In an exemplary embodiment, the first portion may have a first mean radius, the second portion having a second mean radius strictly less than the first mean radius. By "average radius" is meant the average of the radius of the portion considered over its entire axial dimension.
    In an exemplary embodiment, the second portion may be located downstream of the first portion, and the casing of the casing may further comprise a third portion between the first portion and the upstream flange, the casing further comprising an acoustic coating present on an external face of said third portion, all or part of said third portion comprising perforations.
    The casing according to the invention may be made of composite material comprising a fibrous reinforcement densified by a matrix with a resin precursor. Alternatively, it may be made of a metallic material.
    In an exemplary embodiment, the acoustic covering may comprise a plurality of acoustic panels fixed to the external face of the second portion of the barrel of the casing. For example, the acoustic panels can be glued to the external face of the second portion of the barrel of the casing.
    The invention also relates to an aeronautical turbomachine comprising a casing such as that presented above.
    The invention also relates, according to a second aspect, to a method of manufacturing an aeronautical turbomachine fan casing made of composite material comprising a fibrous reinforcement densified by a matrix with resin precursor, the casing comprising an upstream flange, a downstream flange, and a barrel extending axially between said flanges, said barrel comprising: a first portion extending axially over a part of said barrel located at a distance from the flanges, said first portion having an internal face covered by an abradable coating and being intended to be positioned opposite the tops of the fan blades; and a second portion located between the first portion and a flange, an acoustic coating being present on an external face of said second portion, all or part of said second portion comprising perforations, ie method comprising the following steps:
    a) shaping a fibrous preform intended to form the fibrous reinforcement of the casing on a tool having the form of said casing,
    b) insertion of needles into at least one portion of the shaped preform corresponding to the second portion of the barrel of the casing,
    c) impregnation of the preform obtained after step b) with a matrix precursor resin and heat treatment of the impregnated preform so as to obtain a preform densified by the matrix,
    d) withdrawal of the needles from the densified preform in step c) so as to obtain the perforations in the second portion of the barrel of the casing, and
    e) formation of the acoustic coating on all or part of the external face of the second portion of the casing of the casing.
    In an exemplary embodiment, the step of forming the acoustic covering may comprise the fixing of a plurality of acoustic panels on the external face of the second portion of the barrel of the casing. For example, fixing the plurality of acoustic panels can consist of bonding said panels to the housing. An acoustic panel may for example include a honeycomb structure, also called a "nest", and a carbon skin covering said honeycomb structure.
    When the casing is made of a metallic material, it can be manufactured by techniques well known to those skilled in the art, the perforations then being machined in all or part of the portion or portions of the casing of the casing on which the acoustic coating will be present. .
    Brief description of the drawings
    Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an embodiment thereof devoid of any limiting character. In the figures:
    - Figure 1 is a very schematic view of an aircraft engine turbomachine;
    - Figure 2 is a schematic perspective view of a fan casing according to an embodiment of the invention;
    - Figure 3 is an axial sectional view of Figure 2; and
    - Figures 4A to 4C illustrate different stages of an example of a method of manufacturing a housing according to the invention in composite material with organic matrix.
    Detailed description of the invention
    The invention will be described below in the context of its application to an airplane engine turbomachine fan casing.
    As shown diagrammatically in FIG. 1, such a turbomachine comprises, from upstream to downstream in the direction of flow of the gas flow in the turbomachine, a fan 1 disposed at the inlet of the turbomachine, a compressor 2, a chamber combustion 3, a high pressure turbine 4 and a low pressure turbine 5. The turbines 4 and 5 are respectively coupled to the compressor 2 and to the blower 1 by respective coaxial shafts. The turbomachine is housed in a casing comprising several parts corresponding to different of its elements. Thus, the fan 1 is surrounded by a fan casing 10 having a shape of revolution.
    As shown in Figures 2 and 3, the housing 10 extends axially along the axis A-A and takes a generally cylindrical shape. In the present description, the terms “radial”, “circumferential”, “axial”, “internal”, “external”, and their derivatives are defined with respect to the axis A-A. The casing 10 has at its upstream axial end an upstream flange or flange 12 and at its downstream axial end a downstream flange or flange 14. The flanges 12, 14 allow the fan casing 10 to be fixed.
    The casing 10 comprises an annular wall or barrel which comprises a first portion 16 intended to be located opposite the ends of the blades 11 of the fan 1. The first portion 16 is located at a distance from the flanges 12, 14, that is to say - say that it is not located in the immediate vicinity of these. The first portion 16 comprises an internal face 16a covered with an abradable coating 18. In the example illustrated, the abradable coating 18 is made of abradable material and is directly formed on the internal face 16a of the casing 10. As a variant, the coating abradable 18 can be formed of a set of panels or cartridges, juxtaposed, fixed to the casing and lined with abradable material.
    The casing 10 illustrated further comprises a second portion 20 located downstream of the first portion 16, and more precisely between the first portion 16 and the downstream flange 14. This second portion 20 comprises an external face 20a on which is present a acoustic coating 22 or soundproofing coating. In known manner, the acoustic covering 22 can be formed by a set of acoustic panels, for example six panels distributed on the external circumference of the casing 10. Such acoustic panels can comprise cells formed by cells delimited by walls s' extending substantially radially, and covered for example with a carbon skin. In order to ensure the soundproofing function of the acoustic covering 22, the casing 10 is, at the second portion 20, provided with perforations 24 passing through the barrel of the casing 10. The perforations 24 may be present on all or part of the second portion 20. In general, it can be ensured that each portion on which the acoustic coating 22 is present is provided with perforations 24.
    In the example illustrated, the barrel of the casing 10 further comprises a third portion 20 ′, similar to the second portion 20, located upstream of the first portion 16, and more precisely between the first portion 16 and the upstream flange 12. This third portion 20 ′ comprises an external face 20a ′ on which an acoustic coating 22 ′ or soundproofing coating is present. In a known manner, the acoustic covering can be formed by a set of acoustic panels, for example six panels distributed on the external circumference of the casing 10. Such acoustic panels can comprise cells formed by cells delimited by walls extending substantially radially, and covered for example with a carbon skin. In order to ensure the soundproofing function of the acoustic covering 22 ', the casing 10 is, at the third portion 20', also provided with perforations 24 'passing through the barrel of the casing 10.
    Thus, the barrel of the casing 10 according to the invention comprises, from upstream to downstream, the third portion 20 ', the first portion 16 and the second portion 20. The internal face of the second 20 and third 20' portions, define with the internal face 26 of the abradable coating of the first portion 16, the aerodynamic air intake stream in the turbomachine. In the example illustrated, the diameter of the casing is substantially constant at each of the first 16, second 20 and third 20 'portions. Alternatively, the diameter of the casing at each of the first 16, second 20 and third 20 'portions can be variable, for example increasing or decreasing. In the figures, the average radius Ri of the first portion 16 is here strictly greater than the average radii R 2 and R 3 of each of the second 20 and third 20 'portions. The diameter of the casing according to the invention is thus variable. In the example illustrated, the casing of the casing has, from the third 20 'to the first 16 portion, an increasing diameter. Correspondingly, the casing of the casing has, from the first 16 to the second portion, a decreasing diameter.
    Thanks to the arrangement of the acoustic coverings 22, 22 'on external faces 20a, 20a' of the casing of the casing 10 according to the invention, the diameter of the casing at the level of the portions 20 and 20 'is reduced, resulting in a reduction in mass of all. Similarly, when the abradable coating 18 is directly in contact with the internal face 16a of the first portion 16, as in the example illustrated, it is possible to also reduce the diameter of the casing 10 at the level of the first portion relative to casings 10 where the abradable coating comprises abradable support panels on which the abradable material is present.
    The casing 10 according to the invention can for example be made of a metallic material or, as a variant, a composite material.
    The perforations 24, 24 'may for example have a diameter less than or equal to 2 mm, for example less than or equal to 1 mm. The thickness of the housing barrel can, in the case of a metal housing, be between 2 mm and 4 mm. As a variant, in the case of a casing made of composite material comprising a fibrous reinforcement densified by a matrix, the thickness of the barrel of the casing may be between 10 mm and 14 mm thick.
    To obtain the casing 10 according to the invention in metallic material, the casing 10 is produced in the desired shape and dimensions, in a manner known per se, then the perforations are formed in the portions 20, 20 ′ of the casing of the casing, by example by drilling, and finally forming the acoustic coating on the portions 20, 20 ′ of the casing 10.
    On the other hand, when the casing is made of composite material, it can be difficult to machine the perforations in the casing of the casing, the ratio between the thickness to be drilled and the diameter of the perforations being too great. A method of manufacturing the casing 10 illustrated in FIGS. 2 and 3 in composite material will be described in connection with FIGS. 4A to 4C.
    The construction of the casing begins with the formation of a fibrous texture in the form of a strip. FIG. 4A very schematically shows a fibrous structure 100 woven in the form of a strip intended to form a fibrous preform of the casing 10. The fibrous structure 100 is obtained by three-dimensional or multilayer weaving produced in known manner by means of a loom of the jacquard type on which a bundle of warp threads or strands has been placed in a plurality of layers, the warp threads being linked by weft threads. The three-dimensional weaving can, in the example illustrated, be an “interlock” weaving weave, known per se. Other types of known multilayer weaving can be used, such as in particular those described in document WO 2006/136755. The fibrous structure can in particular be woven from son of carbon fibers, ceramic such as silicon carbide SiC, glass or even aramid.
    As illustrated in FIG. 4A, the fibrous reinforcement is formed by winding on a mandrel 200 of the fibrous texture 100 produced by three-dimensional weaving, the mandrel 200 having a profile corresponding to that of the casing 10 to be produced. To this end, the mandrel 200 has an external surface 201 whose profile corresponds to the internal surface of the casing to be produced. By its winding on the mandrel 200, the fibrous texture 100 follows the profile thereof. The mandrel 200 has on its external surface 201 an annular boss 210 whose shape and dimensions correspond to those of the first portion 16 to be formed. The mandrel 200 also comprises two flanges or flanges 220 and 230 for forming parts of the fiber preform corresponding to the flanges 12, 14 of the casing 10 to be manufactured.
    Next, needles or pins are inserted into the portions of the fiber preform 100 intended to form the portions 20, 20 ′ of the casing 10. These needles will make it possible to form the perforations 24, 24 ′. In the example described here, this step is carried out after closing the mold 300 which will then make it possible to densify the preform. The mold 300 here consists of the mandrel 200 on which the preform 100 is wound, and of a set of counter mold sectors 310, here five in number. The counter mold sectors 310 can be provided with retractable or removable needles 311 which can project on the internal face of the sectors 310. The counter mold sectors 310 are approached radially from the mandrel (in the direction indicated by the arrows 312 on Figure 4B) and fixed so as to close the mold. The needles 311 are then inserted into the preform 100. The needles 311 each extend in a radial direction relative to the axis of the mandrel 200. The mold 300 thus closed is shown in FIG. 4C. It will be noted that, as a variant, the needles 311 can be independent of the sectors 310 and inserted into the preform 100 before the mold 200 is closed.
    The fiber preform 100 is then densified by a matrix. The densification of the fibrous preform consists in filling the porosity of the preform, in all or part of the volume thereof, with the material constituting the matrix.
    The matrix can be obtained in a manner known per se according to the liquid method. The liquid method consists in impregnating the preform with a liquid composition containing an organic precursor of the matrix material. The organic precursor is usually in the form of a polymer, such as a resin, optionally diluted in a solvent. Once the fibrous preform 100 is placed in the mold 300 closed in a sealed manner, the liquid matrix precursor, for example a resin, is injected into the entire housing inside the mold 300 to impregnate the entire fibrous part of the preform.
    The transformation of the precursor into an organic matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after elimination of the possible solvent and crosslinking of the polymer, the preform always being maintained in the mold having a shape corresponding to that of the part to be produced. The organic matrix can in particular be obtained from epoxy resins, such as, for example, the high performance epoxy resin sold, or liquid precursors of carbon or ceramic matrices.
    In the case of the formation of a carbon or ceramic matrix, the heat treatment consists in pyrolyzing the organic precursor in order to transform the organic matrix into a carbon or ceramic matrix according to the precursor used and the pyrolysis conditions. For example, liquid carbon precursors can be relatively high coke resins, such as phenolic resins, while liquid ceramic precursors, in particular SiC, can be polycarbosilane (PCS) resins or polytitanocarbosilane (PTCS) or polysilazane (PSZ). Several consecutive cycles, from impregnation to heat treatment, can be performed to achieve the desired degree of densification.
    According to one aspect of the invention, the densification of the fiber preform can be carried out by the well-known resin transfer molding process called RTM ("Resin Transfer Molding"). In accordance with the RTM process, a thermosetting resin is injected into the internal space of the mold 300 in which the fibrous preform 100 is present. A pressure gradient is generally established in this internal space between the place where the resin is injected and orifices evacuation of the latter in order to control and optimize the impregnation of the preform by the resin.
    The resin used can be, for example, an epoxy resin. Resins suitable for RTM processes are well known. They preferably have a low viscosity to facilitate their injection into the fibers. The choice of the temperature class and / or the chemical nature of the resin is determined according to the thermomechanical stresses to which the part must be subjected. Once the resin has been injected into all of the reinforcement, it is polymerized by heat treatment in accordance with the RTM process.
    After injection and polymerization, the needles 311 are removed from the casing 10 thus densified to leave room for the perforations 24, 24 ′ and the casing 10 is removed from the mold. In the end, the part is cut out to remove the excess resin and finishing operations can be carried out.
    In a final step, the abradable coating is formed or fixed on the internal face 16a of the first portion 16 of the housing 10, and the acoustic coating on each of the portions 20, 20 ′ of the housing 10. For example, it is possible to spread over the internal face 16 has a precursor of abradable material and polymerize it by heat treatment. It is also possible to attach acoustic panels to the external faces of said portions 20, 20 ′ by applying, for example beforehand, a layer of epoxy adhesive which can be heated before application of the panels so as not to obstruct the perforations 24, 24 ′ previously formed.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Fan casing (10) of an aeronautical turbomachine comprising an upstream flange (12), a downstream flange (14), and a barrel extending axially between said flanges, said barrel comprising:
    a first portion (16) extending axially over a part of said barrel located at a distance from the flanges, said first portion having an internal face (16a) covered by an abradable coating (18) and being intended to be positioned facing the tops of the blades (11) of the fan (1), and a second portion (20) located between the first portion and a flange, an acoustic coating (22) being present on said second portion (20), characterized in that the acoustic coating is present on an external face (22a) of the second portion, and in that all or part of said second portion comprises perforations (24).
    [2" id="c-fr-0002]
    2. Housing according to claim 1, characterized in that the abradable coating (18) is directly in contact with the internal face (16a) of the first portion (16).
    [3" id="c-fr-0003]
    3. Housing according to any one of claims 1 and 2, characterized in that the first portion (16) has a first mean radius (RJ, the second portion having a second mean radius (R 2 ) strictly less than the first mean radius .
    [4" id="c-fr-0004]
    4. Housing according to any one of claims 1 to 3, characterized in that the second portion (20) is located downstream of the first portion (16), and in that the barrel of the housing (10) comprises in addition a third portion (209 between the first portion and the upstream flange (12), the casing further comprising an acoustic coating (22 ') present on an external face (22a 4 * * 7 ) of said third portion, all or part of said third portion comprising perforations (249.
    [5" id="c-fr-0005]
    5. Housing according to any one of claims 1 to 4, characterized in that it is made of composite material comprising a fibrous reinforcement densified by a matrix with resin precursor.
    [6" id="c-fr-0006]
    6. Housing according to any one of claims 1 to 4, characterized in that it is made of a metallic material.
    [7" id="c-fr-0007]
    7. Housing according to any one of claims 1 to 6, characterized in that the acoustic coating (22) comprises a plurality of acoustic panels fixed to the external face (20a) of the second portion (20) of the barrel of the housing.
    [8" id="c-fr-0008]
    8. Aeronautical turbomachine comprising a casing according to any one of claims 1 to 7.
    [9" id="c-fr-0009]
    9. Method for manufacturing a fan casing (10) of an aeronautical turbomachine made of composite material comprising a fibrous reinforcement densified by a resin precursor matrix, the casing comprising an upstream flange (12), a downstream flange (14), and a barrel extending axially between said flanges, said barrel comprising: a first portion (16) extending axially over a part of said barrel located at a distance from the flanges, said first portion having an internal face (16a) covered by an abradable coating (18) and being intended to be positioned opposite the tops of the blades (11) of the fan (1); and a second portion (20) located between the first portion and a flange, an acoustic coating (22) being present on an external face (22a) of said second portion, all or part of said second portion comprising perforations (24), the process comprising the following steps:
    a) shaping a fibrous preform (100) intended to form the fibrous reinforcement of the casing on a tool (200) having the shape of said casing,
    b) insertion of needles (311) into at least one portion of the shaped preform corresponding to the second portion (20) of the barrel of the casing,
    c) impregnation of the preform obtained after step b) with a matrix precursor resin and heat treatment of the impregnated preform so as to obtain a preform densified by the matrix,
    d) withdrawal of the needles from the densified preform in step c) so as to obtain the perforations (24) in the second portion of the barrel of the casing, and
    e) formation of the acoustic coating (22) on all or part of the external face (20a) of the second portion (20) of the casing of the casing.
    [10" id="c-fr-0010]
    10. The method of claim 9, wherein the step of forming the acoustic coating (22) comprises fixing a plurality of acoustic panels on the external face (22a) of the second portion (20) of the casing of the casing. (10).
    2/4
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    同族专利:
    公开号 | 公开日
    FR3059044B1|2020-09-25|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20030156940A1|2002-02-15|2003-08-21|General Electric Company|Fan casing acoustic treatment|
    US20100065367A1|2008-09-17|2010-03-18|General Electric Company|Method of Manufacture of Composite Laminates, an Assembly Therefor, and Related Articles|
    FR3031469A1|2015-01-14|2016-07-15|Snecma|CARRIER IN MATERIAL COMPOSITE WITH ORGANIC MATRIX AUTO-RAIDI|FR3085447A1|2018-09-04|2020-03-06|Safran Aircraft Engines|BLOWER HOUSING FOR AN AIRCRAFT TURBOMACHINE DIRECTLY INTEGRATING ABRADABLE PORTIONS AND HAVING ACOUSTIC PROPERTIES|
    WO2021009457A1|2019-07-15|2021-01-21|Safran Aircraft Engines|Method for producing a casing for an aircraft turbine engine|
    FR3108867A1|2020-04-07|2021-10-08|Safran Aircraft Engines|Mold for the manufacture of a turbine engine fan casing in composite material|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-25| PLSC| Publication of the preliminary search report|Effective date: 20180525 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661359A|FR3059044B1|2016-11-22|2016-11-22|AERONAUTICAL TURBOMACHINE BLOWER HOUSING|
    FR1661359|2016-11-22|FR1661359A| FR3059044B1|2016-11-22|2016-11-22|AERONAUTICAL TURBOMACHINE BLOWER HOUSING|
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