US20130171000A1 - Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades - Google Patents

Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades Download PDF

Info

Publication number
US20130171000A1
US20130171000A1 US13/820,791 US201113820791A US2013171000A1 US 20130171000 A1 US20130171000 A1 US 20130171000A1 US 201113820791 A US201113820791 A US 201113820791A US 2013171000 A1 US2013171000 A1 US 2013171000A1
Authority
US
United States
Prior art keywords
vane
turbojet
casing
leading edge
trailing edge
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
Application number
US13/820,791
Other languages
English (en)
Inventor
Richard Masson
Patrick Dunleavy
Bertrand Desjoyeaux
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Safran Landing Systems SAS
Original Assignee
Messier Bugatti Dowty SA
Aircelle SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Messier Bugatti Dowty SA, Aircelle SA filed Critical Messier Bugatti Dowty SA
Assigned to MESSIER-BUGATTI-DOWTY, AIRCELLE reassignment MESSIER-BUGATTI-DOWTY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DESJOYEAUX, BERTRAND, DUNLEAVY, PATRICK, MASSON, RICHARD
Publication of US20130171000A1 publication Critical patent/US20130171000A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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

  • Vanes made of composite material that have ends carrying fastener means for fastening them to annular casings of a turbojet.
  • the object of the invention is thus to propose a turbojet vane that is simple to produce and easy to mount.
  • turbojet vane in particular a compressor guide vane comprising the following elements:
  • the vane includes a core-forming central portion arranged between the leading edge and the trailing edge, and preferably, the leading edge and the trailing edge present extensions that project from the core from at least one end of the vane in order to form attachment means for attaching the vane to a casing of the turbojet.
  • the leading and/or the trailing edge comprises an elongate body obtained by pultrusion and impregnated with thermoplastic resin having fibers that are arranged essentially along a longitudinal axis of the leading and/or trailing edge. If the vanes are of constant section, then the leading and/or trailing edges may be cut to length from a section member bar made in the manner described. Such a technique makes it possible to obtain a leading edge and a trailing edge capable of withstanding high levels of stress.
  • the invention also provides a turbojet specially adapted to receive such vanes, each vane being fastened to at least one casing in such a manner that the attachment means of the vane co-operate with complementary attachment means of the casing.
  • the attachment means of the casing are obtained by pultrusion and impregnated with thermoplastic resin, and they are assembled to the casing by hot compaction.
  • FIG. 1 is a plan view of a vane of the invention
  • FIG. 2 is a perspective view of the FIG. 1 vane, the skin covering the core of the vane being partially cut away;
  • FIG. 3 is a perspective view of a first technique for fastening the vane to a casing
  • FIG. 4 is a perspective view of a second technique for fastening the vane to the casing.
  • the vane 1 shown therein is a guide vane for extending behind the fan of a turbojet.
  • the vane 1 has a leading edge 2 that is in the form of a one-piece elongate structure.
  • the vane 1 also has a trailing edge 3 that is likewise in the form of a one-piece elongate structure.
  • the leading edge 2 and the trailing edge 3 are cut from section members obtained by pultrusion, preferably with fibers being placed obliquely (the so-called “pullbraiding” method).
  • the section members have fibers, e.g. carbon fibers, that are arranged essentially along a longitudinal axis in order to form an elongate body.
  • substantially 80% of the fibers are arranged along the longitudinal axis X of the leading edge and along the longitudinal axis Y of the trailing edge, and 20% of the fibers are arranged at an angle of inclination of about 60 degrees relative to the longitudinal axis.
  • the fibers are impregnated in thermoplastic resin.
  • a skin 5 is made up in this example of two webs 5 A and 5 B that are obtained by being cut out from a fiber fabric that has been pre-impregnated with thermoplastic resin, the webs extending on either side of the core 4 so as to cover both the core and also zones of the leading edge 2 and of the trailing edge 3 that are contiguous with the core 4 .
  • the faces of the core 4 that are not covered by the webs 5 A and 5 B form free ends of the core 4 , and in this example they are protected and reinforced by means of a mixture 22 of short fibers and of resin inserted in a cavity defined by the webs 5 A and 5 B and the free edge of the core 4 .
  • the leading edge 2 and the trailing edge 3 include extensions 10 , 11 , 12 , and 13 that extend projecting from the core 4 at each end of the vane 1 .
  • the various components of the vane 1 are assembled together by hot compaction so as to join the components of the assembly to one another. This type of assembly imparts great strength to the vane 1 as a whole.
  • orifices 14 , 15 , 16 , and 17 are formed in the extensions 10 , 11 , 12 , and 13 so as to transform the extensions into means for attaching the vane 1 , which means are designed to co-operate with complementary attachment means in a casing of the turbojet, as described below in detail with reference to FIGS. 3 and 4 .
  • FIG. 3 shows a first technique for fastening the vane 1 to an annular turbojet casing 20 .
  • the casing 20 has orifices 26 for passing the extensions 10 and 12 of the leading edge 2 and of the trailing edge 3 through the casing 20 .
  • the orifices 26 are shown as being of sufficient extent to allow the extensions from both the leading edge and the trailing edge to pass through the same orifice. Nevertheless, in a variant, it would be possible to make the orifices in two portions, comprising an upstream orifice and a downstream orifice respectively for passing the end of the leading edge and the end of the trailing edge.
  • the casing 20 is fitted with means for attaching the leading edges, which means are in the form of a peripheral rail 21 extending around the casing on a face thereof that faces away from the vanes.
  • the rail 21 defines a housing suitable for receiving the heads 24 of fastener elements 23 that are generally T-shaped or L- shaped. One of these elements is shown in the figure.
  • the fastener element 23 has an opposite end 25 that is remote from its head 24 and that is cut so as to receive the extension 10 of the leading edge.
  • the fastener element 23 is joined to the extension 10 by pinning.
  • the end 25 includes an orifice (not shown in the drawing) that is situated in register with the orifice 14 in the extension 10 of the leading edge 2 in order to receive a fastener pin 27 .
  • the extension 12 of the trailing edge 3 is fastened in similar manner by means of a second rail 21 ′ in which a second fastener element 23 ′ is engaged to co-operate with the extension 12 of the trailing edge 3 , the assembly being pinned together with the help of a pin 27 ′.
  • the rails 21 and 21 ′ and the fastener elements 23 and 23 ′ are made by pultrusion and they are impregnated with thermoplastic resin, thus enabling the entire assembly to be joined together by a single hot compaction operation on the casing 20 .
  • FIG. 3 shows only half of the vane 1 .
  • the terminal portions 11 and 13 that are not shown are fastened to an inner casing in a manner that is identical to that described above. Nevertheless, if the vane does not have a structural function, the vane needs to be fastened to only one of the casings.
  • FIG. 4 shows a second technique for fastening the vane 1 to a turbojet casing 20 .
  • the attachment means comprise an angle bar 30 arranged peripherally all around the casing.
  • the angle bar 30 extends over a face of the casing 20 facing away from the vane 1 .
  • the casing 20 has through orifices 26 for passing the extensions of the leading and trailing edges of the vane through the casing 20 so that they face the angle bar 30 .
  • the angle bar 30 is made by pultrusion and is impregnated with thermoplastic resin.
  • the angle bar 30 has an L-shaped section with a first face 28 that is fastened to the casing 20 by hot compaction and a second face 29 that is fastened to the extension 10 by pinning.
  • the face 29 of the angle bar 30 is pierced by an orifice that comes into register with the orifice 114 formed in the extension 10 of the leading edge.
  • the orifice 114 is formed perpendicularly relative to the orifice 14 of the above-described embodiment.
  • the extension 10 has been machined to present a flat face that comes to bear against the facing face of the flange 29 .
  • thermocompaction As in the above-described example, the various elements of the casing are joined together by thermocompaction.
  • extensions 11 , 12 , and 13 of the leading edge 2 and of the trailing edge 3 that are not shown are fastened in identical manner to respective similar angle bars.
  • the materials used for making the various elements 2 , 3 , 4 , 5 of the vane 1 and for making the attachment means 21 , 23 , 27 may equally well be composite materials or metals or a combination of both.
  • the reinforcements 22 that are visible in FIG. 2 covering the free ends of the core 4 may be replaced by or associated with the skin of one or both of the webs 5 A, 5 B being folded over. Under such circumstances, the dimensions of the webs 5 A, 5 B should be adjusted to leave a flap suitable for covering the free end of the core.
  • attachment means of the casing and the attachment means of the leading and trailing edges may be joined together by operations involving hot compaction, welding, adhesive, or indeed by using nut- and-bolt fasteners or any other solution that serves to hold the elements together.
  • FIGS. 3 and 4 suggest identical fastener means for each of the extensions 10 , 11 , 12 , 13 of the leading edge 2 and of the trailing edge 3 in two different embodiments, it is not contrary to the invention for each extension to be fastened to the casing 20 using one or the other of the fastener means in independent manner.
  • the core may be reinforced in part or in full with short fibers.
  • the core may be arranged to fill the volume extending between the leading edge and the trailing edge in full or only in part.
  • the central portion may also have the shape of one or more core-forming strips.
  • the vane need not have a central core, the portions forming the leading and trailing edges then being contiguous.
  • the vane may include a core of low mechanical strength or it may have no core: the mechanical connection between the leading and trailing edges is provided by the skin and/or by the reinforcements, with the core and the reinforcements preferably being made out of a single piece of plastics resin incorporating short fibers.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Architecture (AREA)
  • Composite Materials (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/820,791 2010-09-06 2011-09-05 Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades Abandoned US20130171000A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1057070A FR2964411B1 (fr) 2010-09-06 2010-09-06 Aube de turboreacteur, notamment une aube de redresseur, et turboreacteur recevant de telles aubes
FR1057070 2010-09-06
PCT/EP2011/065338 WO2012032016A1 (fr) 2010-09-06 2011-09-05 Aube de turboreacteur, notamment une aube de redresseur, et turboreacteur recevant de telles aubes

Publications (1)

Publication Number Publication Date
US20130171000A1 true US20130171000A1 (en) 2013-07-04

Family

ID=43844601

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/820,791 Abandoned US20130171000A1 (en) 2010-09-06 2011-09-05 Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades

Country Status (8)

Country Link
US (1) US20130171000A1 (fr)
EP (1) EP2614221B1 (fr)
CN (1) CN103080476B (fr)
BR (1) BR112013005104A2 (fr)
CA (1) CA2810184C (fr)
FR (1) FR2964411B1 (fr)
RU (1) RU2544102C2 (fr)
WO (1) WO2012032016A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140227100A1 (en) * 2011-09-23 2014-08-14 Howden Solyvent-Ventect Rotating Machine Blade with Reinforced Modular Structure

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140112796A1 (en) * 2012-10-23 2014-04-24 General Electric Company Composite blade with uni-tape airfoil spars
RU2640889C1 (ru) * 2016-10-14 2018-01-12 федеральное государственное бюджетное образовательное учреждение высшего образования "Пермский национальный исследовательский политехнический университет" Способ формования лопатки спрямляющего аппарата
RU173787U1 (ru) * 2016-10-14 2017-09-11 федеральное государственное бюджетное образовательное учреждение высшего образования "Пермский национальный исследовательский политехнический университет" Лопатка спрямляющего аппарата
DE102016123712A1 (de) * 2016-12-07 2018-06-07 Maschinenfabrik Gustav Eirich Gmbh & Co. Kg Mischflügel mit Verschleißelement sowie Verfahren zum Befestigen eines Verschleißelementes an einem Grundteil eines Mischflügels

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US267405A (en) * 1882-11-14 debes
US748912A (en) * 1904-01-05 Type-writing machine
US3674379A (en) * 1969-01-30 1972-07-04 Siai Marchetti Spa Helicopter rotor blade
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
US4470862A (en) * 1982-05-27 1984-09-11 United Technologies Corporation Manufacture of fiber reinforced articles
US4648921A (en) * 1980-10-02 1987-03-10 United Technologies Corporation Method of making fiber reinforced articles
US5462408A (en) * 1992-12-23 1995-10-31 Europcopter France Blade made of thermoplastic composite, in particular for ducted tail rotor of a helicopter, and its method of manufacture
US5547342A (en) * 1993-12-22 1996-08-20 Alliedsignal Inc. Insertable stator vane assembly
US6375863B1 (en) * 1998-10-30 2002-04-23 Toray Industries, Inc. Thermoplastic resin composition, production thereof, and molded article thereof
US20020071760A1 (en) * 2000-12-08 2002-06-13 Dingwell William Terence Variable stator vane bushing
US6409472B1 (en) * 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
US8198356B2 (en) * 2008-08-29 2012-06-12 E I Du Pont De Nemours And Company Composite parts for airplane engines

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU503024A1 (ru) * 1974-05-28 1976-02-15 Предприятие П/Я Р-6378 Рабочее колесо осевой турбомашины
US5403153A (en) * 1993-10-29 1995-04-04 The United States Of America As Represented By The Secretary Of The Air Force Hollow composite turbine blade
US6494677B1 (en) * 2001-01-29 2002-12-17 General Electric Company Turbine nozzle segment and method of repairing same
DE10307610A1 (de) * 2003-02-22 2004-09-02 Rolls-Royce Deutschland Ltd & Co Kg Verdichterschaufel für ein Flugzeugtriebwerk
AT503840B1 (de) * 2006-06-30 2010-09-15 Facc Ag Leitschaufelanordnung für ein triebwerk
GB2458685B (en) * 2008-03-28 2010-05-12 Rolls Royce Plc An article formed from a composite material
RU95046U1 (ru) * 2009-12-21 2010-06-10 Общество с ограниченной ответственностью "Научно-производственное предприятие Вакууммаш" Пустотелая лопатка турбомашины

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US267405A (en) * 1882-11-14 debes
US748912A (en) * 1904-01-05 Type-writing machine
US3674379A (en) * 1969-01-30 1972-07-04 Siai Marchetti Spa Helicopter rotor blade
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
US4648921A (en) * 1980-10-02 1987-03-10 United Technologies Corporation Method of making fiber reinforced articles
US4470862A (en) * 1982-05-27 1984-09-11 United Technologies Corporation Manufacture of fiber reinforced articles
US5462408A (en) * 1992-12-23 1995-10-31 Europcopter France Blade made of thermoplastic composite, in particular for ducted tail rotor of a helicopter, and its method of manufacture
US5547342A (en) * 1993-12-22 1996-08-20 Alliedsignal Inc. Insertable stator vane assembly
US6375863B1 (en) * 1998-10-30 2002-04-23 Toray Industries, Inc. Thermoplastic resin composition, production thereof, and molded article thereof
US6409472B1 (en) * 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
US20020071760A1 (en) * 2000-12-08 2002-06-13 Dingwell William Terence Variable stator vane bushing
US8198356B2 (en) * 2008-08-29 2012-06-12 E I Du Pont De Nemours And Company Composite parts for airplane engines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140227100A1 (en) * 2011-09-23 2014-08-14 Howden Solyvent-Ventect Rotating Machine Blade with Reinforced Modular Structure
US10408060B2 (en) * 2011-09-23 2019-09-10 Howden Solyvent-Ventec Rotating machine blade with reinforced modular structure

Also Published As

Publication number Publication date
BR112013005104A2 (pt) 2016-05-03
EP2614221B1 (fr) 2015-04-15
EP2614221A1 (fr) 2013-07-17
FR2964411A1 (fr) 2012-03-09
CN103080476A (zh) 2013-05-01
CN103080476B (zh) 2015-03-11
CA2810184A1 (fr) 2012-03-15
CA2810184C (fr) 2015-09-01
FR2964411B1 (fr) 2012-08-24
WO2012032016A1 (fr) 2012-03-15
RU2544102C2 (ru) 2015-03-10
RU2013115374A (ru) 2014-10-20

Similar Documents

Publication Publication Date Title
US20130171000A1 (en) Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades
JP6251579B2 (ja) 荷重を担持するボックス構造体、およびその製作方法
EP2264310B1 (fr) Procédé d'assemblage de pale d'éolienne
US9957972B2 (en) Airfoil with an integrally stiffened composite cover
US6676373B2 (en) Assembly formed by at least one blade and a blade-fixing platform for a turbomachine, and a method of manufacturing it
US20130251519A1 (en) Turbojet casing and turbojet receiving such casings
US6779757B2 (en) Preforms for acute structural edges
CN108930611B (zh) 用于制造和组装推力反向器叶栅的方法
US9248900B2 (en) Tip fairing of a horizontal airfoil of an aircraft
US9217333B2 (en) Composite-material vane
US20110254267A1 (en) Composite Flange, Duct Incorporating a Flange and Method of Making a Flange
EP3527812B1 (fr) Cascade d'inverseur de poussée
US20150034763A1 (en) Aircraft fuselage frame element integrating tabs for the fastening of stiffeners
US20170101878A1 (en) Low modulus insert for a component of a gas turbine engine
US20140322482A1 (en) Composite article including composite to metal interlock and method of fabrication
US20100264273A1 (en) Fuselage structure for an aircraft fuselage in composite material and aircraft equipped with such a fuselage structure
CN105874169A (zh) 叶片的连结部构造以及使用该叶片的连结部构造的喷气式发动机
US10738738B2 (en) Nacelle with bifurcation extension and integral structural reinforcement
EP3974641B1 (fr) Réseau d'inverseur de poussée en cascade et son procédé de production
EP2971527B1 (fr) Construction de pale de soufflante hybride avec noyau comprimé
US10450052B2 (en) Sandwich structure
EP4365077A1 (fr) Profil aérodynamique et ses procédés d'assemblage

Legal Events

Date Code Title Description
AS Assignment

Owner name: AIRCELLE, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MASSON, RICHARD;DESJOYEAUX, BERTRAND;DUNLEAVY, PATRICK;REEL/FRAME:029925/0971

Effective date: 20130218

Owner name: MESSIER-BUGATTI-DOWTY, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MASSON, RICHARD;DESJOYEAUX, BERTRAND;DUNLEAVY, PATRICK;REEL/FRAME:029925/0971

Effective date: 20130218

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION