EP2829687A1 - Confinement de boîtier et procédé de fabrication - Google Patents

Confinement de boîtier et procédé de fabrication Download PDF

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Publication number
EP2829687A1
EP2829687A1 EP14177235.0A EP14177235A EP2829687A1 EP 2829687 A1 EP2829687 A1 EP 2829687A1 EP 14177235 A EP14177235 A EP 14177235A EP 2829687 A1 EP2829687 A1 EP 2829687A1
Authority
EP
European Patent Office
Prior art keywords
structures
housing part
energy
housing
turbomachine
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.)
Granted
Application number
EP14177235.0A
Other languages
German (de)
English (en)
Other versions
EP2829687B1 (fr
Inventor
Sven-Jürgen Hiller
Peter Geiger
Erwin Bayer
Thomas Hess
Jens Wittmer
Petra Kufner
Rudolf Stanka
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2829687A1 publication Critical patent/EP2829687A1/fr
Application granted granted Critical
Publication of EP2829687B1 publication Critical patent/EP2829687B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6034—Orientation of fibres, weaving, ply angle
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/61—Syntactic materials, i.e. hollow spheres embedded in a matrix

Definitions

  • the present invention relates to a housing part for a turbomachine, such as a stationary gas turbine or an aircraft engine, which surrounds the flow channel of the turbomachine at least partially in the circumferential direction and comprises a circumferentially extending wall, on the radially outer side of energy absorbing structures are formed in a radially outward mechanical action to a large extent absorb energy.
  • a turbomachine such as a stationary gas turbine or an aircraft engine
  • the present invention relates to a method for producing a corresponding housing part.
  • turbomachines such as stationary gas turbines or aircraft engines
  • fast moving blades are used in the compressor or the turbine, which move at high speed about an axis of rotation along the longitudinal axis (axial direction) of the turbomachine. Due to the high rotational speeds of the blades, there is a risk that a fragment of the blade breaks through the surrounding housing in case of breakage of a blade and causes damage outside of the turbomachine due to the high centrifugal forces.
  • fragments of blades have to be prevented from leaving the housing to avoid that caused by leaking fragments damage to the aircraft structure, such as the wings or the passenger cabin.
  • the invention is based on the recognition that complex energy-absorbing structures, which allow optimal energy absorption of the kinetic energy of fragments of rotor blades, can be generated in layers by means of generative production processes.
  • generative manufacturing processes make it possible to produce very complex energy-absorbing structures in a simple manner, so that the conflict of objectives can be achieved, on the one hand, with optimal energy-absorbing structures which have a certain complexity and, on the other hand, with simple production processes.
  • various methods can be used in which a layered structure of a component made of powder materials is possible, such as selective laser welding or selective electron beam welding, in which by laser beams or electron beams powdery material particles in the areas of powder layers in which the corresponding component is to arise to be welded together.
  • laser particles or electron beams also powder particles can be sintered together, so that selective laser beam sintering or selective Electron beam can be used internally.
  • components can be produced layer by layer by cold gas spraying of powder, wherein the powder particles are injected at high speed, so that they weld cold. This method can thus be used for the generative production of corresponding housing parts.
  • other generative manufacturing processes in which powder particles are bonded together in layers, can be used.
  • complex component geometries and / or material composites as energy-absorbing structures, which enable optimum energy absorption with respect to radially outward mechanical action by fragments of moving blades.
  • complex component geometries here are understood forms of components that can absorb as much energy of an incident fragment of a blade by a corresponding movement and / or deformation.
  • composite materials ie components made of different materials or material components, can be used to effectively reduce the kinetic energy of impacting debris.
  • the geometric structures may include cavity structures, hollow sphere structures, honeycomb structures, layer structures, fiber structures, fabric structures, lattice structures, chain structures, network structures, radially extending structures, and other deformation structures.
  • Hollow structures are understood to be structures in which defined cavities are provided so that the surrounding material can undergo a corresponding deformation or fracture without a forming crack being able to run directly through the entire component.
  • a cavity structure offers the arrangement of hollow spheres, which may in particular be firmly connected to each other.
  • honeycomb structures ie structures in the form of honeycombs, may also be provided.
  • lattice structures can be used as cavity structures, which can be formed by transversely interconnected webs in the form of a truss. Grids here mean not only a grating in the mathematical sense, but any arrangement of web-like parts in two- or dimensional form with the formation of gaps.
  • Fiber structures are structures in which fiber materials with or without surrounding matrix material or an embedding are arranged along the wall surrounding the flow channel, wherein the longitudinal direction of the fibers can be aligned in the circumferential direction around the flow channel. Additionally or alternatively, however, the fibers may also in a longitudinal direction, be arranged as parallel to the axial direction of the housing part. As fibers come different fiber materials in question, such as plastic fibers and aramid fibers in particular.
  • Tissue structures are understood to be structures of thread-like structures which cross each other transversely to form a tissue.
  • the threads in the tissue structure can cross each other perpendicularly and a plurality of flat tissues can be arranged in a single core.
  • fabric structures with their transverse and in particular perpendicular to each other arranged filaments or thread-like structures provide particularly stable and thus energy-absorbing structures.
  • the threads or thread-like structures can not be firmly connected to each other at their points of intersection, so that they are movable relative to each other.
  • the fabric structures can have threads with a wave structure that form wave troughs and wave crests, the valleys and mountains being radially spaced apart.
  • reinforcement webs can be woven into these fabric structures, which restrict the movement of the threads during bracing in the event of a fragment hits and promote energy absorption.
  • the energy-absorbing chain structures can be individual linear chains with form-fitting interlocking chain links or flat, ie two-dimensional, or three-dimensional, ie three-dimensional chain structures with superimposed and juxtaposed linear chains, which can additionally be linked to one another.
  • Both the chain structures and the network structures and / or the fabric structures can be arranged one above the other in one or more layers, in particular in the radial direction.
  • Folding structures are structures in which a predetermined folding takes place when a mechanical action, such as, for example, the impact of a fragment of a moving blade, takes place in the radial direction.
  • a folding structure may be formed by an accordion structure in which a plurality of sheet-like plate-like members are arranged at an angle to each other, so that deformation work is required at the connecting portions between the plate-shaped members when the sheet-like plate-like members are pressed against each other and the folding structure is folded.
  • meander-like structures or comparable structures can be provided, in which deformation work must be expended by the folding or compression.
  • folding structures can be provided as individual structures in a reinforcing area (containment) of a housing part or a plurality of folding structures can be arranged next to one another in the axial direction.
  • further deformation structures in which a high energy absorption is possible in the case of deformation in the radial direction, can be provided which have different shapes.
  • radially extending structures ie components or components with the maximum dimension in the radial direction in the gain region (containment) may be arranged in order to effectively reduce the kinetic energy of a fragment of a blade upon impact.
  • material composites which can bring about high energy absorption due to the different phases and components of materials and the phase boundaries therebetween.
  • hard and ductile materials such as ceramics and metals may be combined, with the ductile materials avoiding catastrophic crack growth complete failure, while the hard materials may have high fracture energies.
  • material composites with different materials such as metallic and / or ceramic and / or polymeric materials and combinations thereof may also be combined with different component geometries.
  • Generative manufacturing processes can be used to produce structures that are fully generative, as well as structures where only parts are generatively produced while other parts are conventionally produced.
  • housing parts can be produced with reinforcement areas (containment), which at least partially a metallic double wall structure, which includes a housing cavity in which ceramic hollow balls are arranged, which are materially connected to each other, for example by sintering or by binder.
  • reinforcement areas (containment)
  • the metallic double-wall structure can be produced by a generative manufacturing process, while the ceramic hollow spheres are then filled into the cavity and bonded together by sintering or a correspondingly filled binder cohesively.
  • the sintering process can also be favored by a ceramic nanopowder or by an organometallic metal compound.
  • the Fig. 1 shows a partial section through a turbomachine, such as an aircraft engine, with a housing part 1, which surrounds a flow channel 2, which extends axially along the longitudinal axis 3.
  • a turbomachine such as an aircraft engine
  • rotating disks 4 are mounted, on which blades 5 are arranged.
  • the blades 5 move at high rotational speed about the longitudinal axis 3, as indicated by the arrow. If, for example, a penetrating foreign body or some other reason causes a blade 5 to break, the fragment 5 'of the blade 5 is accelerated radially outwards due to the centrifugal forces, where it threatens to penetrate the housing 1.
  • the reinforcing regions 6 are formed as a closed double wall structures of the housing 1, which include a housing cavity in which a ceramic hollow spherical structure 7 is arranged.
  • the housing part 1 is produced according to the invention by a generative manufacturing method, such as selective laser welding.
  • the structure of the housing part 1 takes place along the longitudinal axis or axial direction, as shown by the arrow 9.
  • the housing part 1 is in this case constructed generatively from a metallic material, wherein metal powder is applied in layers.
  • the housing part 1 in this case essentially comprises a cylindrical wall 8 surrounding the flow channel, which wall is double-walled in the reinforcing area 6 in order to form a housing cavity in which the ceramic hollow spheres can be arranged.
  • the metallic double-wall structure 8 is initially generatively constructed in the reinforcement region 6 in order to form the housing cavity 10.
  • ceramic hollow spheres 11 are filled with or without a binder, such as an organic platinum compound.
  • the housing part 1 is subjected to a heat treatment in order to sinter the ceramic hollow spheres and the possibly filled binder.
  • ceramic nanoparticles can be used as binders in order to facilitate a cohesive connection of the ceramic hollow spheres with one another.
  • the heat treatment may also be performed prior to sealing the housing cavity 10 to allow escape of the housing cavity 10 from the organic constituent which decomposes during the heat treatment.
  • a) to d) complex component geometries and material composites can be produced as energy-absorbing structures in a cheap and simple way.
  • an arbitrarily shaped double wall structure 8 made of a metallic material can be formed and combined with a ceramic hollow spherical structure 7 in order to prevent fragments 5 'of moving blades from leaving the housing 1.
  • the fragment 5' If a fragment 5 'hits the reinforcing region 6 of the housing 1, the fragment 5' must first break through the radially inner edge region of the metallic double wall structure 8 and then the ceramic hollow spherical structure 7, whereby the deformation of the metallic hollow wall structure and the ceramic hollow sphere structure much energy is absorbed that the fragment 5 'is prevented from leaving the housing 1.
  • the Fig. 4 shows a further housing part 1 'with a reinforcing region 6', in which another embodiment of an energy absorbing structure is provided.
  • the energy absorbing structure of the embodiment of the Fig. 4 is formed by a plurality of parallel, in the axial direction juxtaposed, radially oriented folding structures 13, whose longitudinal extent, that is, the direction with the largest length dimension, is radially aligned.
  • the folding structure 13 is formed by a plurality of plate portions 21, which are arranged at an acute angle along edges 23 to each other, wherein the edges 22 in the radial direction one behind the other and alternately axially offset, so that there is a concertina structure.
  • the folding structure 13 Upon impact of a fragment 5 ', the folding structure 13 is bent along the edges 22, so that the plate region 21 are moved towards each other. As a result, deformation energy is consumed and at the same time a thick wall area is provided, which must be penetrated by the impinging fragment 5 '.
  • the Fig. 5 shows a further embodiment of a housing part according to the invention 1 "with a gain region 6", which also, as the gain region 6 'of Fig. 4 with the Folded structure 13, so that not only the double-wall structure of the reinforcing region 6 ", but also the energy-absorbing structure accommodated in the housing cavity can be produced generatively, thus enabling complex component geometries and / or material combinations to be realized Ensure energy absorption.
  • the energy-absorbing structure is formed by a layer structure 14, which is formed from a plurality of individual layers arranged one above the other in the radial direction, wherein the individual layers can be formed from different materials.
  • a layer structure 14 which is formed from a plurality of individual layers arranged one above the other in the radial direction, wherein the individual layers can be formed from different materials.
  • different component geometries can be realized in the individual layers, such as cavity structures, honeycomb structures, lattice structures and the like.
  • the Fig. 6 shows yet another embodiment of a housing component according to the invention 1 "'with a reinforcing region 6"', in which a plurality of energy absorbing structures in the form of inserts 15 are provided, which may be arranged in separate housing cavities or in a common housing cavity.
  • the inserts 15 are formed as radially superimposed and axially offset from one another deposits 15.
  • the Fig. 7 shows a fabric structure 16, which may form, for example, an insert 15 of the housing part 1 "'.
  • the fabric structure 16 is formed of two layers, each woven from a plurality of parallel threads 17 and 18, the ends of the threads 17 and 18 being fixedly connected together. In between, the threads 17,18 are interwoven, so crossed. In the crossing region 19 of the fabric structure 16, the threads 17, 18 are not firmly connected to each other, but can move relative to each other.
  • the parallel threads 17, 18 each form a wave structure with corresponding wave crests and wave troughs, between the wave crests of a thread group and the troughs of the other thread group gaps are formed in which stiffening webs 20 are arranged.
  • an incident fragment 5 'of a blade 5 can initially cause the threads 17, 18 to move toward one another, so that the threads are tensioned, whereby an excessive movement of the threads 17, 18 is prevented by the stiffening webs 20.
  • the tensioning of the threads 17, 18 in the fabric structure 16 already absorbs energy.
  • further energy is provided by elastically deforming the filaments 17, 18 and the stiffening webs 20 absorbed.
  • energy would have to be applied for the tearing of the threads 17, 18, so that with such a structure there is an effective protection that no fragments of moving blades 5 leave the housing of a turbomachine.
  • Such a complex fabric structure 16, as shown in the Fig. 7 can also be generated by additive manufacturing processes.
  • the Fig. 8 shows a further embodiment of a housing part according to the invention 1 "" with a gain region 6 "".
  • a wall 8 surrounding the flow channel in the circumferential direction is provided on the radially outer side of which an energy-absorbing structure in the form of a chain structure 23 is provided.
  • the chain structure consists of a plurality of chain links which are arranged in a three-dimensional structure in one another in the manner of a chainmail. Also, such a structure can be produced by a generative manufacturing process in a favorable manner.
  • a chain structure 23 can also be provided in a housing cavity, such as, for example, as an insert 15.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Vibration Dampers (AREA)
EP14177235.0A 2013-07-23 2014-07-16 Procédé de fabrication d'un boîtier de confinement Not-in-force EP2829687B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013214389.3A DE102013214389A1 (de) 2013-07-23 2013-07-23 Gehäusecontainment

Publications (2)

Publication Number Publication Date
EP2829687A1 true EP2829687A1 (fr) 2015-01-28
EP2829687B1 EP2829687B1 (fr) 2017-09-06

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14177235.0A Not-in-force EP2829687B1 (fr) 2013-07-23 2014-07-16 Procédé de fabrication d'un boîtier de confinement

Country Status (3)

Country Link
EP (1) EP2829687B1 (fr)
DE (1) DE102013214389A1 (fr)
ES (1) ES2641197T3 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3660282A1 (fr) * 2018-11-27 2020-06-03 Honeywell International Inc. Système de confinement pour turboréacteur
US20210324759A1 (en) * 2018-07-13 2021-10-21 Rolls-Royce Plc Manufacture of a fan track liner

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015013182A1 (de) * 2015-10-10 2017-04-13 Diehl Defence Gmbh & Co. Kg Gehäuse für ein Getriebe und Verwendung eines additiven Fertigungsverfahrens
US11262804B2 (en) * 2020-06-11 2022-03-01 Dell Products L.P. Ultra thin information handling system housing with hybrid assembly

Citations (13)

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US4547122A (en) 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
FR2581400A1 (fr) * 1985-05-02 1986-11-07 Snecma Tissu composite destine a la realisation d'anneaux de retention pour turbomachines et procede pour leur mise en oeuvre
EP0286815B1 (fr) 1987-04-15 1991-05-29 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Anneaux de rétention pour carter de turbomachine
FR2663412A1 (fr) * 1990-06-18 1991-12-20 Gen Electric Bouclier de protection contre les projectiles.
US5403148A (en) 1993-09-07 1995-04-04 General Electric Company Ballistic barrier for turbomachinery blade containment
DE19956444B4 (de) 1999-11-24 2004-08-26 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Leichtbauteils in Verbundbauweise
EP1589195A1 (fr) 2004-04-20 2005-10-26 ROLLS-ROYCE plc Dispositif de rétention des aubes pour turbine à gaz
US6979172B1 (en) 2002-01-03 2005-12-27 Saint-Gobain Ceramics & Plastics, Inc. Engine blade containment shroud using quartz fiber composite
US20060165519A1 (en) 2005-01-21 2006-07-27 Mcmillan Alison J Aerofoil containment structure
EP1726787A2 (fr) 2005-05-24 2006-11-29 Rolls-Royce plc Anneau de rétention pour un moteur d'avion
DE102007042767A1 (de) 2007-09-07 2009-03-12 Mtu Aero Engines Gmbh Mehrschichtiger Abschirmungsring für einen Flugantrieb
EP2305985A2 (fr) * 2009-09-25 2011-04-06 Rolls-Royce plc Boîtier de confinement pour moteur d'avion
DE102011108957A1 (de) * 2011-07-29 2013-01-31 Mtu Aero Engines Gmbh Verfahren zum Herstellen, Reparieren und/oder Austauschen eines Gehäuses, insbesondere eines Triebwerkgehäuses, sowie ein entsprechendes Gehäuse

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US5160248A (en) * 1991-02-25 1992-11-03 General Electric Company Fan case liner for a gas turbine engine with improved foreign body impact resistance
US6916529B2 (en) * 2003-01-09 2005-07-12 General Electric Company High temperature, oxidation-resistant abradable coatings containing microballoons and method for applying same
DE102006041321A1 (de) * 2006-09-01 2008-03-06 Rolls-Royce Deutschland Ltd & Co Kg Gehäuseabschnitt, insbesondere Fangehäuse, für ein Gasturbinentriebwerk

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4547122A (en) 1983-10-14 1985-10-15 Aeronautical Research Associates Of Princeton, Inc. Method of containing fractured turbine blade fragments
FR2581400A1 (fr) * 1985-05-02 1986-11-07 Snecma Tissu composite destine a la realisation d'anneaux de retention pour turbomachines et procede pour leur mise en oeuvre
EP0286815B1 (fr) 1987-04-15 1991-05-29 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Anneaux de rétention pour carter de turbomachine
FR2663412A1 (fr) * 1990-06-18 1991-12-20 Gen Electric Bouclier de protection contre les projectiles.
US5403148A (en) 1993-09-07 1995-04-04 General Electric Company Ballistic barrier for turbomachinery blade containment
DE19956444B4 (de) 1999-11-24 2004-08-26 Mtu Aero Engines Gmbh Verfahren zur Herstellung eines Leichtbauteils in Verbundbauweise
US6979172B1 (en) 2002-01-03 2005-12-27 Saint-Gobain Ceramics & Plastics, Inc. Engine blade containment shroud using quartz fiber composite
EP1589195A1 (fr) 2004-04-20 2005-10-26 ROLLS-ROYCE plc Dispositif de rétention des aubes pour turbine à gaz
US20060165519A1 (en) 2005-01-21 2006-07-27 Mcmillan Alison J Aerofoil containment structure
EP1726787A2 (fr) 2005-05-24 2006-11-29 Rolls-Royce plc Anneau de rétention pour un moteur d'avion
DE102007042767A1 (de) 2007-09-07 2009-03-12 Mtu Aero Engines Gmbh Mehrschichtiger Abschirmungsring für einen Flugantrieb
EP2305985A2 (fr) * 2009-09-25 2011-04-06 Rolls-Royce plc Boîtier de confinement pour moteur d'avion
DE102011108957A1 (de) * 2011-07-29 2013-01-31 Mtu Aero Engines Gmbh Verfahren zum Herstellen, Reparieren und/oder Austauschen eines Gehäuses, insbesondere eines Triebwerkgehäuses, sowie ein entsprechendes Gehäuse

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20210324759A1 (en) * 2018-07-13 2021-10-21 Rolls-Royce Plc Manufacture of a fan track liner
US11448090B2 (en) * 2018-07-13 2022-09-20 Rolls-Royce Plc Fan track liner
US11746673B2 (en) * 2018-07-13 2023-09-05 Rolls-Royce Plc Manufacture of a fan track liner
EP3660282A1 (fr) * 2018-11-27 2020-06-03 Honeywell International Inc. Système de confinement pour turboréacteur
US11015482B2 (en) 2018-11-27 2021-05-25 Honeywell International Inc. Containment system for gas turbine engine
US11698001B2 (en) 2018-11-27 2023-07-11 Honeywell International Inc. Containment system for gas turbine engine

Also Published As

Publication number Publication date
DE102013214389A1 (de) 2015-01-29
EP2829687B1 (fr) 2017-09-06
ES2641197T3 (es) 2017-11-08

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