EP2288798A1 - Carter comprenant une ceinture peripherique pour rotor de turbomachine - Google Patents
Carter comprenant une ceinture peripherique pour rotor de turbomachineInfo
- Publication number
- EP2288798A1 EP2288798A1 EP09757683A EP09757683A EP2288798A1 EP 2288798 A1 EP2288798 A1 EP 2288798A1 EP 09757683 A EP09757683 A EP 09757683A EP 09757683 A EP09757683 A EP 09757683A EP 2288798 A1 EP2288798 A1 EP 2288798A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- belt
- carter
- housing
- casing
- fitting
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- 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
- 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
-
- 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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- 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
-
- 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
- the present invention relates to a casing for a turbomachine rotor, and more particularly to a turbojet fan casing.
- An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped, such as for example, a system of operation. thrust reversal.
- a nacelle generally has a structure comprising an air inlet upstream of the engine, a median section intended to surround a fan of the turbojet engine, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing means for thrust reversal.
- the blower of the turbojet engine essentially consists of a rotary shaft carrying a plurality of blades. At their radial end, the blades are surrounded circumferentially by a housing.
- Blower housings are generally machined metal elements.
- Such an embodiment makes it easy to add circumferential webs of structural reinforcement to a shell between the two ends of the housing, said webs then being able to also support engine or nacelle equipment.
- these housings can be made of composite material, especially carbon fiber.
- the present invention aims at overcoming the disadvantages mentioned above and consists for this purpose in a casing for a turbomachine rotor, more particularly for a turbojet fan, comprising a peripheral belt designed to form a clamping collar enclosing the housing, characterized in that the belt carries at least one fitting or a sail for attaching equipment.
- the latter can be used to support the attachment elements and accessory wings of a nacelle or turbojets to be fixed at said casing.
- the casing can thus be designed from the outset to receive fastening means determined and adapted to the belt and will not have to be modified to directly integrate the fittings and sails accessories. Furthermore, in case of addition of hardware or sails, they can be easily added to the belt without risking to damage the integrity of the housing by adding new fasteners.
- the belt is made from a resealable tape on itself.
- the belt is made from at least two partially peripheral strips and able to be joined together.
- the belt is made from two substantially half-peripheral strips.
- the belt is mainly metallic.
- the installation of fittings or sails can then be carried out as in the prior art.
- the belt is made mainly of composite material, in particular from braided composite fibers.
- the housing comprises abutments, located on either side of the belt so as to ensure the positioning and centering of the latter, and / or stops capable of preventing any rotational movement of the latter.
- the belt is glued to the housing.
- the housing has at least at the belt level, a surface having a coefficient of friction with at least a portion of a belt surface sufficient to limit or prevent rotation of the belt around the housing.
- the housing comprises at least two belts capable of holding each at least one base of at least one fitting, said base being inserted between the belt and the housing.
- the belt is held on the housing by at least one discrete fixing means.
- the present invention also relates to a propulsion unit comprising a turbojet engine housed in a nacelle, characterized in that it comprises a fan casing according to the invention.
- Figure 1 is a schematic representation in longitudinal section of a housing surrounding a blower of a turbojet engine.
- FIG. 2 is an enlarged partial cross-sectional view of a fastening of a belt according to the invention around the casing of FIG. 1.
- Figure 3 is a schematic representation of a fitting mounted on the belt of Figure 2, said fitting being oriented perpendicularly to the belt.
- Figure 4 is a schematic representation of a fitting mounted on the belt of Figure 2, said fitting being oriented in the plane of the belt.
- Figure 5 is an enlarged partial view in cross section of the belt of Figure 2 associated with a housing holding stop.
- Figure 6 is a partial schematic longitudinal sectional view of a belt disposed in a groove presented by the housing.
- Figure 7 is a schematic representation in longitudinal section of a fitting held on the housing with two belts according to the invention.
- Figure 8 is a partial schematic representation in longitudinal section of two belts held on the housing with the aid of discrete fixing means.
- FIG. 1 shows a fan 1 of a turbojet engine 2, said fan 1 comprising a rotary shaft 4 carrying a set of peripheral blades 3. At their radial end, the blades are surrounded circumferentially by a casing 5 ensuring aerodynamic continuity. internal between an inner wall of an air inlet structure (not visible) and an inner wall of a downstream section (not visible) of a nacelle.
- the housing 5 is surrounded by a peripheral belt 6 in the manner of a clamp.
- the belt 6 shown in Figure 2 is made from a resealable tape on itself around said housing 5 having to do two ends 7, 8 brought, in the closed position, facing one another preferably at a longitudinal median plane of the casing 5
- the belt 6 is kept closed around the casing 5 by a screw system 9 / nut 10.
- a screw system 9 / nut 10 Such a fixing system makes it easy to adapt the tightening of the belt 6 to the casing 5.
- Figures 3 and 4 each show a fitting 12, 13 carried by the belt 6.
- the fitting 12 has a foot 12a fixed in the belt 6 by means of fixing means 12b nuts.
- the fitting 12 is mounted perpendicularly to the belt 6.
- the fitting 13 has a foot 13a fixed in the belt 6 by means of fixing means 13b nuts.
- the fitting 13 is mounted in the axis at the waistband 6.
- FIGS. 3 and 4 illustrate the fact that the number, the size, the position, the orientation and the shape of the fittings can vary on the same belt 6, and their fixing is not dependent on the realization of particular fixing means on the housing.
- these lateral stops 16, 17 are constituted by the production of a peripheral groove 18 in the casing 5, the belt 6 being disposed inside said groove 18.
- the peripheral groove 18 is preferably made by machining in a local excess thickness of the housing 5.
- FIG. 7 illustrates another method of fastening a fitting 21 by two belts 6.
- the fitting 21 has a fastening foot 21a extending on either side of said bracket 21 along a longitudinal axis of the casing 5.
- the foot 21a thus has an upstream extension and a downstream extension which are each held by a belt 6 on the housing
- FIG. 8 is an example of distribution of belts 6 along a fan casing 5, the belts 6 being fixed in the casing by means of discrete fixing means distributed around the casing 5.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0803156A FR2932233B1 (fr) | 2008-06-06 | 2008-06-06 | Carter pour rotor de turbomachine |
PCT/FR2009/000366 WO2009147307A1 (fr) | 2008-06-06 | 2009-03-30 | Carter comprenant une ceinture peripherique pour rotor de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2288798A1 true EP2288798A1 (fr) | 2011-03-02 |
Family
ID=40184857
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09757683A Withdrawn EP2288798A1 (fr) | 2008-06-06 | 2009-03-30 | Carter comprenant une ceinture peripherique pour rotor de turbomachine |
Country Status (8)
Country | Link |
---|---|
US (1) | US20110085897A1 (fr) |
EP (1) | EP2288798A1 (fr) |
CN (1) | CN102016265B (fr) |
BR (1) | BRPI0912082A2 (fr) |
CA (1) | CA2726024A1 (fr) |
FR (1) | FR2932233B1 (fr) |
RU (1) | RU2511960C2 (fr) |
WO (1) | WO2009147307A1 (fr) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8206102B2 (en) * | 2007-08-16 | 2012-06-26 | United Technologies Corporation | Attachment interface for a gas turbine engine composite duct structure |
FR2963469B1 (fr) | 2010-07-27 | 2012-07-27 | Aircelle Sa | Panneau acoustique |
FR2966508B1 (fr) * | 2010-10-22 | 2015-04-03 | Snecma | Carter de soufflante de moteur aeronautique en materiau composite et procede pour sa fabrication |
CN103975142B (zh) * | 2011-12-07 | 2016-09-28 | 株式会社Ihi | 安装用凸台以及风扇壳 |
FR2995038B1 (fr) * | 2012-08-30 | 2014-09-19 | Snecma | Carter de soufflante de turbine a gaz ayant une ceinture de fixation d'equipements |
EP2733314B1 (fr) * | 2012-11-15 | 2017-04-05 | Safran Aero Boosters SA | Brides radiales de fixation et de positionnement pour viroles de carter de turbomachine axiale |
US10107202B2 (en) * | 2014-11-26 | 2018-10-23 | United Technologies Corporation | Composite fan housing assembly of a turbofan engine and method of manufacture |
FR3058343B1 (fr) * | 2016-11-04 | 2020-02-28 | Safran Aircraft Engines | Systeme d'usinage ameliore d'une bride de fixation d'un carter de turbomachine d'aeronef |
FR3074855A1 (fr) * | 2017-12-11 | 2019-06-14 | Airbus Operations | Grille pour la formation d'un flux d'inversion d'un turboreacteur d'aeronef |
CN108412644A (zh) * | 2018-03-05 | 2018-08-17 | 安徽江淮汽车集团股份有限公司 | 具有减震功能的空气滤清器安装底座 |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2548249A (en) * | 1946-07-01 | 1951-04-10 | Marman Products Co Inc | Band clamp |
US2997958A (en) * | 1960-06-13 | 1961-08-29 | Heinicke Pump Co | Centrifugal pump |
FR2514823B1 (fr) * | 1981-10-16 | 1986-06-27 | Poudres & Explosifs Ste Nale | Dispositif de protection contre l'eclatement d'elements rotatifs d'une machine tournante |
US4934899A (en) * | 1981-12-21 | 1990-06-19 | United Technologies Corporation | Method for containing particles in a rotary machine |
US4759521A (en) * | 1984-04-18 | 1988-07-26 | Aluma-Form, Inc. | Flexible banding and instrument support system |
US5226789A (en) * | 1991-05-13 | 1993-07-13 | General Electric Company | Composite fan stator assembly |
US5208569A (en) * | 1992-06-03 | 1993-05-04 | The United States Of America As Represented By The United States Department Of Energy | Simplified flangeless unisex waveguide coupler assembly |
DE4232385A1 (de) * | 1992-09-26 | 1994-03-31 | Asea Brown Boveri | Gasturbine mit angeflanschtem Abgasgehäuse |
DE4329014C1 (de) * | 1993-08-28 | 1995-01-05 | Mtu Muenchen Gmbh | Rotorgehäuse, insbesondere Gehäuse für Turbotriebwerke |
US20010048048A1 (en) * | 1999-01-13 | 2001-12-06 | Brian L Riedel | Backside fitting attachment for nacelle acoustic panels |
GB9922618D0 (en) * | 1999-09-25 | 1999-11-24 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
GB0206136D0 (en) * | 2002-03-15 | 2002-04-24 | Rolls Royce Plc | Improvements in or relating to cellular materials |
US6824471B2 (en) * | 2002-09-06 | 2004-11-30 | S. A. Armstrong Limited | Motor and pump shaft connecting assembly with shaft locating jack ring |
US6899574B1 (en) * | 2003-08-28 | 2005-05-31 | Garmin Ltd. | Transducer bracket |
GB2406627B (en) * | 2003-10-03 | 2008-05-07 | Rolls Royce Plc | Connecting arrangement |
FR2887931B1 (fr) * | 2005-06-29 | 2007-08-17 | Snecma | Dispositif de support et de logement de servitudes dans un turboreacteur a double flux |
DE102005033860A1 (de) * | 2005-07-13 | 2007-01-25 | Rolls-Royce Deutschland Ltd. & Co. Kg | Schutzring für das Fangehäuse eines Gasturbinentriebwerks |
FR2903732B1 (fr) * | 2006-07-12 | 2008-09-12 | Airbus France Sas | Entree d'air pour turbomoteur d'aeronef. |
US8475895B2 (en) * | 2006-11-21 | 2013-07-02 | General Electric Company | Articles comprising composite structures having mounting flanges |
US8021102B2 (en) * | 2006-11-30 | 2011-09-20 | General Electric Company | Composite fan containment case and methods of fabricating the same |
-
2008
- 2008-06-06 FR FR0803156A patent/FR2932233B1/fr not_active Expired - Fee Related
-
2009
- 2009-03-30 WO PCT/FR2009/000366 patent/WO2009147307A1/fr active Application Filing
- 2009-03-30 US US12/995,344 patent/US20110085897A1/en not_active Abandoned
- 2009-03-30 EP EP09757683A patent/EP2288798A1/fr not_active Withdrawn
- 2009-03-30 RU RU2010152292/06A patent/RU2511960C2/ru not_active IP Right Cessation
- 2009-03-30 CA CA2726024A patent/CA2726024A1/fr not_active Abandoned
- 2009-03-30 BR BRPI0912082A patent/BRPI0912082A2/pt not_active IP Right Cessation
- 2009-03-30 CN CN200980115270.4A patent/CN102016265B/zh not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2009147307A1 * |
Also Published As
Publication number | Publication date |
---|---|
FR2932233B1 (fr) | 2012-09-28 |
RU2511960C2 (ru) | 2014-04-10 |
CN102016265A (zh) | 2011-04-13 |
US20110085897A1 (en) | 2011-04-14 |
FR2932233A1 (fr) | 2009-12-11 |
WO2009147307A1 (fr) | 2009-12-10 |
RU2010152292A (ru) | 2012-07-20 |
BRPI0912082A2 (pt) | 2015-10-06 |
CN102016265B (zh) | 2014-06-18 |
CA2726024A1 (fr) | 2009-12-10 |
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Legal Events
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DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
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RIC1 | Information provided on ipc code assigned before grant |
Ipc: F01D 21/04 20060101ALI20151111BHEP Ipc: F01D 25/28 20060101AFI20151111BHEP Ipc: F02C 7/04 20060101ALI20151111BHEP Ipc: F01D 25/24 20060101ALI20151111BHEP |
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INTG | Intention to grant announced |
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STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
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18D | Application deemed to be withdrawn |
Effective date: 20160413 |