WO2012032017A1 - Carter de turboreacteur et turboreacteur recevant de tels carters - Google Patents
Carter de turboreacteur et turboreacteur recevant de tels carters Download PDFInfo
- Publication number
- WO2012032017A1 WO2012032017A1 PCT/EP2011/065339 EP2011065339W WO2012032017A1 WO 2012032017 A1 WO2012032017 A1 WO 2012032017A1 EP 2011065339 W EP2011065339 W EP 2011065339W WO 2012032017 A1 WO2012032017 A1 WO 2012032017A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- housing
- blades
- blade
- turbojet
- casing
- Prior art date
Links
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
- 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
- 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
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- 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
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- 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
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
-
- 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 turbojet casing adapted to receive a plurality of blades and a turbojet incorporating such casings.
- Annular housings are known comprising attachment means intended to cooperate with the ends of a blade.
- the document US2009 / 0317246 recommends ends having a cylindrical platform forming a portion of the outer casing and carrying two fixing flanks, which leads to complex shapes to manufacture.
- the document US2009 / 0317246 recommends the joining of the blades together by means of a circular ring before mounting the assembly thus formed in the housing. This is a cumbersome solution to implement, requiring assembly tools.
- the object of the invention is therefore to provide a turbojet casing simple to produce and easy to assemble.
- a turbojet engine housing adapted to receive a plurality of blades, comprising means for hooking an end of each blade on the housing.
- the attachment means extend on one face of the housing opposite the blades, the casing has orifices for passing the ends of the blades so that they can cooperate with the attachment means of the housing.
- the means fastening means comprise an annular member extending around the casing, the casing comprising long fibers and thermoplastic resin, and the annular member being obtained by pultrusion and impregnated with a thermoplastic resin weldable with the thermoplastic resin of the housing, assembly being assembled by hot compaction. This gives the whole a strong cohesion.
- the invention also relates to a turbojet comprising at least one housing according to the invention and a plurality of blades each having an end connected to the housing.
- each blade comprises:
- At least one of the leading edge or the trailing edge has extensions which project from the web at least on one side of the blade, to carry hooking means cooperating with the means attachment of the turbojet casing.
- FIG. 1 is a top view of a blade to be fixed to a housing according to the invention
- FIG. 2 is a perspective view of the blade of Figure 1, the skin covering the soul of the blade being partially cut away;
- Figure 3 is a perspective view of a first mode of attachment of the blade to a housing according to the invention.
- FIG. 4 is a perspective view of a second mode of fixing the blade to the casing according to the invention.
- the blade 1 which is illustrated here is a stator blade, intended to extend behind the fan of a turbojet engine.
- the blade 1 comprises a leading edge 2 which is here in the form of an elongate monobloc structure.
- the blade 1 further comprises a trailing edge 3 which is also in the form of an elongate monobloc structure.
- the leading edge 2 and the trailing edge 3 are cut in profiles obtained by pultrusion, preferably with oblique fiber placement (so-called "pullbraiding” process).
- the profiles comprise fibers, for example carbon fibers, substantially disposed along a longitudinal axis to form an elongated body. Ideally, substantially 80% of the fibers are disposed along the longitudinal axis of the leading edge X and leakage Y and 20% of the fibers are disposed at an inclination of about 60 degrees to the longitudinal axis. These proportions and the arrangement of the fibers are given by way of example.
- the fibers are here impregnated with thermoplastic resin. Between the leading edge 2 and the trailing edge 3 extends a core 4.
- a skin 5 comprising here two webs 5A, 5B obtained by cutting in a fiber fabric cross ⁇ impregnated with thermoplastic resin, extend from and other of the core 4 to cover it as well as zones 6, 7 of the leading edge 2 and the trailing edge 3 contiguous to the core 4.
- the faces of the core 4 not covered by the webs 5A, 5B forming free ends of the core 4 are here protected and reinforced by means of a mixture 22 of short fibers and resin inserted in a cavity defined by the sails 5A, 5B and the free edge of the core 4.
- the leading edge 2 and the trailing edge 3 comprise extensions 10, 11, 12, 13 which protrude from the core 4 on each side of dawn 1.
- FIG. 3 represents a first mode of attachment of the blade 1 to an annular casing 20 of a turbojet engine.
- the housing 20 has orifices 26 for passage through the casing 20 of the extensions 10, 12 of the leading edge 2 and the trailing edge 3.
- the orifices 26 are illustrated as being sufficiently extended to allow the extensions of the leading and trailing edges by the same orifice. However, it will be possible alternatively to make the orifices in two parts, including an upstream orifice and a downstream orifice for passing respectively the leading edge and the trailing edge.
- the casing 20 is equipped with fastening means leading edges which comprise a peripheral rail 21 which extends around the casing, on a face thereof opposite the blade.
- the rail 21 defines a housing adapted to receive the heads 24 of fasteners 23 in the general shape of T or L.
- fasteners 23 in the general shape of T or L.
- the fastener 23 has an opposite end 25 opposite the head 24 which is cut to accommodate the extension of the leading edge.
- the fastening between the fastening element 23 and the extension 10 is here made by broaching.
- the end 25 comprises an orifice, not visible here, located opposite the orifice 14 of the extension 10 of the leading edge 2, to receive a fixing pin 27.
- Fixing the extension 12 of the trailing edge 3 is similarly performed by means of a second rail 21 ', in which a second fastening element 23' is engaged to cooperate with the extension 12 of the trailing edge 3, the any broach using a 27 'pin.
- the rails 21, 21 'and the fixing elements 23, 23' are made by pultrusion and are impregnated with thermoplastic resin thus allowing the assembly to be joined together by a single operation of hot compaction to the casing. 20.
- FIG. 3 represents, moreover, only one half of the blade 1.
- the end portions 11, 13 which are not visible are fixed to an internal casing in such a way that identical to what has just been described.
- the dawn may be fixed to only one of the housings.
- FIG. 4 illustrates a second mode of attachment of the blade 1 to a turbojet casing 20.
- the attachment means comprise a peripheral angle 30 extending around the housing.
- the angle 30 extends on an opposite face of the housing 20 relative to the blade 1.
- the housing 20 has through holes 26 allowing the extensions of the leading and trailing edges of the blade to pass through the housing 20 to extend facing the angle 30.
- the angle 30 is made by pultrusion and is impregnated with thermoplastic resin.
- the angle 30 has an L-shaped section, a first face 28 is here fixed to the housing 20 by hot compaction and a second face 29 is fixed to the extension 10 by broaching.
- the face 29 of the angle 30 is pierced with an orifice coming opposite the orifice 114 formed in the extension 10 of the leading edge. It will be noted moreover that the orifice 114 is pierced perpendicularly to the orifice 14 of the previous embodiment. It will also be noted that the extension 10 has been machined to present an upright face bearing against the face facing the wing 29.
- the different elements of the casing are joined together by thermocompaction.
- the materials used for the production of the various elements 2, 3, 4, 5 of the blade 1 and the attachment means 21, 23, 27 can be composite materials as well as metallic materials or a combination both.
- capping the free ends of the core 4 may be replaced or supplemented by a folding of the skin of one or more webs 5A, 5B.
- the size of the webs 5A, 5B will be adjusted to provide a flap from covering the free end of the core.
- attachment means of the housing and those of the leading edge and trailing edge can be secured to each other by hot compaction, welding, gluing or even using screw / nut torques or any other solution ensuring the maintenance of these elements between them.
- the blades may have a different structure from that described and for example a monobloc structure.
- FIGS. 3 and 4 suggest identical fixing means to each of the extensions 10, 11, 12, 13 of the leading edge 2 and the trailing edge 3 according to two different embodiments, it is not necessary to contrary to the invention that each extension is fixed to the casing 20 according to one or the other of the fixing means independently.
- attachment means comprise an annular member in the form of a rail or a peripheral angle extending around the housing
- attachment means could be envisaged, such as fixing lugs on which are fixed the ends of the blades after passing through the housing.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Non-Positive Displacement Air Blowers (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/820,545 US20130251519A1 (en) | 2010-09-06 | 2011-09-05 | Turbojet casing and turbojet receiving such casings |
EP11754367.8A EP2614258A1 (fr) | 2010-09-06 | 2011-09-05 | Carter de turboreacteur et turboreacteur recevant de tels carters |
RU2013115370/06A RU2544107C2 (ru) | 2010-09-06 | 2011-09-05 | Корпус турбореактивного двигателя и турбореактивный двигатель, содержащий такие корпуса |
BR112013004717A BR112013004717A2 (pt) | 2010-09-06 | 2011-09-05 | "cárter de turborreator e turborreator que recebe tais cárteres". |
CA2810181A CA2810181A1 (fr) | 2010-09-06 | 2011-09-05 | Carter de turboreacteur et turboreacteur recevant de tels carters |
CN2011800425646A CN103080562A (zh) | 2010-09-06 | 2011-09-05 | 涡轮喷气机壳体和接纳此种壳体的涡轮喷气机 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1057072A FR2964427B1 (fr) | 2010-09-06 | 2010-09-06 | Carter de turboreacteur et turboreacteur recevant de tels carters |
FR1057072 | 2010-09-06 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012032017A1 true WO2012032017A1 (fr) | 2012-03-15 |
Family
ID=43770444
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2011/065339 WO2012032017A1 (fr) | 2010-09-06 | 2011-09-05 | Carter de turboreacteur et turboreacteur recevant de tels carters |
Country Status (8)
Country | Link |
---|---|
US (1) | US20130251519A1 (fr) |
EP (1) | EP2614258A1 (fr) |
CN (1) | CN103080562A (fr) |
BR (1) | BR112013004717A2 (fr) |
CA (1) | CA2810181A1 (fr) |
FR (1) | FR2964427B1 (fr) |
RU (1) | RU2544107C2 (fr) |
WO (1) | WO2012032017A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3077328B1 (fr) * | 2018-01-30 | 2020-07-31 | Safran Aircraft Engines | Turboreacteur comportant une piece de liaison d'une ailette avec un organe elastique et procede de montage d'une ailette |
CN109372798A (zh) * | 2018-12-13 | 2019-02-22 | 中国航发沈阳发动机研究所 | 一种风扇叶片 |
US11572796B2 (en) | 2020-04-17 | 2023-02-07 | Raytheon Technologies Corporation | Multi-material vane for a gas turbine engine |
US11795831B2 (en) * | 2020-04-17 | 2023-10-24 | Rtx Corporation | Multi-material vane for a gas turbine engine |
US11879360B2 (en) * | 2020-10-30 | 2024-01-23 | General Electric Company | Fabricated CMC nozzle assemblies for gas turbine engines |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US764450A (en) * | 1903-12-19 | 1904-07-05 | Gen Electric | Turbine-bucket cover. |
GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
GB599391A (en) * | 1945-05-25 | 1948-03-11 | Power Jets Res & Dev Ltd | Improvements in and relating to axial flow compressors, turbines and the like machines |
GB732919A (en) * | 1953-07-15 | 1955-06-29 | Rolls Royce | Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines |
GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
US4710097A (en) * | 1986-05-27 | 1987-12-01 | Avco Corporation | Stator assembly for gas turbine engine |
EP1079075A2 (fr) * | 1999-08-09 | 2001-02-28 | United Technologies Corporation | Stator pour une turbomachine et agrafe pour le stator |
EP1213484A1 (fr) * | 2000-12-06 | 2002-06-12 | Techspace Aero S.A. | Etage redressseur d'un compresseur |
DE102007059220A1 (de) * | 2007-12-07 | 2009-06-10 | Rolls-Royce Deutschland Ltd & Co Kg | Leitschaufelkranz für thermische Strömungsmaschinen, insbesondere Flugtriebwerke |
EP2072760A1 (fr) * | 2007-12-21 | 2009-06-24 | Techspace aero | Dispositif de fixation d'aubes a une virole d'étage de stator d'une turbomachine et procède de fixation associe |
US20090317246A1 (en) | 2006-06-30 | 2009-12-24 | Fischer Advanced Composite Components Ag | Guide Vane Arrangement for a Driving Mechanism |
Family Cites Families (14)
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 |
FR2697285B1 (fr) * | 1992-10-28 | 1994-11-25 | Snecma | Système de verrouillage d'extrémités d'aubes. |
FR2699498B1 (fr) * | 1992-12-23 | 1995-03-10 | Eurocopter France | Pale en composite thermoplastique, notamment pour rotor arrière caréné d'hélicoptère, et son procédé de fabrication. |
US5494404A (en) * | 1993-12-22 | 1996-02-27 | Alliedsignal Inc. | Insertable stator vane assembly |
TWI233444B (en) * | 1998-10-30 | 2005-06-01 | Toray Industries | Thermoplastic resin composition, production thereof, and molded article thereof |
US6474941B2 (en) * | 2000-12-08 | 2002-11-05 | General Electric Company | Variable stator vane bushing |
RU38840U1 (ru) * | 2004-02-20 | 2004-07-10 | Открытое акционерное общество "Невский завод" | Обойма направляющих лопаток турбомашины |
CN102137888B (zh) * | 2008-08-29 | 2013-07-17 | 纳幕尔杜邦公司 | 用于飞机发动机的复合材料部件 |
US7891947B2 (en) * | 2008-12-12 | 2011-02-22 | General Electric Company | Turbine blade and method of fabricating the same |
-
2010
- 2010-09-06 FR FR1057072A patent/FR2964427B1/fr not_active Expired - Fee Related
-
2011
- 2011-09-05 CA CA2810181A patent/CA2810181A1/fr not_active Abandoned
- 2011-09-05 CN CN2011800425646A patent/CN103080562A/zh active Pending
- 2011-09-05 RU RU2013115370/06A patent/RU2544107C2/ru not_active IP Right Cessation
- 2011-09-05 EP EP11754367.8A patent/EP2614258A1/fr not_active Withdrawn
- 2011-09-05 BR BR112013004717A patent/BR112013004717A2/pt not_active IP Right Cessation
- 2011-09-05 US US13/820,545 patent/US20130251519A1/en not_active Abandoned
- 2011-09-05 WO PCT/EP2011/065339 patent/WO2012032017A1/fr active Application Filing
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US764450A (en) * | 1903-12-19 | 1904-07-05 | Gen Electric | Turbine-bucket cover. |
GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
GB599391A (en) * | 1945-05-25 | 1948-03-11 | Power Jets Res & Dev Ltd | Improvements in and relating to axial flow compressors, turbines and the like machines |
GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
US2772856A (en) * | 1950-08-01 | 1956-12-04 | Rolls Royce | Structural elements for turbo-machines such as compressors or turbines of gasturbineengines |
GB732919A (en) * | 1953-07-15 | 1955-06-29 | Rolls Royce | Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines |
US4710097A (en) * | 1986-05-27 | 1987-12-01 | Avco Corporation | Stator assembly for gas turbine engine |
EP1079075A2 (fr) * | 1999-08-09 | 2001-02-28 | United Technologies Corporation | Stator pour une turbomachine et agrafe pour le stator |
EP1213484A1 (fr) * | 2000-12-06 | 2002-06-12 | Techspace Aero S.A. | Etage redressseur d'un compresseur |
US20090317246A1 (en) | 2006-06-30 | 2009-12-24 | Fischer Advanced Composite Components Ag | Guide Vane Arrangement for a Driving Mechanism |
DE102007059220A1 (de) * | 2007-12-07 | 2009-06-10 | Rolls-Royce Deutschland Ltd & Co Kg | Leitschaufelkranz für thermische Strömungsmaschinen, insbesondere Flugtriebwerke |
EP2072760A1 (fr) * | 2007-12-21 | 2009-06-24 | Techspace aero | Dispositif de fixation d'aubes a une virole d'étage de stator d'une turbomachine et procède de fixation associe |
Also Published As
Publication number | Publication date |
---|---|
BR112013004717A2 (pt) | 2016-05-17 |
FR2964427A1 (fr) | 2012-03-09 |
RU2013115370A (ru) | 2014-10-20 |
RU2544107C2 (ru) | 2015-03-10 |
CN103080562A (zh) | 2013-05-01 |
US20130251519A1 (en) | 2013-09-26 |
EP2614258A1 (fr) | 2013-07-17 |
CA2810181A1 (fr) | 2012-03-15 |
FR2964427B1 (fr) | 2014-05-09 |
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Legal Events
Date | Code | Title | Description |
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