WO2012147802A1 - 成形部品 - Google Patents

成形部品 Download PDF

Info

Publication number
WO2012147802A1
WO2012147802A1 PCT/JP2012/061105 JP2012061105W WO2012147802A1 WO 2012147802 A1 WO2012147802 A1 WO 2012147802A1 JP 2012061105 W JP2012061105 W JP 2012061105W WO 2012147802 A1 WO2012147802 A1 WO 2012147802A1
Authority
WO
WIPO (PCT)
Prior art keywords
additional pad
flange
component
machining
main body
Prior art date
Application number
PCT/JP2012/061105
Other languages
English (en)
French (fr)
Inventor
敬 原田
重成　有
宏一 稲垣
崇 田中
忠寛 石榑
Original Assignee
株式会社Ihi
株式会社Ｉｈｉエアロスペース
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 株式会社Ihi, 株式会社Ｉｈｉエアロスペース filed Critical 株式会社Ihi
Priority to CA2832743A priority Critical patent/CA2832743C/en
Priority to CN201280019932.XA priority patent/CN103492158B/zh
Priority to EP12777801.7A priority patent/EP2703148B1/en
Priority to JP2013512408A priority patent/JP5662566B2/ja
Publication of WO2012147802A1 publication Critical patent/WO2012147802A1/ja
Priority to US14/057,734 priority patent/US9739175B2/en

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
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
    • B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
    • B29C66/1312—Single flange to flange joints, the parts to be joined being rigid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/54—Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles
    • B29C66/543—Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles joining more than two hollow-preforms to form said hollow articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7392—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic
    • B29C66/73921—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoplastic characterised by the materials of both parts being thermoplastics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7394—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset
    • B29C66/73941—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset characterised by the materials of both parts being thermosets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/748—Machines or parts thereof not otherwise provided for
    • B29L2031/7504—Turbines
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
    • 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 molded part that can be fastened in a state of being abutted against a counterpart part by using a fastener, such as a fan case used for an aircraft engine.
  • the fan case covers a plurality of fan blades in an aircraft engine, and is usually made of a metal such as a titanium alloy.
  • the fan case can be fastened in a state where it is abutted against a mating part using a fastener made of fastening bolts and nuts.
  • the fan case has a cylindrical case body as a component body, and the case body extends in the case axial direction. Also, at least one end side of the case main body is integrally formed with a bent portion 115 that can be abutted against a mating part via a curved portion 115, and an insertion hole into which a fastener (fastening bolt) can be inserted. 112 is formed.
  • a fastening seat surface 111 that is perpendicular to the outer peripheral surface of the case body and is flat is formed by machining on the outer surface opposite to the flange butting side, and the fastening seat surface 111 is a part of the fastener. The portion (the head of the fastening bolt or the bottom of the nut) can be supported.
  • the center of the insertion hole 112 of the flange 110 in other words, the center of the fastening seating surface 111 is located on the case body. Accordingly, the area end (area end) 114 of the machined machining area 113 is positioned on the curved surface on the small diameter side of the bending portion 115.
  • the technology related to the present invention is, for example, US Patent Publication No. 2008-0118683.
  • thermosetting resin or a composite material (FRP) of a thermoplastic resin and a reinforced fiber is attracting attention as a lightweight and high-strength material, and an attempt to apply FRP as a constituent material of a fan case has been made. Has been made.
  • the fastening surface of the flange 110 is required to have a predetermined surface state defined by perpendicularity, flatness, surface roughness, etc. with respect to the engine shaft in order to fasten the bolt.
  • the flange material is a forged metal or a molded composite material, it is difficult to realize such a surface state, and further machining is necessary.
  • the fan case is finished to the final shape by machining to secure the assembly accuracy with the mating parts.
  • the ultrasonic transducer (ultrasonic wave) is used after finishing the final shape. It is necessary to perform an ultrasonic flaw inspection using a probe 130 and confirm that there are no internal defects such as delamination due to machining.
  • the area end 114 of the processing area 113 when the area end 114 of the processing area 113 is positioned on the curved surface on the small diameter side of the curved portion 115, the area end 114 of the processing area 113 is a smooth surface (in this case). Is likely to be a machining step (machining mismatch) with respect to the curved surface on the small diameter side of the curved portion 115, and the reflected wave of the ultrasonic wave USW transmitted from the ultrasonic transducer 130 toward the curved portion 115 is scattered to the fan case. There is a problem that it is difficult to ensure the inspection accuracy of ultrasonic flaw detection to a high level.
  • a molded part (laminated part) that can be fastened in a state in which a thermosetting resin or a composite material of a thermoplastic resin and a reinforcing fiber is used as a constituent material and is abutted against a counterpart part using a fastener.
  • a machining process is performed in which a fastening seating surface that can support a part of the fastener on the outer surface side of the additional pad and is perpendicular to the outer surface of the component body is formed by machining.
  • An area end (area end) of the area is located on the component main body side beyond the curved portion.
  • the “molded part” is not limited to a fan case used for an aircraft engine, but includes various molded parts made of a composite material of a thermosetting resin or a thermoplastic resin and a reinforcing fiber.
  • FIG. 1A is an enlarged view of an arrow IA in FIG.
  • FIG. 1B is an enlarged view of the arrow IB in FIG.
  • FIG. 2 is an enlarged view of the arrow II in FIG.
  • FIG. 3 is a schematic cross-sectional view of an aircraft engine.
  • FIG. 4 is a cross-sectional view illustrating a problem to be solved by the invention.
  • FIG. 1A indicates the forward direction
  • FR indicates the backward direction
  • a cylindrical fan case 1 As shown in FIGS. 2 and 3, a cylindrical fan case 1 according to an embodiment of the present invention is used for an aircraft engine 3 and covers a plurality of fan blades 5 in the aircraft engine 3, and is thermoset.
  • a composite material (FRP) of a functional resin or a thermoplastic resin and a reinforcing fiber is used as a constituent material.
  • the fan case 1 is abutted against an engine cowl 9 (an example of a counterpart part) and a rear case 11 (an example of a counterpart part) in the aircraft engine 3 using a plurality of fasteners 7 including fastening bolts B and nuts N. Can be fastened in a state.
  • the fan case 1 includes a cylindrical case body 13 as a component body, and the case body 13 extends in the case axial direction (front-rear direction).
  • An annular front flange 17 that can be abutted against the mating flange 15 of the engine cowl 9 is integrally formed on the front end side (one end side) of the case body 13 via a curved front curved portion 19. 17, a plurality of (only one shown) front insertion holes 17h into which the fastening bolts B can be inserted are formed at intervals in the circumferential direction.
  • annular rear flange 23 that can be abutted against the mating flange 21 of the rear case 11 is integrally formed on the rear end side (the other end side) of the case body 13 via a curved rear curved portion 25.
  • the rear flange 23 is formed with a plurality of rear insertion holes 23h (only one shown) through which the fastening bolts B can be inserted at intervals in the circumferential direction.
  • the case main body 13, the front flange 17, the front curved portion 19, the rear flange 23, and the rear curved portion 25 are made of a thermosetting resin such as an epoxy resin, a phenol resin, or a polyimide resin, and a carbon fiber (an example of a reinforcing fiber). ), And specifically, is formed by a common carbon fiber woven fabric (not shown) and roving (not shown) impregnated with a thermosetting resin.
  • the case body 13 and the like are composed of a composite material of a thermoplastic resin such as polyether ether ketone and polyphenylene sulfide and a carbon fiber instead of the composite material of a thermosetting resin and carbon fiber. It does not matter.
  • an annular first front additional pad extends from the outer surface on the opposite side of the abutting side of the front flange 17 to the front end side of the case body 13 via the curved surface on the small diameter side of the front curved portion 19.
  • 27 is additionally provided integrally.
  • a first front slope 27 s that gradually decreases in the distal direction is formed at the end (end surface) of the first front additional pad 27 on the case body 13 side.
  • first front additional pad 27 is formed with a plurality of (only one shown) first front through holes 27h through which the fastening bolts B can be inserted at intervals in the circumferential direction.
  • the holes 27h are aligned with the corresponding front insertion holes 17h.
  • An annular and flat front fastening seat surface 27f is formed by machining on the outer surface side of the first front additional pad 27, and the front fastening seat surface 27f can support the head of the fastening bolt B. And perpendicular to the outer surface of the case body 13.
  • the machining area PA machined on the outer surface side of the first front additional pad 27 extends from the end surface on the front flange 17 side of the first front additional pad 27 to the end surface on the case body 13 side.
  • the area end (area end) PAe is located on the case body 13 side beyond the front curved portion 19.
  • An annular (disc-shaped) second front additional pad 29 is additionally provided integrally on the outer surface of the front flange 17 on the abutting side.
  • a second front slope 29 s that gradually decreases in the distal direction is formed at the end (end surface) of the second front additional pad 29 on the case body 13 side.
  • the second front additional pad 29 is formed with a plurality of second front through holes 29h through which the fastening bolts B can be inserted at intervals in the circumferential direction, and each second front through hole 29h corresponds to the second front through hole 29h. It is aligned with the front insertion hole 17h.
  • an annular and flat front abutting surface 29f is formed on the outer surface side of the second front additional pad 29 by machining, and the front abutting surface 29f can be abutted against the mating flange 15 of the engine cowl 9. It is perpendicular to the outer surface of the case body 13.
  • the machining area PA machined on the outer surface side of the second front additional pad 29 extends from the end surface on the front flange 17 side of the second front additional pad 29 to the end surface on the case body 13 side.
  • the area end PAe is located on the front side of the front bending portion 19.
  • the annular flange extends from the outer surface on the opposite side of the abutting side of the rear flange 23 to the rear end side of the case body 13 via the curved surface on the small diameter side of the rear curved portion 25.
  • One rear additional pad 31 is additionally provided integrally.
  • a first rear slope 31 s is formed at the end (end surface) on the case body 13 side of the first rear additional pad 31 that gradually decreases in the distal direction.
  • the first rear additional pad 31 is formed with a plurality of first rear through holes 31h through which the fastening bolts B can be inserted at intervals in the circumferential direction, and each first rear through hole 31h corresponds. It is aligned with the rear insertion hole 23h.
  • An annular and flat rear fastening seat surface 31f is formed by machining on the outer surface side of the first rear additional pad 31, and the rear fastening seat surface 31f can support the bottom surface of the nut N. And it is perpendicular to the outer surface of the case body 13.
  • the machining area PA machined on the outer surface side of the first rear additional pad 31 extends from the end surface on the rear flange 23 side of the first rear additional pad 31 to the end surface on the case body 13 side.
  • the area end PAe is located on the case body 13 side beyond the rear curved portion 25.
  • An annular (disc-shaped) second rear additional pad 33 is additionally provided integrally on the outer surface of the rear flange 23 on the abutting side.
  • a second rear slope 33 s is formed at the end (end surface) of the second rear additional pad 33 on the case body 13 side, which gradually becomes thinner in the distal direction.
  • a plurality of second rear through holes 33h into which the fastening bolts B can be inserted are formed in the second rear additional pad 33 at intervals in the circumferential direction, and each second rear through hole 33h corresponds. It is aligned with the rear insertion hole 23h.
  • annular and flat rear abutting surface 33f is formed at intervals in the circumferential direction by machining, and the rear abutting surface 33f is a counterpart of the rear case 11. It can abut against the flange 21 and is perpendicular to the outer surface of the case body 13.
  • the machining area PA machined on the outer surface side of the second rear additional pad 33 extends from the end surface on the rear flange 23 side of the second rear additional pad 33 to the end surface on the case body 13 side, and is processed.
  • the area end PAe is located on the front side of the rear curved portion 25.
  • the first front additional pad 27, the second front additional pad 29, the first rear additional pad 31, and the second rear additional pad 33 are made of a thermosetting resin such as epoxy resin, phenol resin, or polyimide resin, and glass. It is composed of a composite material with fibers (an example of reinforcing fibers), and specifically, is formed by a woven fabric (not shown) made of glass fibers impregnated with a thermosetting resin. That is, GFRP (glass fiber composite material) is easier to process and inspect after processing than CFRP (carbon fiber composite material), and there is no electrical contact with the bolt due to electrical conduction.
  • CFRP carbon fiber composite material
  • the first front additional pad 27 and the like are composed of a composite material of a thermoplastic resin such as polyether ether ketone and polyphenylene sulfide and glass fiber instead of the composite material of the thermosetting resin and glass fiber. It does not matter if it is
  • An annular first front additional pad 27 is additionally provided integrally from the outer surface on the opposite side of the front flange 17 to the front side of the outer surface of the case body 13, and a plurality of first front additional pads 27 are provided on the outer surface side of the first front additional pad 27.
  • a plurality of first front additional pads 27 are provided on the outer surface side of the first front additional pad 27.
  • an annular second front additional pad 29 is additionally provided on the outer surface on the abutting side of the front flange 17 so that the second front additional pad 29 is integrally provided.
  • a plurality of flat front abutting surfaces 29f are formed by machining on the outer surface side. Therefore, it is possible to finish the fan case 1 by minimizing or minimizing machining on the case main body 13, the front flange 17, and the front curved portion 19.
  • annular first rear additional pad 31 is additionally provided integrally from the outer surface on the opposite side of the abutting side of the rear flange 23 to the rear end side of the outer surface of the case body 13.
  • a plurality of flat rear fastening seating surfaces 31f are formed by machining on the outer surface side
  • an annular second rear additional pad 33 is additionally provided integrally on the outer surface of the rear flange 23 butting side.
  • a plurality of flat rear abutting surfaces 33f are formed on the outer surface side of the rear additional pad 33 by machining. Therefore, it is possible to finish the fan case 1 by minimizing or reducing machining on the rear flange 23 and the rear curved portion 25 as much as possible.
  • a flat front fastening seat surface 27f is formed by machining on the outer surface side of the first front additional pad 27, and the area end PAe of the machining area PA machined on the outer surface side of the first front additional pad 27 is front curved. Since it is located on the case body 13 side beyond the portion 19, the stress is not concentrated at a specific location, and when the fan case 1 is finished to the final shape by machining, the front side portion of the fan case 1 (the front curved portion 19). It is possible to minimize the occurrence of processing steps (processing mismatch) on the side).
  • the stress is further diffused, and the rate of occurrence of the machining step in the front side portion of the fan case 1 is substantially zero. Can be.
  • a flat rear fastening seat surface 31f is formed by machining on the outer surface side of the first rear additional pad 31, and the area end PAe of the machining area PA machined on the outer surface side of the first rear additional pad 31 is rear. Since it is located on the case body 13 side beyond the curved portion 25, it is possible to minimize the occurrence of a machining step on the rear portion (on the rear curved portion 25 side) of the fan case 1. In particular, since the first rear slope 31s is formed at the end of the first rear additional pad 31 on the case body 13 side, the occurrence rate of the machining step in the rear portion of the fan case 1 can be made substantially zero. .
  • the embodiment of the present invention it is possible to minimize the occurrence of processing steps in the front portion and the rear portion of the fan case 1, so that the front bending portion 19 and the ultrasonic transducer (see FIG. 4)
  • the disturbance of reflection of the ultrasonic wave transmitted toward the rear curved portion 25 or the like can be suppressed, and the inspection accuracy of the ultrasonic flaw detection inspection for the fan case 1 can be sufficiently ensured to a high level.
  • the fan case 1 can be finished with as little or as little machining as possible on the case body 13 and the like, the occurrence rate of defective products can be reduced and the productivity of the fan case 1 can be greatly improved. .
  • an additional pad is additionally provided integrally from the outer surface opposite to the flange butting side to one end of the outer surface of the component body, and a flat fastening seating surface is provided on the outer surface side of the additional pad. Since it is formed by machining, it is possible to finish the molded part by minimizing or minimizing machining on the component main body, the flange, and the curved portion.
  • a flat fastening seating surface is formed by machining on the outer surface side of the additional pad, and the area end of the machined machining area is positioned on the component body side beyond the curved portion.
  • the present invention is not limited to the description of the above-described embodiment.
  • the technical idea applied to the fan case 1 is applied to a molded part other than the fan case 1, and other appropriate changes are made. Therefore, the present invention can be implemented in various modes. Further, the scope of rights encompassed by the present invention is not limited to these embodiments.

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)
  • Connection Of Plates (AREA)
  • Moulding By Coating Moulds (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)

Abstract

　フランジ１７の突き合わせ側の反対側の外面から湾曲部１９の小径側の曲面を経由して部品本体１３の外面の一端側にかけて追加パッド２７が追加して一体的に設けられ、追加パッド２７の外面側に締結座面２７ｆが機械加工によって形成され、機械加工された加工エリアＰＡのエリア端ＰＡｅが湾曲部１９を越えて部品本体１３側に位置していること。

Description

成形部品
　本発明は、例えば航空機エンジンに用いられるファンケース等、締結具を用いて相手部品に突き合わせた状態で締結可能な成形部品に関する。
　航空機エンジンに用いられるファンケースについて簡単に説明する。
　ファンケースは、航空機エンジンにおける複数のファンブレードを覆うものであって、通常、チタン合金等の金属を構成材料としている。また、ファンケースは、締結ボルト及びナットからなる締結具を用いて、相手部品に突き合わせた状態で締結可能である。
　ファンケースは、部品本体としての筒状のケース本体を具備しており、ケース本体は、ケース軸方向へ延びている。また、ケース本体の少なくとも一端側には、相手部品に突き合わせ可能なフランジ１１０が湾曲した湾曲部１１５を介して一体形成されており、フランジには、締結具（締結ボルト）を挿通可能な挿通穴１１２が形成されている。そして、フランジの突き合わせ側の反対側の外面には、ケース本体の外周面に対して垂直でかつ平坦な締結座面１１１が機械加工によって形成されており、締結座面１１１は、締結具の一部（締結ボルトの頭部又はナットの底面）を支持可能である。ここで、ファンケースと相手部品との締結強度を十分に確保するために、図４に示すように、フランジ１１０の挿通穴１１２の中心、換言すれば、締結座面１１１の中心をケース本体の外周面から大きく離隔しないようにしており、それに伴い、機械加工された加工エリア１１３のエリア端（エリア終端）１１４が湾曲部１１５の小径側の曲面に位置づけられる。
　本発明に関連する技術はたとえば米国公開特許第２００８－０１１８６８３号である。
　航空機エンジンの分野において、熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料（ＦＲＰ）が軽量で高強度を有する素材として注目されており、ＦＲＰをファンケースの構成材料として適用する試みがなされている。
　フランジ１１０の締結面はボルト締結するために、エンジン軸に対する垂直度、平面度、表面粗さ等によって規定される所定の表面状態が要求される。しかし、フランジ素材が鍛造金属や成形された複合材料のままではかかる表面状態を実現することが困難であるためさらに機械加工する必要がある。
　ところが、複合材料の場合には機械加工により繊維を切ってしまうという問題がある。すなわち、複合材料は繊維構造により剛性および強度を確保しているため、繊維が一部でも切れると強度等が大きく低下するという問題がある。
　また、ファンケースは相手部品と組立精度確保のため締結部を機械加工で最終形状に仕上げており、ＦＲＰを構成材料とするファンケースについては、最終形状に仕上げた後に、超音波トランスデューサ（超音波プローブ）１３０を用いて超音波探傷検査を行い、機械加工に起因する層間剥離等の内部欠陥がないことを確認する必要がある。
　すなわち、層が湾曲するフランジ部では特に応力が集中しやすく層間剥離検査において特に重要な検査箇所である。超音波検査は対象物に対して音波を入射し、通過または反射した音波を計測するが、この際に対象物表面に段差や不連続があると音波が散乱して正確な測定が困難になる。
　より具体的には、図４に示すように、加工エリア１１３のエリア端１１４が湾曲部１１５の小径側の曲面に位置していると、加工エリア１１３のエリア端１１４が滑らかな面（この場合は、湾曲部１１５の小径側の曲面）に対する加工段差（加工ミスマッチ）になり易く、超音波トランスデューサ１３０から湾曲部１１５に向かって発信された超音波ＵＳＷの反射波が散乱されて、ファンケースに対する超音波探傷検査の検査精度を高いレベルまで確保することが困難になるという問題がある。
　なお、前述の問題は、ＦＲＰを構成材料とするファンケースだけでなく、ＦＲＰを構成材料とする種々の成形部品においても発生するものである。
　本発明によれば、複合材料の繊維強度を低下させず、高精度の超音波検査を可能とする成形部品を提供することができる。
　本発明の技術的側面によれば、熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料を構成材料とし、締結具を用いて相手部品に突き合わせた状態で締結可能な成形部品（積層部品）において、部品本体と、前記部品本体の少なくとも一端側に湾曲した湾曲部を介して一体形成され、前記締結具を挿通可能な挿通穴が形成され、前記相手部品に突き合わせ可能なフランジと、前記フランジの突き合わせ側の反対側（締結座面側）の外面から前記湾曲部の小径側の曲面を経由して前記部品本体の外面の一端側にかけて追加して一体的に設けられ、前記フランジの前記挿通穴に整合しかつ前記締結具を挿通可能な通孔が形成された追加パッドと、を具備する。さらに、前記追加パッドの外面側に前記締結具の一部を支持可能であってかつ前記部品本体の外面に対して垂直でかつ平坦な締結座面が機械加工によって形成され、機械加工された加工エリアのエリア端（エリア終端）が前記湾曲部を越えて前記部品本体側に位置していることを特徴とする。
　なお、「成形部品」とは、航空機エンジンに用いられるファンケースに限られず、熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料を構成材料とした種々の成形部品を含む意である。
図１Ａは、図２における矢視部IAの拡大図である。 図１Ｂは、図２における矢視部IBの拡大図である。 図２は、図３における矢視部IIの拡大図である。 図３は、航空機エンジンの模式断面図である。 図４は、発明が解決しようとする課題を説明する断面図である。
　本発明の実施形態について図１Ａ、図１Ｂ、図２、及び図３を参照して説明する。なお、図面中、「ＦＦ」は、前方向、「ＦＲ」は、後方向をそれぞれ指してある。
　図２及び図３に示すように、本発明の実施形態に係る筒状のファンケース１は、航空機エンジン３に用いられ、航空機エンジン３における複数のファンブレード５を覆うものであって、熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料（ＦＲＰ）を構成材料としている。
　また、ファンケース１は、締結ボルトＢとナットＮからなる複数の締結具７を用いて、航空機エンジン３におけるエンジンカウル９（相手部品の一例）及びリアケース１１（相手部品の一例）に突き合わせた状態で締結可能になっている。
　ファンケース１は、部品本体としての筒状のケース本体１３を具備しており、このケース本体１３は、ケース軸方向（前後方向）へ延びている。また、ケース本体１３の前端側（一端側）には、エンジンカウル９の相手フランジ１５に突き合わせ可能な環状のフロントフランジ１７が湾曲したフロント湾曲部１９を介して一体形成されており、このフロントフランジ１７には、締結ボルトＢを挿通可能な複数（１つのみ図示）のフロント挿通穴１７ｈが周方向に間隔を置いて形成されている。
　更に、ケース本体１３の後端側（他端側）には、リアケース１１の相手フランジ２１に突き合わせ可能な環状のリアフランジ２３が湾曲したリア湾曲部２５を介して一体形成されており、このリアフランジ２３には、締結ボルトＢを挿通可能な複数（１つのみ図示）のリア挿通穴２３ｈが周方向に間隔を置いて形成されている。
　ここで、ケース本体１３、フロントフランジ１７、フロント湾曲部１９、リアフランジ２３、及びリア湾曲部２５は、エポキシ樹脂，フェノール樹脂，又はポリイミド樹脂等の熱硬化性樹脂と炭素繊維（強化繊維の一例）との複合材料により構成され、具体的には、熱硬化性樹脂を含浸させた共通の炭素繊維の織物（図示省略）及びロービング（図示省略）によって成形されている。なお、ケース本体１３等が熱硬化性樹脂と炭素繊維との複合材料により構成される代わりに、ポリエーテルエーテルケトン，ポリフェニレンスルファイド等の熱可塑性樹脂と炭素繊維との複合材料により構成されるものであっても構わない。
　図１Ａ及び図２に示すように、フロントフランジ１７の突き合わせ側の反対側の外面からフロント湾曲部１９の小径側の曲面を経由してケース本体１３の前端側にかけて、環状の第１フロント追加パッド２７が追加して一体的に設けられている。また、第１フロント追加パッド２７におけるケース本体１３側の端部（端面）には、先端方向に向かって徐々に薄くなる第１フロントスロープ２７ｓが形成されている。
　更に、第１フロント追加パッド２７には、締結ボルトＢを挿通可能な複数（１つのみ図示）の第１フロント通孔２７ｈが周方向へ間隔を置いて形成されており、各第１フロント通孔２７ｈは、対応するフロント挿通穴１７ｈに整合している。そして、第１フロント追加パッド２７の外面側には、環状でかつ平坦なフロント締結座面２７ｆが機械加工によって形成されており、フロント締結座面２７ｆは、締結ボルトＢの頭部を支持可能であってかつケース本体１３の外面に対して垂直である。
　そして、第１フロント追加パッド２７の外面側に機械加工された加工エリアＰＡは、第１フロント追加パッド２７におけるフロントフランジ１７側の端面からケース本体１３側の端面まで延びてあって、加工エリアＰＡのエリア端（エリア終端）ＰＡｅは、フロント湾曲部１９を越えてケース本体１３側に位置している。
　フロントフランジ１７の突き合わせ側の外面には、環状（円盤状）の第２フロント追加パッド２９が追加して一体的に設けられている。また、第２フロント追加パッド２９におけるケース本体１３側の端部（端面）には、先端方向に向かって徐々に薄くなる第２フロントスロープ２９ｓが形成されている。
　更に、第２フロント追加パッド２９には、締結ボルトＢを挿通可能な複数の第２フロント通孔２９ｈが周方向へ間隔を置いて形成されており、各第２フロント通孔２９ｈは、対応するフロント挿通穴１７ｈに整合している。更に、第２フロント追加パッド２９の外面側には、環状でかつ平坦なフロント突き合わせ面２９ｆが機械加工によって形成されており、フロント突き合わせ面２９ｆは、エンジンカウル９の相手フランジ１５に突き合わせ可能であってかつケース本体１３の外面に対して垂直である。
　なお、第２フロント追加パッド２９の外面側に機械加工された加工エリアＰＡは、第２フロント追加パッド２９におけるフロントフランジ１７側の端面からケース本体１３側の端面まで延びてあって、加工エリアＰＡのエリア端ＰＡｅは、フロント湾曲部１９の手前側に位置している。
　同様に、図１Ｂ及び図２に示すように、リアフランジ２３の突き合わせ側の反対側の外面からリア湾曲部２５の小径側の曲面を経由してケース本体１３の後端側にかけて、環状の第１リア追加パッド３１が追加して一体的に設けられている。また、第１リア追加パッド３１におけるケース本体１３側の端部（端面）には、先端方向に向かって徐々に薄くなる第１リアスロープ３１ｓが形成されている。更に、第１リア追加パッド３１には、締結ボルトＢを挿通可能な複数の第１リア通孔３１ｈが周方向へ間隔を置いて形成されており、各第１リア通孔３１ｈは、対応するリア挿通穴２３ｈに整合している。
　そして、第１リア追加パッド３１の外面側には、環状でかつ平坦なリア締結座面３１ｆが機械加工によって形成されており、リア締結座面３１ｆは、ナットＮの底面を支持可能であってかつケース本体１３の外面に対して垂直である。そして、第１リア追加パッド３１の外面側に機械加工された加工エリアＰＡは、第１リア追加パッド３１におけるリアフランジ２３側の端面からケース本体１３側の端面まで延びてあって、加工エリアＰＡのエリア端ＰＡｅは、リア湾曲部２５を越えてケース本体１３側に位置している。
　リアフランジ２３の突き合わせ側の外面には、環状（円盤状）の第２リア追加パッド３３が追加して一体的に設けられている。また、第２リア追加パッド３３におけるケース本体１３側の端部（端面）には、先端方向に向かって徐々に薄くなる第２リアスロープ３３ｓが形成されている。更に、第２リア追加パッド３３には、締結ボルトＢを挿通可能な複数の第２リア通孔３３ｈが周方向へ間隔を置いて形成されており、各第２リア通孔３３ｈは、対応するリア挿通穴２３ｈに整合している。更に、第２リア追加パッド３３の外面側には、環状でかつ平坦なリア突き合わせ面３３ｆが機械加工によって周方向に間隔を置いて形成されており、リア突き合わせ面３３ｆは、リアケース１１の相手フランジ２１に突き合わせ可能であってかつケース本体１３の外面に対して垂直である。
　なお、第２リア追加パッド３３の外面側に機械加工された加工エリアＰＡは、第２リア追加パッド３３におけるリアフランジ２３側の端面からケース本体１３側の端面まで延びてあって、加工エリアＰＡのエリア端ＰＡｅは、リア湾曲部２５の手前側に位置している。
　ここで、第１フロント追加パッド２７、第２フロント追加パッド２９、第１リア追加パッド３１、及び第２リア追加パッド３３は、エポキシ樹脂，フェノール樹脂，又はポリイミド樹脂等の熱硬化性樹脂とガラス繊維（強化繊維の一例）との複合材料により構成され、具体的には、熱硬化性樹脂を含浸させかつガラス繊維からなる織物（図示省略）によって成形されている。すなわち、ＧＦＲＰ（ガラス繊維複合材料）は、ＣＦＲＰ（炭素繊維複合材料）に比べて加工および加工後の検査が容易であり、電気伝導によるボルトとの間の電触がない。
　なお、第１フロント追加パッド２７等が熱硬化性樹脂とガラス繊維との複合材料により構成される代わりに、ポリエーテルエーテルケトン，ポリフェニレンスルファイド等の熱可塑性樹脂とガラス繊維との複合材料により構成されるものであっても構わない。
　フロントフランジ１７の突き合わせ側の反対側の外面からケース本体１３の外面の前端側にかけて環状の第１フロント追加パッド２７が追加して一体的に設けられ、第１フロント追加パッド２７の外面側に複数の平坦なフロント締結座面２７ｆが機械加工によって形成されると共に、フロントフランジ１７の突き合わせ側の外面に環状の第２フロント追加パッド２９が追加して一体的に設けられ、第２フロント追加パッド２９の外面側に複数の平坦なフロント突き合わせ面２９ｆが機械加工によって形成されている。したがって、ケース本体１３、フロントフランジ１７、及びフロント湾曲部１９に対する機械加工を極力なくすか又は極力少なくして、ファンケース１を仕上げることができる。
　同様に、リアフランジ２３の突き合わせ側の反対側の外面からケース本体１３の外面の後端側にかけて環状の第１リア追加パッド３１が追加して一体的に設けられ、第１リア追加パッド３１の外面側に複数の平坦なリア締結座面３１ｆが機械加工によって形成されると共に、リアフランジ２３の突き合わせ側の外面に環状の第２リア追加パッド３３が追加して一体的に設けられ、第２リア追加パッド３３の外面側に複数の平坦なリア突き合わせ面３３ｆが機械加工によって形成されている。したがって、リアフランジ２３及びリア湾曲部２５に対する機械加工を極力なくすか又は極力少なくして、ファンケース１を仕上げることができる。
　また、第１フロント追加パッド２７の外面側に平坦なフロント締結座面２７ｆが機械加工によって形成され、第１フロント追加パッド２７の外面側に機械加工された加工エリアＰＡのエリア端ＰＡｅがフロント湾曲部１９を越えてケース本体１３側に位置しているため、応力が特定箇所に集中せず、機械加工によってファンケース１を最終形状に仕上げる際に、ファンケース１の前側部分（フロント湾曲部１９側）に加工段差（加工ミスマッチ）が発生することを極力なくすことができる。特に、第１フロント追加パッド２７におけるケース本体１３側の端部に第１フロントスロープ２７ｓが形成されているため、応力がさらに拡散されてファンケース１の前側部分における加工段差の発生率をほぼ０にすることができる。
　同様に、第１リア追加パッド３１の外面側に平坦なリア締結座面３１ｆが機械加工によって形成され、第１リア追加パッド３１の外面側に機械加工された加工エリアＰＡのエリア端ＰＡｅがリア湾曲部２５を越えてケース本体１３側に位置しているため、ファンケース１の後側部分（リア湾曲部２５側）に加工段差が発生することを極力なくすことができる。特に、第１リア追加パッド３１におけるケース本体１３側の端部に第１リアスロープ３１ｓが形成されているため、ファンケース１の後側部分における加工段差の発生率をほぼ０にすることができる。
　従って、本発明の実施形態によれば、ファンケース１の前側部分及び後側部分に加工段差が発生することを極力なくすことができるため、超音波トランスデューサ（図４参照）からフロント湾曲部１９及びリア湾曲部２５等に向かって発信された超音波の反射の乱れを抑えて、ファンケース１に対する超音波探傷検査の検査精度を高いレベルまで十分に確保することができる。
　ケース本体１３等に対する機械加工を極力なくすか又は極力少なくして、ファンケース１を仕上げることができるため、不良品の発生率を減らして、ファンケース１の生産性を大幅に向上させることができる。
　本発明の特徴によると、フランジの突き合わせ側の反対側の外面から部品本体の外面の一端側にかけて追加パッドが追加して一体的に設けられ、追加パッドの外面側に平坦な締結座面が機械加工によって形成されているため、部品本体、フランジ、及び湾曲部に対する機械加工を極力なくすか又は極力少なくして、成形部品を仕上げることができる。
　また、前記追加パッドの外面側に平坦な締結座面が機械加工によって形成され、機械加工された加工エリアのエリア端が湾曲部を越えて部品本体側に位置しているため、機械加工によって成形部品を最終形状に仕上げる際に、成形部品に加工段差（加工ミスマッチ）が発生することを極力なくすことができる。
　なお、本発明は、前述の実施形態の説明に限られるものではなく、例えば、ファンケース１に適用した技術的思想をファンケース１以外の成形部品に適用する等、その他、適宜の変更を行うことにより、種々の態様で実施可能である。また、本発明に包含される権利範囲は、これらの実施形態に限定されないものである。
　（米国指定）
　本国際特許出願は米国指定に関し、２０１１年４月２６日に出願された日本国特許出願第２０１１－０９８３３７号について米国特許法第１１９条（ａ）に基づく優先権の利益を援用し、当該開示内容を引用する。

Claims (5)

  1. 　熱硬化性樹脂又は熱可塑性樹脂と強化繊維との複合材料を構成材料とし、締結具を用いて相手部品に突き合わせた状態で締結可能な成形部品において、
    　部品本体と、
    　前記部品本体の少なくとも一端側に湾曲した湾曲部を介して一体形成され、前記締結具を挿通可能な挿通穴が形成され、前記相手部品に突き合わせ可能なフランジと、
    　前記フランジの突き合わせ側の反対側の外面から前記湾曲部の小径側の曲面を経由して前記部品本体の外面の一端側にかけて追加して一体的に設けられ、前記フランジの前記挿通穴に整合しかつ前記締結具を挿通可能な通孔が形成された追加パッドとを具備し、
    　前記追加パッドの外面側に前記締結具の一部を支持可能であってかつ前記部品本体の外面に対して垂直でかつ平坦な締結座面が機械加工によって形成され、機械加工された加工エリアのエリア端が前記湾曲部を越えて前記部品本体側に位置づけられることを特徴とする成形部品。
  2. 　前記追加パッドにおける前記部品本体側の端部に先端方向に向かって徐々に薄くなるスロープが形成されていることを特徴とする請求項１に記載の成形部品。
  3. 　前記追加パッドは、第１追加パッドであって、前記通孔は、第１通孔であって、
    　前記フランジの突き合わせ側の外面に追加して一体的に設けられ、前記フランジの前記挿通穴に整合しかつ前記締結具を挿通可能な第２通孔が形成された第２追加パッドと、を具備し、
    　前記第２追加パッドの外面側に前記相手部品に突き合わせ可能であってかつ前記部品本体の外面に対して垂直でかつ平坦な突き合わせ面が機械加工によって形成されていることを特徴とする請求項１又は請求項２に記載の成形部品。
  4. 　前記部品本体、前記フランジ、及び前記湾曲部は、熱硬化性樹脂又は熱可塑性樹脂と炭素繊維との複合材料により構成され、前記第１追加パッド及び前記第２追加パッドは、熱硬化性樹脂又は熱可塑性樹脂とガラス繊維との複合材料により構成されていることを特徴とする請求項３に記載の成形部品。
  5. 　航空機エンジンに用いられかつ前記航空機エンジンにおける複数のファンブレードを覆うものであって、
    　前記部品本体が筒状を呈してあって、前記フランジが環状を呈していることを特徴とする請求項１から請求項４のうちのいずれか１項に記載の成形部品。
PCT/JP2012/061105 2011-04-26 2012-04-25 成形部品 WO2012147802A1 (ja)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CA2832743A CA2832743C (en) 2011-04-26 2012-04-25 Molded part
CN201280019932.XA CN103492158B (zh) 2011-04-26 2012-04-25 成形部件
EP12777801.7A EP2703148B1 (en) 2011-04-26 2012-04-25 Moulded article
JP2013512408A JP5662566B2 (ja) 2011-04-26 2012-04-25 成形部品
US14/057,734 US9739175B2 (en) 2011-04-26 2013-10-18 Molded part

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2011-098337 2011-04-26
JP2011098337 2011-04-26

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/057,734 Continuation US9739175B2 (en) 2011-04-26 2013-10-18 Molded part

Publications (1)

Publication Number Publication Date
WO2012147802A1 true WO2012147802A1 (ja) 2012-11-01

Family

ID=47072319

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2012/061105 WO2012147802A1 (ja) 2011-04-26 2012-04-25 成形部品

Country Status (6)

Country Link
US (1) US9739175B2 (ja)
EP (1) EP2703148B1 (ja)
JP (1) JP5662566B2 (ja)
CN (1) CN103492158B (ja)
CA (1) CA2832743C (ja)
WO (1) WO2012147802A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150139794A1 (en) * 2012-06-05 2015-05-21 Snecma Counter plate and turbo machine comprising a counter plate

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9140135B2 (en) * 2010-09-28 2015-09-22 United Technologies Corporation Metallic radius block for composite flange
FR2975970B1 (fr) * 2011-05-30 2013-05-17 Aircelle Sa Ensemble pour une nacelle d'aeronef
GB201411657D0 (en) * 2014-07-01 2014-08-13 Rolls Royce Plc Casing
US20180045218A1 (en) * 2016-08-11 2018-02-15 United Technologies Corporation Shim for gas turbine engine
US10968775B2 (en) * 2017-11-28 2021-04-06 General Electric Company Support system having shape memory alloys
GB201819913D0 (en) * 2018-12-06 2019-01-23 Rolls Royce Plc A method of reducing burn-on time
US11773748B2 (en) 2019-07-30 2023-10-03 Siemens Energy Global GmbH & Co. KG High temperature flange joint, exhaust diffuser and method for coupling two components in a gas turbine engine
US20240110492A1 (en) * 2022-10-03 2024-04-04 Raytheon Technologies Corporation Flange and assembly for gas turbine engine case

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH079481A (ja) * 1993-06-22 1995-01-13 Nippon Zeon Co Ltd 密封接合構造
JPH08290480A (ja) * 1995-04-24 1996-11-05 Sekisui Chem Co Ltd 繊維強化樹脂製フランジ付き管状体
JP2000117844A (ja) * 1998-10-15 2000-04-25 Toray Ind Inc Ｆｒｐ構造体
US20080011868A1 (en) 2006-06-16 2008-01-17 Bowels Fluidics Corporation Fluidic device yielding three-dimensional spray patterns
JP2008068626A (ja) * 2006-09-13 2008-03-27 General Electric Co <Ge> 複合材角部及び複合材角部の製造方法
JP2008128249A (ja) * 2006-11-21 2008-06-05 General Electric Co <Ge> 取付けフランジを有する複合材構造体を作る方法

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4074914A (en) * 1975-07-28 1978-02-21 United Technologies Corporation High pressure lightweight flanges
FR2616409B1 (fr) 1987-06-09 1989-09-15 Aerospatiale Pale en materiaux composites et son procede de fabrication
US5063661A (en) * 1990-07-05 1991-11-12 The United States Of America As Represented By The Secretary Of The Air Force Method of fabricating a split compressor case
MX9204769A (es) * 1991-08-20 1993-02-01 Du Pont Material compuesto para empaquetaduras y proceso para su fabricacion.
GB9820226D0 (en) * 1998-09-18 1998-11-11 Rolls Royce Plc Gas turbine engine casing
US6352404B1 (en) * 2000-02-18 2002-03-05 General Electric Company Thermal control passages for horizontal split-line flanges of gas turbine engine casings
GB0216362D0 (en) * 2002-07-13 2002-08-21 Rolls Royce Plc Stress defender holes
FR2857409B1 (fr) * 2003-07-11 2006-07-28 Snecma Moteurs Dispositif pour piloter passivement la dilatation thermique du carter d'extension d'un turboreacteur
US8079773B2 (en) * 2005-10-18 2011-12-20 General Electric Company Methods and apparatus for assembling composite structures
GB0609166D0 (en) * 2006-05-09 2006-06-21 Airbus Uk Ltd Apparatus for and method of inhibiting delamination
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
US7713021B2 (en) * 2006-12-13 2010-05-11 General Electric Company Fan containment casings and methods of manufacture
JP2008223952A (ja) * 2007-03-14 2008-09-25 Uchiyama Mfg Corp ガスケット
FR2936223B1 (fr) * 2008-09-23 2010-09-17 Airbus France Dispositif de liaison entre une entree d'air et une motorisation d'une nacelle d'aeronef
US9140135B2 (en) * 2010-09-28 2015-09-22 United Technologies Corporation Metallic radius block for composite flange

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH079481A (ja) * 1993-06-22 1995-01-13 Nippon Zeon Co Ltd 密封接合構造
JPH08290480A (ja) * 1995-04-24 1996-11-05 Sekisui Chem Co Ltd 繊維強化樹脂製フランジ付き管状体
JP2000117844A (ja) * 1998-10-15 2000-04-25 Toray Ind Inc Ｆｒｐ構造体
US20080011868A1 (en) 2006-06-16 2008-01-17 Bowels Fluidics Corporation Fluidic device yielding three-dimensional spray patterns
JP2008068626A (ja) * 2006-09-13 2008-03-27 General Electric Co <Ge> 複合材角部及び複合材角部の製造方法
JP2008128249A (ja) * 2006-11-21 2008-06-05 General Electric Co <Ge> 取付けフランジを有する複合材構造体を作る方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP2703148A4

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150139794A1 (en) * 2012-06-05 2015-05-21 Snecma Counter plate and turbo machine comprising a counter plate
US9494051B2 (en) * 2012-06-05 2016-11-15 Snecma Counter plate and turbo machine comprising a counter plate

Also Published As

Publication number Publication date
EP2703148A4 (en) 2014-10-08
JP5662566B2 (ja) 2015-02-04
US9739175B2 (en) 2017-08-22
CN103492158B (zh) 2016-06-15
CA2832743C (en) 2017-04-04
EP2703148B1 (en) 2017-11-22
US20140044539A1 (en) 2014-02-13
CN103492158A (zh) 2014-01-01
JPWO2012147802A1 (ja) 2014-07-28
CA2832743A1 (en) 2012-11-01
EP2703148A1 (en) 2014-03-05

Similar Documents

Publication Publication Date Title
JP5662566B2 (ja) 成形部品
US7788993B2 (en) Tie rod assembly
EP2185345B1 (fr) Cadre de structure en materiau composite et fuselage d&#39;aeronef comportant un tel cadre
US10294973B2 (en) Struts and methods utilizing a locking collar nut
US7452156B2 (en) Composite structural member and method for making the same
US7780432B2 (en) Method and device for connecting a plastic workpiece to a further workpiece
JP2010530319A (ja) 複合フランジ、フランジを組み込むダクト及びフランジの製造方法
US8215885B2 (en) Lockable fastener assembly
EP2533938B1 (fr) Procédé de réparation d&#39;une bride d&#39;un carter
WO2010046684A1 (en) Joint between aircraft components
FR2929352A1 (fr) Procede d&#39;assemblage entre une piece en materiau metallique et une piece en materiau composite
US10215040B2 (en) Coupling part structure for vane and jet engine including the same
JP2018069903A (ja) 車両用ホイール
FR2862112A1 (fr) Procede de fabrication d&#39;un organe formant au moins une rotule et organe ainsi realise
US20130236701A1 (en) Joint structure for fiber reinforced resin and metal, and joining method for fiber reinforced resin and metal
US8455085B2 (en) Metal/composite joint with selective interlaminar reinforcement
JP5647888B2 (ja) 樹脂部材の締結構造
KR20190091808A (ko) 복합재 일체형 연료탱크의 수리 방법
US20180312249A1 (en) Rotor blade snubber retainer for a rotary wing aircraft
FR3011269A1 (fr) Aube de redresseur pour moteur a turbine a gaz a structure hybride
WO2019181607A1 (ja) 複合材組立体
JP4435656B2 (ja) 複合パネルのボルト取付構造
FR3039089A1 (fr) Procede de fabrication d&#39;une piece en materiau composite integrant des composants et des moyens de reperage
US20230286223A1 (en) Shimming welded interface(s) between thermoplastic components
FR2983264A1 (fr) Piece d&#39;assemblage

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 12777801

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2832743

Country of ref document: CA

Ref document number: 2013512408

Country of ref document: JP

Kind code of ref document: A

NENP Non-entry into the national phase

Ref country code: DE

REEP Request for entry into the european phase

Ref document number: 2012777801

Country of ref document: EP