GB788517A - Improvements relating to blades of air-foil configuration and method of making same - Google Patents

Improvements relating to blades of air-foil configuration and method of making same

Info

Publication number
GB788517A
GB788517A GB11020/55A GB1102055A GB788517A GB 788517 A GB788517 A GB 788517A GB 11020/55 A GB11020/55 A GB 11020/55A GB 1102055 A GB1102055 A GB 1102055A GB 788517 A GB788517 A GB 788517A
Authority
GB
United Kingdom
Prior art keywords
blade
root
die
resin
moulding
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.)
Expired
Application number
GB11020/55A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB11020/55A priority Critical patent/GB788517A/en
Publication of GB788517A publication Critical patent/GB788517A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
    • 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
    • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
    • B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
    • B29C45/14336—Coating a portion of the article, e.g. the edge of the article
    • B29C45/14426—Coating the end of wire-like or rod-like or cable-like or blade-like or belt-like 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/081—Combinations of fibres of continuous or substantial length and short 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
    • B29C70/845—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined by moulding material on a relative small portion of the preformed parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

788,517. Moulding aircraft propeller blades &c. WARNKEN, E. P. April 16, 1955, No. 11020/55. Class 87(2). [Also in Groups XXVI and XXXIII] A blade of aerofoil cross-section, for example an aircraft propeller blade or an axial flow compressor blade, comprises a vane portion 14 formed of laminations of resin-impregnated glass fibres 15, the laminations extending longitudinally of the vane portion, and a root portion formed of short resin-impregnated glass fibres. The laminations 15 are moulded by heat and pressure to form the vane portion 14 which is formed with ribs 17 at its root end. An injection moulding machine for forming the blade root is shown in Figs. 8 and 9 and comprises upper and lower members 19<SP>1</SP>, 19 which are recessed to receive a die member 23 and a die-holding member 24, the latter having an aperture 26 in which a die member 27 is mounted. The die member 27 is formed with a slot 28 through which the vane portion 14 is passed, the ribbed end 17 being positioned within the cavity 29 between the dies. Short resinimpregnated fibres are injected under pressure through the nozzle 31 into the cavity 29. When the resin is properly cured, the moulded blade is removed. In a further embodiment a plurality of vanes 42 is united with a root member 43 and a shroud member 44. A machine for forming the moulded blade assembly is indicated in Fig. 10 and the moulding device 45<SP>1</SP> for forming the shroud member 44 is shown in detail in Fig. 12. The upper and lower members 46<SP>1</SP>, 46 are recessed to receive a die member 48 and a pair of interengaging die members 49, 51, the latter members having aligned slots through which the vanes 42 are passed, the ribbed vane ends being positioned within the moulding cavity 52. Resin-impregnated short glass fibres are injected through the nozzle 57 and the shroud member 44 is thus formed. The root member 43 is formed in the same manner in the moulding device 4511, Fig. 10.
GB11020/55A 1955-04-16 1955-04-16 Improvements relating to blades of air-foil configuration and method of making same Expired GB788517A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB11020/55A GB788517A (en) 1955-04-16 1955-04-16 Improvements relating to blades of air-foil configuration and method of making same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB11020/55A GB788517A (en) 1955-04-16 1955-04-16 Improvements relating to blades of air-foil configuration and method of making same

Publications (1)

Publication Number Publication Date
GB788517A true GB788517A (en) 1958-01-02

Family

ID=9978580

Family Applications (1)

Application Number Title Priority Date Filing Date
GB11020/55A Expired GB788517A (en) 1955-04-16 1955-04-16 Improvements relating to blades of air-foil configuration and method of making same

Country Status (1)

Country Link
GB (1) GB788517A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2567062A1 (en) * 1984-07-07 1986-01-10 Rolls Royce ANNULAR ELEMENT WITH BLADES HAVING AN INTEGRATING REINFORCING RING AND ITS MANUFACTURING DEVICE
FR2567209A1 (en) * 1984-07-07 1986-01-10 Rolls Royce COMPRESSOR ROTOR ASSEMBLY AND METHOD FOR MANUFACTURING SUCH AN ASSEMBLY
CH681793A5 (en) * 1990-05-04 1993-05-28 Sulzer Ag Heavy duty fibre reinforced thermoplastic component - includes load-bearing core contg. endless fibres
EP0776754A1 (en) * 1995-11-30 1997-06-04 INOPLAST, Société Anonyme: Process and apparatus for injection moulding and composite material produced thereby
FR3012515A1 (en) * 2013-10-31 2015-05-01 Safran AUBE COMPOSITE TURBOMACHINE
US20170254212A1 (en) * 2014-08-27 2017-09-07 Safran Aircraft Engines A guide vane made of composite material for a gas turbine engine, and it's method of fabrication
CN112743872A (en) * 2020-12-25 2021-05-04 中国航空制造技术研究院 RTM (resin transfer molding) mold and method for large-curvature special-shaped structure composite material part

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2567062A1 (en) * 1984-07-07 1986-01-10 Rolls Royce ANNULAR ELEMENT WITH BLADES HAVING AN INTEGRATING REINFORCING RING AND ITS MANUFACTURING DEVICE
FR2567209A1 (en) * 1984-07-07 1986-01-10 Rolls Royce COMPRESSOR ROTOR ASSEMBLY AND METHOD FOR MANUFACTURING SUCH AN ASSEMBLY
CH681793A5 (en) * 1990-05-04 1993-05-28 Sulzer Ag Heavy duty fibre reinforced thermoplastic component - includes load-bearing core contg. endless fibres
EP0776754A1 (en) * 1995-11-30 1997-06-04 INOPLAST, Société Anonyme: Process and apparatus for injection moulding and composite material produced thereby
FR3012515A1 (en) * 2013-10-31 2015-05-01 Safran AUBE COMPOSITE TURBOMACHINE
US20160153295A1 (en) * 2013-10-31 2016-06-02 Safran Composite vane for a turbine engine
US20170254212A1 (en) * 2014-08-27 2017-09-07 Safran Aircraft Engines A guide vane made of composite material for a gas turbine engine, and it's method of fabrication
CN112743872A (en) * 2020-12-25 2021-05-04 中国航空制造技术研究院 RTM (resin transfer molding) mold and method for large-curvature special-shaped structure composite material part

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