摘要:
A method for designing a composite airfoil (10), comprises designing a mold (32) having an inner surface (32i) that defines a surface profile of the airfoil, defining a preliminary core surface of a woven core (30), wherein the preliminary core surface is offset from the inner surface of the mold (32i) by a specified percentage, filling the space between the mold (32) and the preliminary core surface with a plurality of plies (26) and assembling the woven core (30) and the plurality of plies (26) in the mold (32) and curing to form the composite airfoil (10).
摘要:
The invention relates to a foam core (11, 12) or honey comb core comprising insections (13, 17, 18) to form at least one profiled end, said at least one profiled end being profiled for a longitudinal form lock connection with a complementary profiled end of another foam core (11, 12). The invention relates as well to a method of manufacturing a rotor blade with such foam cores (11, 12) or honey comb cores and to a rotor blade, particularly a rotor blade of a helicopter, assembled of such foam cores (11, 12) or honey comb cores.
摘要:
A component made of at least one thermoformable material, having a first layer (12) made of a first material, a second layer (14) made of a second material, and a third layer (16) made of the first material. The three layers form a sheet, which is formed to various shapes, depending upon the part that is to be created. The sheet may be formed to produce a wind blade, the bumper of an automobile, a door panel for an automobile, a flotation device, such as a pontoon for a pontoon boat, or the like. The first (12) and third layers (16) are SMC, and the second layer (14), or "core," is disposed between the first and third layers, allowing the strength of the first and third layers to be used more efficiently, compared to a sheet having only the first and third layers, and no core.
摘要:
A method of manufacturing a wind turbine blade shell part comprising fibre material impregnated with cured resin is described. The method comprises the steps of : a) providing a first mould part (110) having a first forming surface (112) with a contour that defines at least a part of an outer surface of turbine blade shell part, b) arranging fibre material in the first mould part, the fibre material comprising fibres of a magnetisable material, c) providing a resin in the first mould part simultaneous with and/or subsequent to step b), and d) curing the resin in order to form the wind turbine blade shell part or wind turbine blade (150). The fibre material is retained against the first forming surface by use of magnet means (114, 116, 118) during step b) and/or step c). A mould part comprising magnet means (114, 116, 118) and a wind turbine blade are also described.
摘要:
According to the method to produce a wind-turbine-blade (BL) a bottom layer (BA) is laid down into a forming tool. The bottom layer (BA) is used as a basis of a pile (PI). A predefined number of additional layers is stacked vertically on top of the basis to form the pile (PI), while the pile (PI) is used as a separate module for the production of the blade. The bottom layer (BA) is made of a nearly airtight material, to prevent that surrounding air is allowed to flow vertically through the pile (PI). An extraction of air is applied by a machine to a topmost layer of the pile in a way that the pile is sucked towards the machine. This allows to lift up the pile and to bring it into a mould for the further production of the blade.
摘要:
A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs.
摘要:
A method of manufacturing a composite structure comprising fibre material impregnated with cured resin is described. The method comprises the steps of: a) providing a first mould part (110) having a first forming surface (112) with a contour that defines at least a part of an outer surface of the composite structure (150), b) arranging fibre material (152,156) in the first mould part, the fibre material comprising fibres of a magnetisable material, c} providing a resin in the first mould part simultaneous with and/or subsequent to step b), and d) curing the resin in order to form the composite structure, the fibre material is retained against the first forming surface by use of magnet means (118) during step b) and/or step c).
摘要:
A method for manufacturing of a fibre reinforced laminate (13, 15) is provided. The method comprises the steps of: a) building up a part (15) of the laminate (13, 15) to a determined thickness using at least one layer of fibre material, b) placing a laterally extended layer (13) on top of the partially completed laminate (15), the layer (13) having in a first lateral direction (21) a greater stiffness than in a second lateral direction (22) and having in the first lateral direction (21) a greater stiffness than the other layers constituting the laminate, c) building up a new part of the laminate (15) to a determined thickness, and d) in case the thickness of the laminate built up pursuant to the steps a)-c) is not as large as a desired thickness of the completed laminate, repeating steps b) and c) until the thickness of the laminate built up is equal to the desired thickness of the completed laminate.