公开(公告)号：US20230264434A1

公开(公告)日：2023-08-24

申请号：US18017705

申请日：2021-07-27

Applicant: LEONARDO S.P.A.

Inventor： Stefano Giuseppe CORVAGLIA ,  Pasquale GAMBARDELLA

IPC: B29C70/30 ,  B29C70/54 ,  B29C70/88 ,  B64F5/10

CPC classification number: B29C70/302 ,  B29C70/545 ,  B29C70/887 ,  B64F5/10 ,  B29D99/0014

Abstract: A process for manufacturing a structural component made of composite material comprising a skin and at least one stiffening stringer applied rigidly and integrally to one face of the skin. The process comprises a) arranging, on a tool, a plurality of first layers of uncured or pre-cured composite material, forming the stringer and having a raised portion protruding from at least one flange; b) arranging, on the tool, a plurality of second layers of uncured or pre-cured composite material forming the skin; c) making a face of the skin and the flange of the stringer adhere to each other; d) applying a predetermined temperature and pressure on the assembly to compact the layers together, possibly curing the uncured material and rigidly joining the skin to the stringer; and e) performing a cutting operation on the free end side edge/s of the flange in a slanted direction.

公开(公告)号：US11820500B2

公开(公告)日：2023-11-21

申请号：US17498154

申请日：2021-10-11

Applicant: Bell Textron Inc.

Inventor： Tom S. Chiang ,  Bruce B. Bacon ,  Frank S. Allen ,  Jahanzeb Tareen ,  Christopher L. Gravelle

IPC: B29C35/04 ,  B64C3/18 ,  F16B5/01 ,  F16B11/00 ,  B64F5/10 ,  B29C70/30 ,  B29C70/34 ,  B64C29/00 ,  B29K105/08 ,  B29L31/30

CPC classification number: B64C3/187 ,  B29C35/045 ,  B29C70/302 ,  B29C70/34 ,  B64C3/185 ,  B64C29/0033 ,  B64F5/10 ,  F16B5/01 ,  F16B11/006 ,  B29K2105/0872 ,  B29L2031/3085

Abstract: A method of curing an aircraft component including applying a temperature sensitive adhesive to a surface of a component, the surface having a contour; positioning a heating tool including a manifold with a ventilation path such that the ventilation path is adjacent to the surface by aligning the ventilation path to the contour of the component; and heating the surface of the component with uniform airflow from the ventilation path; wherein the manifold includes a chamber with a diverging portion configured to provide uniform airflow through the ventilation path to provide heating to the surface.

公开(公告)号：US20230219305A1

公开(公告)日：2023-07-13

申请号：US17647434

申请日：2022-01-07

Applicant: The Boeing Company

Inventor： Joseph G. Kirchhoff ,  Brice A. Johnson

IPC: B29C70/30 ,  B29C70/38 ,  G05B19/4155

CPC classification number: B29C70/302 ,  B29C70/382 ,  G05B19/4155 ,  G05B2219/35113

Abstract: A method, apparatus, system, and computer program product for designing a composite hollow body. A computer system selects ply layers for the hollow composite body. The ply layers comprise courses having course edges. The computer system positions the course edges between the ply layers throughout the hollow composite body to create a staggering of the course edges between the ply layers for a design of the hollow composite body.

公开(公告)号：US11951659B2

公开(公告)日：2024-04-09

申请号：US17299450

申请日：2019-12-05

Applicant: Vestas Wind Systems A/S

Inventor： Jonathan Smith

IPC: B29C33/30 ,  B29C43/12 ,  B29C43/14 ,  B29C70/30 ,  B29C70/44 ,  B29L31/08 ,  F03D13/10

CPC classification number: B29C33/306 ,  B29C43/12 ,  B29C43/14 ,  B29C70/302 ,  B29C70/446 ,  F03D13/10 ,  B29L2031/085 ,  F05B2230/50 ,  F05B2240/302

Abstract: The invention provides a wind turbine blade body manufacturing method, the method comprising the steps of: providing a mould (40) having an elongated mould surface (43), placing a movable insert (50) on the mould surface, in a first position, forming, with the insert in the first position, a first blade body having a first length (L1), placing the insert (50) on the mould surface, in a second position, and forming, with the insert in the second position, a second blade body having a second length (L2) which is different from the first length.

公开(公告)号：US11879427B2

公开(公告)日：2024-01-23

申请号：US17819162

申请日：2022-08-11

Applicant: TPI Composites, Inc.

Inventor： Karsten Schibsbye ,  Amir Salimi

IPC: F03D1/06 ,  F03D13/10 ,  B29C70/68 ,  B23P15/04 ,  B29C70/30 ,  B29L31/08

CPC classification number: F03D1/0675 ,  B23P15/04 ,  B29C70/30 ,  B29C70/302 ,  B29C70/682 ,  F03D13/10 ,  B29L2031/085 ,  F05B2230/60 ,  F05B2240/2211 ,  Y10T29/49337 ,  Y10T29/49339

Abstract: A wind turbine blade assembly includes a first blade half and a second blade half fixed to the first blade half, defining a blade interior therebetween. The wind turbine blade assembly includes a shear web includes at least one aperture formed therein. The wind turbine blade assembly includes at least one bulkhead attached to the shear web, wherein the shear web and the at least one bulkhead are disposed in the blade interior. In some embodiments the at least one bulkhead includes a frame and a removable lid in order to expose the blade interior and the lid is returnably fixable to the at least one bulkhead. In some embodiments the first and second bulkheads include fluid conduits disposed therethrough and are spaced from one another to define first and second air circulation zones.

公开(公告)号：US11850808B2

公开(公告)日：2023-12-26

申请号：US16385005

申请日：2019-04-16

Applicant: ROLLS-ROYCE plc

Inventor： Petar Zivkovic

IPC: B29C70/30 ,  G01N21/88 ,  G06T7/00 ,  G01N21/95

CPC classification number: B29C70/302 ,  G01N21/8851 ,  G01N21/9515 ,  G06T7/0002

Abstract: A method of evaluating a composite sample comprises providing a flatbed scanner comprising a scanning head movable along a scanning direction; providing a composite sample comprising a plurality of plies arranged on planes parallel to a longitudinal direction and comprising a scanning plane containing ply edges, wherein the ply edges are oriented parallel to the longitudinal direction; arranging the composite sample on the flatbed scanner such that the scanning plane is parallel to the scanning direction and the ply edges of the scanning plane are perpendicular to the scanning direction; moving the scanning head along the scanning direction and perpendicularly to the ply edges to scan the scanning plane of the composite sample and obtain an image of the scanning plane; and evaluating the image to identify possible defects in the composite sample.

公开(公告)号：US11826976B2

公开(公告)日：2023-11-28

申请号：US17295163

申请日：2019-03-08

Applicant: IHI AEROSPACE CO., LTD.

Inventor： Takashi Harada ,  Yu Shigenari ,  Toyoharu Akimoto

IPC: B29D99/00 ,  B29C70/46 ,  B29C70/54 ,  B29C70/30 ,  B29K101/10 ,  B29L31/30 ,  B29C70/00

CPC classification number: B29D99/001 ,  B29C70/46 ,  B29C70/54 ,  B29C70/003 ,  B29C70/302 ,  B29K2101/10 ,  B29L2031/3082

Abstract: A fiber reinforced plastic (FRP) molding system in which FRP material, having stacked prepregs, is molded to manufacture an arc-shaped FRP component. The FRP molding system comprises inner and outer jig plates, a partial pressing device, and transfer devices. The jig plates are arc-shaped members having outer and inner surfaces that respectively fit with inner and outer surface shapes of the FRP component. The FRP material is sandwiched between the jig plates to form an integrated jig plate. The partial pressing device intermittently compresses a portion of the integrated jig plate in a radial direction orthogonal to an arc of the FRP component so that the FRP component is partially molded. The transfer devices intermittently move the compressed portion of the integrated jig plate by the partial pressing device. By repeating the partial pressing and the transport, the entire integrated jig plate is compressed to form the FRP component.

公开(公告)号：US11787160B2

公开(公告)日：2023-10-17

申请号：US16488116

申请日：2018-02-22

Applicant: RTL Materials Ltd.

Inventor： Andrew Daton-Lovett

IPC: B32B27/08 ,  B29C70/34 ,  B32B1/08 ,  B32B3/08 ,  B32B5/12 ,  B32B5/26 ,  B32B37/06 ,  B32B37/10 ,  E04C3/00 ,  F16L11/08 ,  F16L25/00 ,  F16S5/00 ,  B32B7/022 ,  B29C70/30 ,  B29L23/00

CPC classification number: B32B27/08 ,  B29C70/302 ,  B29C70/34 ,  B32B1/08 ,  B32B3/08 ,  B32B5/12 ,  B32B5/26 ,  B32B7/022 ,  B32B37/06 ,  B32B37/10 ,  E04C3/005 ,  F16L11/08 ,  F16L25/00 ,  F16S5/00 ,  B29L2023/00 ,  B32B2250/20 ,  B32B2250/44 ,  B32B2305/18 ,  B32B2307/548 ,  B32B2597/00

Abstract: Extendible slit tube members and methods for manufacturing extendible slit tube members are provided. In one aspect, an extendible member (10) comprises a laminated shell (2) of plural fibre reinforced layers (P1-P5) constructed and arranged to be configurable between a coiled form and an extended form. In the extended form (12) the shell is resiliently biased in the form of an elongate tube having longitudinal edges (14) defining a slit (3) along its length and wherein the shell can be opened out at the slit to assume a flattened form in which it can be wound about an axis extending transversely to its longitudinal direction to assume its coiled form (11). In the region of one or both longitudinal edges (50), the amount of reinforcing fibre is less than in the region between the edge regions (51). In another aspect, a flexible cord (40) may be attached along the edge of a shell.

公开(公告)号：US20230382061A1

公开(公告)日：2023-11-30

申请号：US18249010

申请日：2021-10-07

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Thomas BARNETT ,  Lee PROUDLER

IPC: B29C70/30 ,  B64F5/10

CPC classification number: B29C70/302 ,  B64F5/10 ,  B29L2031/3085

Abstract: A method of manufacturing an aircraft aerofoil such as a winglet. The aircraft aerofoil includes: a first cover, a second cover, an aerofoil leading edge, and an aerofoil trailing edge where the first and second cover are joined at a trailing edge interface. The first cover is formed by: a lay-up step in which a plurality of fibre plies are laid up to obtain a preform, wherein the preform has a thickness and a preform trailing edge, and the preform is laid up during the lay-up step with a ramp of decreasing thickness where the thickness of the preform decreases towards the preform trailing edge; and a curing step in which the preform is cured to form the first cover, wherein the ramp of decreasing thickness cures during the curing step to form a contact surface of the first cover.

公开(公告)号：US11773824B2

公开(公告)日：2023-10-03

申请号：US17314287

申请日：2021-05-07

Applicant: Siemens Gamesa Renewable Energy A/S

Inventor： Mogens Nielsen

IPC: F03D3/06 ,  B29C70/30 ,  B29C33/38 ,  B29C70/54 ,  B29L31/08

CPC classification number: F03D3/062 ,  B29C33/3842 ,  B29C70/302 ,  B29C70/54 ,  B29L2031/085 ,  F05B2220/30 ,  F05B2230/20

Abstract: Provided is a method of manufacturing a wind turbine rotor blade, which method includes the steps of preparing a mold by forming a partial negative leading-edge profile in a first mold half, which partial negative leading-edge profile includes a plurality of first indentations along a leading edge region of the first mold half; forming a partial negative leading-edge profile in a second mold half, which partial negative leading-edge profile includes a complementary plurality of second indentations along a leading edge region of the second mold half; and wherein the combined shape of a first indentation and a complementary second indentation corresponds to the negative shape of a leading-edge fin that will extend radially outward from the body of the rotor.