A method for manufacturing a wind turbine blade is provided, including the steps of: a) arranging a fiber lay-up on a mandrel tool, the mandrel tool including a frame and, as seen in cross-section, at least two mandrel portions connected to the frame, and wherein at least a portion of the fiber lay-up is supported by an outer surface of the at least two mandrel portions, b) reducing a cross-section size of the mandrel tool by retracting at least one of the mandrel portions towards the frame, c) arranging the mandrel tool inside adjacent blade sections, d) increasing the cross-section size of the mandrel tool by extending at least one of the mandrel portions away from the frame, and e) infusing at least a portion of the fiber lay-up with a resin and curing the resin to obtain a cured joining portion joining the blade sections inside.

A method for manufacturing a wind turbine blade is provided, including the steps of: a) arranging a fiber lay-up on a mandrel tool, the mandrel tool including a frame and, as seen in cross-section, at least two mandrel portions connected to the frame, and wherein at least a portion of the fiber lay-up is supported by an outer surface of the at least two mandrel portions, b) reducing a cross-section size of the mandrel tool by retracting at least one of the mandrel portions towards the frame, c) arranging the mandrel tool inside adjacent blade sections, d) increasing the cross-section size of the mandrel tool by extending at least one of the mandrel portions away from the frame, and e) infusing at least a portion of the fiber lay-up with a resin and curing the resin to obtain a cured joining portion joining the blade sections inside.

A method of a coating by additive manufacturing on a turbomachine casing includes depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments. A filamentary material deposition system is positioned from the internal surface of the casing; a first layer of the coating is deposited over 360′; a rotation of the filamentary material deposition system is carried out by a first predetermined angle and the filamentary material deposition system is positioned from the deposited layer; a second layer of coating is deposited on the first coating layer, on a sector of the casing; a displacement is carried out corresponding to the first sector already covered, then for the following sectors until 360° is covered; and after having carried out a rotation of the filamentary material deposition system.

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.

A pressure vessel includes a liner including a cylindrical body and a dorm portion continuous with at least one end of the body in an axial direction and includes a reinforced fiber sheet covering an outer side of the liner and made of fabric. The reinforced fiber sheet includes first yarns arranged on the body and the dorm portion such that yarn main axes of the first yarns extend in the circumferential direction of the liner and second yarns arranged on the body and the dorm portion such that yarn main axes of the second yarns extend in the axial direction of the liner. A total number of the first yarns or the second yarns that exist per unit length in the axial direction of the liner is smaller in the dorm portion than in the body.

A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.

A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.

Methods and manufactures disclosed herein generally relate to a cannular composite (ITC) structure composed of multiple layers of sealing, reinforcement, sensing, protection, and interspatial injected materials.

Methods and manufactures disclosed herein generally relate to a cannular composite (ITC) structure composed of multiple layers of sealing, reinforcement, sensing, protection, and interspatial injected materials.

A system for constructing a composite structure includes a braiding machine, a winding tool and a forming machine. The composite structure is constructed of a wound tubular braiding. The wound tubular braiding is constructed of a biaxial or triaxial tubular braid of unidirectional tape.