A method of forming a gas turbine engine according to an example of the present disclosure includes, among other things, attaching a first skin to a main body to enclose at least one internal channel, the first skin and the main body cooperating to define pressure and suction sides of an airfoil, holding the first skin and the main body between first and second dies, and pressurizing the at least one internal channel such that walls of the first skin and the main body move outwardly toward surface contours of the first and second dies. A gas turbine engine component is also disclosed.

An apparatus and a method for correcting a vehicle member, by which twisting or deflection of a vehicle member including a side member of the vehicle, may be corrected, may be disclosed, wherein the apparatus for correcting a vehicle member includes a base extending in a lengthwise direction thereof, and a plurality of correction units disposed on the base to be movable.

Embodiments provide a helical layer structure including: a helical core member which is formed of a flexible, lengthy, flat plate-like core member and which is formed of a steel plate made of a metal material, such as iron; and a polymeric coating layer which is formed of a polymeric material such as a thermosetting elastic material or a thermoplastic elastic material, and which coats the helical core member. The manufacturing method of the helical layer structure includes: a feeding step of feeding a core member having flexibility; a supply step of supplying the polymeric material having fluidity; a coating step of coating the core member with the polymeric material; a cooling step of cooling a coated intermediate which is coated with the polymeric material; and a helix formation step of helically twisting the coated intermediate to form the helical layer structure.

Embodiments provide a helical layer structure including: a helical core member which is formed of a flexible, lengthy, flat plate-like core member and which is formed of a steel plate made of a metal material, such as iron; and a polymeric coating layer which is formed of a polymeric material such as a thermosetting elastic material or a thermoplastic elastic material, and which coats the helical core member. The manufacturing method of the helical layer structure includes: a feeding step of feeding a core member having flexibility; a supply step of supplying the polymeric material having fluidity; a coating step of coating the core member with the polymeric material; a cooling step of cooling a coated intermediate which is coated with the polymeric material; and a helix formation step of helically twisting the coated intermediate to form the helical layer structure.

In a method of manufacturing a fin-assembled tube by arranging a helical fin in an interior of a tube, a plate-shaped fin material is inserted into the interior of the tube and the helical fin is formed by twisting the fin material in the interior of the tube.

The present invention relates to a torsional severe plastic deformation method for a metal bar to which surface polishing is applied to the metal bar to improve the mechanical properties of the metal bar. According to an embodiment of the present invention, there is provided a torsional severe plastic deformation method for a metal bar, which includes: applying torsion to a metal bar; and removing a surface defect on the surface of the metal bar, the surface defect being caused by the applying of torsion, wherein the removing of the surface defect is carried out in a continuous manner in which the removing of the surface defect is performed together with the applying of torsion or in a discontinuous manner in which the applying of torsion is temporarily stopped and then the applying of torsion is performed, and the removing of a surface defect increases the amount of torsional rotation or the shear strain applied to the metal bar.

The present invention relates to a torsional severe plastic deformation method for a metal bar to which surface polishing is applied to the metal bar to improve the mechanical properties of the metal bar. According to an embodiment of the present invention, there is provided a torsional severe plastic deformation method for a metal bar, which includes: applying torsion to a metal bar; and removing a surface defect on the surface of the metal bar, the surface defect being caused by the applying of torsion, wherein the removing of the surface defect is carried out in a continuous manner in which the removing of the surface defect is performed together with the applying of torsion or in a discontinuous manner in which the applying of torsion is temporarily stopped and then the applying of torsion is performed, and the removing of a surface defect increases the amount of torsional rotation or the shear strain applied to the metal bar.

In a case of a mark left type, a slit is formed on a line side (slit side) of a joint portion. The slit is formed, for example, with a scroll saw. By the formation of the slit, a length of the joint portion in a direction orthogonal to an axial direction of a single ring is set to approximately 0.7 mm. In a case of a mark removed type, a slit and a slit are formed respectively on the line side (slit side) and a side opposite thereto of the joint portion. Those slits are formed, for example, with the scroll saw. By the formation of those slits, the length of the joint portion in the direction orthogonal to the axial direction of the single ring is set to approximately 0.8 mm.

In a case of a mark left type, a slit is formed on a line side (slit side) of a joint portion. The slit is formed, for example, with a scroll saw. By the formation of the slit, a length of the joint portion in a direction orthogonal to an axial direction of a single ring is set to approximately 0.7 mm. In a case of a mark removed type, a slit and a slit are formed respectively on the line side (slit side) and a side opposite thereto of the joint portion. Those slits are formed, for example, with the scroll saw. By the formation of those slits, the length of the joint portion in the direction orthogonal to the axial direction of the single ring is set to approximately 0.8 mm.

Apparatus for use in the formation of a helical screw flight, the apparatus comprising: a drive first and second support heads arranged for relative axial movement with respect to one another in a direction of a main axis in response to actuation of the drive the first and second support heads being configured so as to be able to provide for a plurality of position adjustments including a lateral position adjustment whereby the first and second support heads can be displaced or moved laterally with respect to the main axis in a direction of respective lateral axes and a rotational position adjustment wherein at least one of the first and second work heads can be rotated about a rotation axis which extends in a direction generally parallel to coaxial with the main axis.