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.

A drill bit includes a drill bit head, a multi-strand helix made up of three or more helix ribs, and a shank end along a drill bit axis. The multi-strand helix is made up of a conveyance area, a helix gradient, and a pitch. The helix ribs extend parallel to the drill bit axis in a first area adjacent to the drill bit head and a second area adjacent to the shank end.

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.

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.

A method for producing a drill includes cold forming of a rod-shaped blank to form a semifinished product having three or more rectilinear longitudinal ribs extending along a longitudinal axis of the semifinished product, introducing the longitudinal ribs into a first die and a second die in a working direction, where the first die bears against the longitudinal ribs in a direction of rotation about the longitudinal axis and the second die bears against the longitudinal ribs counter to the direction of rotation, pivoting the first die in the direction of rotation in relation to the second die in order to twist the longitudinal ribs between the first and second dies, pulling the longitudinal ribs 31 through the pivoted first die and the second die counter to the working direction in order to twist the longitudinal ribs and apply a drill head to the rear end in the working direction.

A compressive torsion forming device for processing a processing material using a first die and a second die facing each other includes a sliding portion that includes a first hydraulic chamber, and slides in accordance with a change in internal pressure of the first hydraulic chamber so as to move the first die in a direction of an axis; a rotating table provided with the second die and rotatable about the axis; a table support portion provided opposite to the second die with the rotating table interposed therebetween in the direction of the axis; and a rotational bearing that rotatably supports the rotating table with respect to the table support portion, and receives a force acting on the rotating table in a direction from the second die toward the rotating table.

A compressive torsion forming device for processing a processing material using a first die and a second die facing each other includes a sliding portion that includes a first hydraulic chamber, and slides in accordance with a change in internal pressure of the first hydraulic chamber so as to move the first die in a direction of an axis; a rotating table provided with the second die and rotatable about the axis; a table support portion provided opposite to the second die with the rotating table interposed therebetween in the direction of the axis; and a rotational bearing that rotatably supports the rotating table with respect to the table support portion, and receives a force acting on the rotating table in a direction from the second die toward the rotating table.

A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to establish pressure and suction sides of an airfoil, positioning the airfoil between first and second dies of a deforming station, heating the airfoil body to a first predefined temperature threshold between the first and second dies, and moving the first die relative to the second die to hold the airfoil between the first and second dies subsequent to the heating step, and then deforming the airfoil between the first and second dies.

A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to establish pressure and suction sides of an airfoil, positioning the airfoil between first and second dies of a deforming station, heating the airfoil body to a first predefined temperature threshold between the first and second dies, and moving the first die relative to the second die to hold the airfoil between the first and second dies subsequent to the heating step, and then deforming the airfoil between the first and second dies.

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.