An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.

The present disclosure includes calculating coordinates of a midpoint of one of a plurality of first tool teaching points and the subsequent first tool teaching point, and calculating coordinates of a midpoint of one of a plurality of second tool teaching points that corresponds to the one first tool teaching point and the subsequent second tool teaching point, calculating an inter-midpoint distance between the midpoint of the first tool teaching points and the midpoint of the corresponding second tool teaching points, determining whether the inter-midpoint distance is within a given tolerance range, and reporting, when the inter-midpoint distance is out of the given tolerance range, the corresponding first tool teaching points and second tool teaching points as poor.

A single piece stent construction having a plurality of commissure posts, each of which extends upwardly from a solid ring along a bend line and generally along a central longitudinal axis of the stent.

A single piece stent construction having a plurality of commissure posts, each of which extends upwardly from a solid ring along a bend line and generally along a central longitudinal axis of the stent.

A method and apparatus for processing fuselage sections. A first fuselage section is held in a cradle system. A current shape of the first fuselage section in the cradle system is measured. Forces to change the current shape of the first fuselage section to a desired shape for connecting the first fuselage section to a second fuselage section are identified. The forces identified are applied using a system to change the current shape of the first fuselage section towards the desired shape.

Provided is a method for forming a blank, the method being capable of improving both yields and formability. The method for forming a blank 1 includes forming the blank 1 into a preforming shape by plastic deformation and then plastically deforming the blank 1 from the preforming shape into a final shape. The preforming shape is determined so that, in each of cross sections in the final shape, the ratio (L1/L0) of a cross-sectional line length L1 in the preforming shape to a cross-sectional line length L0 in the final shape in the same cross section position falls within a predetermined tolerance range.

Provided is a method for forming a blank, the method being capable of improving both yields and formability. The method for forming a blank 1 includes forming the blank 1 into a preforming shape by plastic deformation and then plastically deforming the blank 1 from the preforming shape into a final shape. The preforming shape is determined so that, in each of cross sections in the final shape, the ratio (L1/L0) of a cross-sectional line length L1 in the preforming shape to a cross-sectional line length L0 in the final shape in the same cross section position falls within a predetermined tolerance range.

In a localized torsional severe plastic deformation method for conical tube metal, a desired region of a conical tube metal can be subjected to severe plastic deformation using molds in which roughness is formed at predetermined regions. The method includes roughening a predetermined region of each of the molds; sticking the conical tube metal only to the roughened regions of the molds; moving the lower mold toward the upper mold to apply a load to the conical tube metal; and rotating the molds to apply severe plastic deformation to the conical tube metal only at the regions stuck to the roughened regions of the molds.

In a localized torsional severe plastic deformation method for conical tube metal, a desired region of a conical tube metal can be subjected to severe plastic deformation using molds in which roughness is formed at predetermined regions. The method includes roughening a predetermined region of each of the molds; sticking the conical tube metal only to the roughened regions of the molds; moving the lower mold toward the upper mold to apply a load to the conical tube metal; and rotating the molds to apply severe plastic deformation to the conical tube metal only at the regions stuck to the roughened regions of the molds.

A machine tool provided with a tool spindle and a work table for supporting a workpiece for plastic forming on a workpiece with a tool attached to the tool spindle. The partially curved tool is has a moving mechanism to move the tool spindle relative to the workpiece, a spindle rotating motor to turn the tool spindle relative to the workpiece, a movement control unit to control the moving mechanism to move the tool along the workpiece while pressing a curved portion on the surface to be machined, and a turn control unit to control the spindle rotating motor to orient a normal line of the curved portion toward the surface of the workpiece at a reference position taken as a reference.