The present invention discloses a method for manufacturing a thin-walled metal component by three-dimensional (3D) printing and hot gas bulging. The present invention uses 3D printing to obtain a complex thin-walled preform, which reduces a deformation during subsequent hot gas bulging. The present invention avoids local bulging thinning and cracking, undercuts at the parting during die closing, and wrinkles due to the uneven distribution of cross-sectional materials, etc. The present invention obtains a high accuracy in the form and dimension through hot gas bulging. After a desired shape is obtained by hot gas bulging, a die is closed to keep the component under high temperature and high pressure for a period of time, so that a grain and a phase of the material are transformed to form a desired microstructure.

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.

An apparatus for forming a part is provided, which includes a die. The die includes a round orifice, a central mandrel disposed within the round orifice, and a plurality of bridges and a corresponding plurality of portholes between the bridges. The bridges and the portholes extending around the central mandrel. A spacing of the bridges around the mandrel is non-equiangular. The die allows a material to be extruded through the die to form a round, closed geometry tube from the material such that the round, closed geometry tube has non-equiangular welds after emerging from the die.

An apparatus for forming a part is provided, which includes a die. The die includes a round orifice, a central mandrel disposed within the round orifice, and a plurality of bridges and a corresponding plurality of portholes between the bridges. The bridges and the portholes extending around the central mandrel. A spacing of the bridges around the mandrel is non-equiangular. The die allows a material to be extruded through the die to form a round, closed geometry tube from the material such that the round, closed geometry tube has non-equiangular welds after emerging from the die.

The present invention discloses a method for manufacturing a thin-walled metal component by three-dimensional (3D) printing and hot gas bulging. The present invention uses 3D printing to obtain a complex thin-walled preform, which reduces a deformation during subsequent hot gas bulging. The present invention avoids local bulging thinning and cracking, undercuts at the parting during die closing, and wrinkles due to the uneven distribution of cross-sectional materials, etc. The present invention obtains a high accuracy in the form and dimension through hot gas bulging. After a desired shape is obtained by hot gas bulging, a die is closed to keep the component under high temperature and high pressure for a period of time, so that a grain and a phase of the material are transformed to form a desired microstructure.

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.

The present invention discloses a method for pressure forming of an aluminum alloy special-shaped tubular component by using an ultra-low temperature medium. By means of the characteristics that the forming property of an aluminum alloy tube is greatly improved under ultra-low temperature conditions, a tube is cooled and pressurized in a die through an ultra-low temperature medium, so that the tube forms a special-shaped tubular component at an ultra-low temperature. In the method for pressure forming of an aluminum alloy special-shaped tubular component by using an ultra-low temperature medium, the ultra-low temperature medium is not only used for cooling the die and the tube, but also used for pressurization to achieve flexible loading of the tube, which is favorable for forming complex special-shaped tubular components with varied cross-sections.

The present invention discloses a method for pressure forming of an aluminum alloy special-shaped tubular component by using an ultra-low temperature medium. By means of the characteristics that the forming property of an aluminum alloy tube is greatly improved under ultra-low temperature conditions, a tube is cooled and pressurized in a die through an ultra-low temperature medium, so that the tube forms a special-shaped tubular component at an ultra-low temperature. In the method for pressure forming of an aluminum alloy special-shaped tubular component by using an ultra-low temperature medium, the ultra-low temperature medium is not only used for cooling the die and the tube, but also used for pressurization to achieve flexible loading of the tube, which is favorable for forming complex special-shaped tubular components with varied cross-sections.

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 part includes extruding a billet through a die, forming a round, closed geometry tube from the billet, and hydroforming the round, closed geometry tube. The extrusion die contains an orifice with a central mandrel, a plurality of bridges, and a corresponding plurality of portholes between the bridges. A spacing of the bridges around the mandrel is non-equiangular. As a result, the round, closed geometry tube has non-equiangular welds after emerging from the die.