A method for manufacturing a blisk includes an intermediate product molding step of molding a blisk intermediate product including a circular disk-corresponding part, a plurality of rotor blade-corresponding parts, and bridges each connecting a front edge of one of each pair of the rotor blade-corresponding parts adjacent to each other and a rear edge of the other one of the rotor blade-corresponding parts. The method for manufacturing the blisk further includes a disk finishing step of cutting the disk-corresponding part so as to finish the disk-corresponding part into the disk in a product form, and a rotor blade finishing step of cutting each bridge so as to finish the respective rotor blade-corresponding parts into the respective rotor blades in a product form.

A method for manufacturing a blisk includes an intermediate product molding step of molding a blisk intermediate product including a circular disk-corresponding part, a plurality of rotor blade-corresponding parts, and bridges each connecting a front edge of one of each pair of the rotor blade-corresponding parts adjacent to each other and a rear edge of the other one of the rotor blade-corresponding parts. The method for manufacturing the blisk further includes a disk finishing step of cutting the disk-corresponding part so as to finish the disk-corresponding part into the disk in a product form, and a rotor blade finishing step of cutting each bridge so as to finish the respective rotor blade-corresponding parts into the respective rotor blades in a product form.

An improved forging process includes the steps of pre-heating the top and bottom dies of a forging press to a specified temperature, and maintaining both dies at the specified temperature during subsequent forging operation with closed-loop temperature control systems. The top and bottom forging dies are each coupled to a dedicated thermic fluid heater, the temperature of each die is individually measured and compared to a respective target temperature, and the respective thermic fluid heaters are controlled in relation to detected deviations of the measured temperatures from the target temperatures. Compressor wheel preforms produced according to this process consistently exhibit primarily radial grain orientations that exactly match the expected values.

An improved forging process includes the steps of pre-heating the top and bottom dies of a forging press to a specified temperature, and maintaining both dies at the specified temperature during subsequent forging operation with closed-loop temperature control systems. The top and bottom forging dies are each coupled to a dedicated thermic fluid heater, the temperature of each die is individually measured and compared to a respective target temperature, and the respective thermic fluid heaters are controlled in relation to detected deviations of the measured temperatures from the target temperatures. Compressor wheel preforms produced according to this process consistently exhibit primarily radial grain orientations that exactly match the expected values.

An embodiment of a tool assembly includes a hub connected to a distal end of a spring-loaded shaft assembly disposed along a first axis. An upper hub portion is adjacent to the distal end of the spring-loaded shaft assembly aligned with the first axis, and a lower hub portion extends along a second axis, forming a nonzero angle relative to the first axis. A roller disk is joined to the lower portion of the hub, and is rotatable about the second axis parallel to the second portion of the hub. A load cell is disposed along the first axis between a proximal end of the shaft and the roller disk, and is adapted to measure a downward force applied along the shaft assembly.

A centrifugal fan is provided that includes a main plate configured to be rotated about a rotational axis, a shroud, having a suction opening, and a plurality of blades arranged in a circumferential direction between the main plate and the shroud to allow air suctioned in through the suction opening to flow from a front edge to a rear edge of each blade. Assuming a first cross section, a second cross section, a third cross section, and a fourth cross section of each blade sequentially taken at layers from the shroud to the main plate, a front edge of the first cross section is located farther from the rotational axis than a front edge of the fourth cross section, and a rear edge of the first cross section is located closer to the rotational axis than a rear edge of the fourth cross section.

A centrifugal fan is provided that includes a main plate configured to be rotated about a rotational axis, a shroud, having a suction opening, and a plurality of blades arranged in a circumferential direction between the main plate and the shroud to allow air suctioned in through the suction opening to flow from a front edge to a rear edge of each blade. Assuming a first cross section, a second cross section, a third cross section, and a fourth cross section of each blade sequentially taken at layers from the shroud to the main plate, a front edge of the first cross section is located farther from the rotational axis than a front edge of the fourth cross section, and a rear edge of the first cross section is located closer to the rotational axis than a rear edge of the fourth cross section.

A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with a regionally selective tempering process in which a treated region receives a tempering process while an untreated region is excluded from receiving the tempering process. The target portion may be the treated region while the remainder portion is the untreated region. The tempering process of the regionally selective tempering process may be configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component.

A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with a regionally selective tempering process in which a treated region receives a tempering process while an untreated region is excluded from receiving the tempering process. The target portion may be the treated region while the remainder portion is the untreated region. The tempering process of the regionally selective tempering process may be configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component.

A method and manufacturing unit for producing a rotor blade (5) of a wind turbine (1) from at least a first rotor blade element (11, 11, 12, 12) and a second rotor blade element (11, 11, 12, 12). The first rotor blade element (11, 11, 12, 12) and the second rotor blade element (11, 11, 12, 12) are positioned in the desired relative arrangement with respect to each other such that a joint gap (13) remains between the first rotor blade element (11, 11, 12, 12) and the second rotor blade element (11, 11, 12, 12). Adhesive is introduced into the joint gap (13) for joining the first rotor blade element (11, 11, 12, 12) and the second rotor blade element (11, 11, 12, 12).