A casting method includes: forming a seed, the seed having a first end and a second end, the forming including bending a seed precursor; placing the seed second end in contact or spaced facing relation with a chill plate; contacting the first end with molten material; and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material. The forming further included reducing a thickness of the seed proximate the first end relative to a thickness of the seed proximate the second end.

A casting method includes forming a seed. The seed has a first end and a second end and an inner diameter (ID) surface and an outer diameter (OD) surface. The seed second end is placed in contact or spaced facing relation with a chill plate. The first end is contacted with molten material. The molten material is cooled and solidified so that a crystalline structure of the seed propagates into the solidifying material. At least a portion of the seed contacted with the molten material has a solidus higher than a solidus of at least an initial pour portion of the molten material.

A gas turbine rotor having a combination of proximal embedded permanent magnets in the blended turbine(s) trunnion structure to which blades are integral to and through these distal trunnion channels attach to which turbine blades are integral to as a single component is provided. Permanent magnets or warm conducting coils or cold superconducting coils can be used. The structure rotates around a superconducting power shaft core (SPSC), running axially in relation to the turbine blade permanent magnets, for example, and embedded distal trunnion rings.

A turbine rotor for an aircraft engine includes a plurality of blades compressed by a compression ring made of ceramic matrix composite (CMC). The CMC includes at least one of: monofilaments and silicon carbide fibers. A method of extracting energy from an airflow using a turbine rotor of an aircraft engine is also disclosed.

A submersible pump assembly includes an electric motor (1) and a centrifugal pump, which is driven by the electric motor (1). A rotor (4) formed of plastic or composite material which is manufactured in the extrusion or pultrusion method.

A method of manufacturing a metal member including a first part and a second part includes a first fabrication process of fabricating the first part through a three-dimensional metal stack fabrication by a powder bed method, and a second fabrication process of fabricating an outer circumference of the second part through the three-dimensional metal stack fabrication by the powder bed method, and then sintering metallic powder remaining in an inner portion of the second part by hot isostatic pressing so as to fabricate the second part.

Methods for creating a cast component, along with the resulting cast components, are provided. The method may include heating a mold having a cavity therein; supplying a first molten metal material into the cavity of the mold such that the first molten metal material is directed to a first portion of the cavity of the mold; supplying a second molten metal material into the cavity of the mold such that the second molten metal material is directed to a second portion of the cavity of the mold, wherein the first molten metal material is compositionally different than the second molten metal material; and thereafter, allowing the first molten metal material and the second molten metal material to form the cast component.

A gas turbine engine includes a rotor that has a rim, blades extending radially outwards from the rim, a hub extending radially inwards from the rim, an arm extending axially from the rim, the arm having a radially outer surface, and a coating disposed on the radially outer surface. The coating is zirconia-toughened alumina in which the alumina is a matrix with grains of the zirconia dispersed there through. The grains of zirconia are predominantly a tetragonal crystal structure.

A blade or a vane for a gas turbine engine. The blade or vane having an aerofoil and a leading edge member attached to the aerofoil. The leading edge has an electrically conductive support member and a nano-coating formed on the support member.

A method includes applying a material coating on a surface of a machine component using a thermal spray, wherein the material coating is formed from a combination of a hardfacing material and aluminum-containing particles. The method also includes thermally treating the material coating to generate an oxide layer comprising aluminum from the aluminum-containing particles, wherein the oxide layer is configured to reduce oxidation of the hardfacing material.