A method of hyper-feed machining the bladed components of turbomachines, and more specifically their bladed components. Hyper-feed machining, by means of the physical process of controlled fracturing, is the fastest, most precise, and nearest net shape method of machining in existence. The practical effects of the invention are: (1) the production of new and useful small-scale gas turbine engines for a wide range of previously impossible or impractical applications, and (2) the production of existing larger-scale gas turbine engines with great improvements in material removal rates by orders of magnitude, greater precision and geometric complexity of the bladed components, faster overall rates of production of these engines, and significantly reduced costs in production. As a consequence, the best preferred embodiment of the invention is the small-scale turboshaft electric engine for automotive vehicles, which makes possible a turbo-electric vehicle that replaces both the electric battery vehicle and the piston-engine vehicle.

A method of hyper-feed machining the bladed components of turbomachines, and more specifically their bladed components. Hyper-feed machining, by means of the physical process of controlled fracturing, is the fastest, most precise, and nearest net shape method of machining in existence. The practical effects of the invention are: (1) the production of new and useful small-scale gas turbine engines for a wide range of previously impossible or impractical applications, and (2) the production of existing larger-scale gas turbine engines with great improvements in material removal rates by orders of magnitude, greater precision and geometric complexity of the bladed components, faster overall rates of production of these engines, and significantly reduced costs in production. As a consequence, the best preferred embodiment of the invention is the small-scale turboshaft electric engine for automotive vehicles, which makes possible a turbo-electric vehicle that replaces both the electric battery vehicle and the piston-engine vehicle.

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.

A mounting plate for forming a gas turbine engine component according to an example of the present disclosure includes, among other things, a plate body defining an abutment dimensioned to mate with a forming die. The plate body defines at least one internal cooling circuit. The at least one internal cooling circuit includes a passageway having an intermediate portion interconnecting inlet and outlet portions. The intermediate portion is dimensioned to follow a perimeter of the abutment. The intermediate portion includes a plurality of fins extending partially from a first sidewall towards a second sidewall opposed to the first sidewall. A method of forming a gas turbine engine component is also disclosed.

A method for producing a rotor disk or a rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein at least one blade groove of the rotor disk for arrangement of a blade foot of a rotor blade for fastening the rotor blade to the rotor disk, or a blade foot of the rotor blade for arrangement in a blade groove of a rotor disk for fastening the rotor blade to the rotor disk is fabricated using an electrochemical material removal and in the axial direction has a profile which is curved once or more.

A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free end. The blade also includes an abrasive tip at the free end of the airfoil section. The abrasive tip includes particles disposed in a matrix material. The matrix material is a polymeric material that has a glass transition temperature greater than or equal to about 225 degrees C. (437 degrees F.). A gas turbine engine and a method of fabricating a blade are also disclosed.

A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free end. The blade also includes an abrasive tip at the free end of the airfoil section. The abrasive tip includes particles disposed in a matrix material. The matrix material is a polymeric material that has a glass transition temperature greater than or equal to about 225 degrees C. (437 degrees F.). A gas turbine engine and a method of fabricating a blade are also disclosed.

An automatically adjustable universal wind turbine blade handling apparatus including a rigid frame supporting a base plate and a plurality of adjustable support members. The support members are spaced from each other and include a vertical pillar, a moveable shaft that can be telescopingly extended or retracted, and a pivotable pad coupled to shaft. The plurality of support members are automatically adjusted to position the pad at predetermined heights and/or angles to accommodate a variety of blade types/sizes.

An automatically adjustable universal wind turbine blade handling apparatus including a rigid frame supporting a base plate and a plurality of adjustable support members. The support members are spaced from each other and include a vertical pillar, a moveable shaft that can be telescopingly extended or retracted, and a pivotable pad coupled to shaft. The plurality of support members are automatically adjusted to position the pad at predetermined heights and/or angles to accommodate a variety of blade types/sizes.

Water droplets that are moved on blade surfaces of a rotor blade are effectively guided toward the blade trailing edge while influence on the strength of the rotor blade is suppressed. A steam turbine rotor blade having a tie-boss for joining to adjacent blades at an intermediate position in the blade length direction is provided. The steam turbine rotor blade includes an airfoil part in which a blade surface is partly hollow as viewed in a section obtained by cutting by an orthogonal plane to a rotation center line of a turbine and a recessed blade surface that is this hollow partial blade surface passes through the blade root side of the tie-boss at least in a region on the pressure side and extends in a strip shape in the blade chord length direction.