A method for designing and building a wheel that is simultaneously a turbine and an impeller with a plurality of impeller blades, wherein each impeller blade of the plurality of impeller blades is hollow along an entire length of the impeller blade and which leads into a peripheral circular chamber that operates as a fueled engine (THRA). The method includes building an evolving section of an inner channel of the impeller blades with a plurality of strips each having a neutral axis, wherein each impeller blade rests on a profile of a plurality of profiles of a corresponding neutral axis, the profile built for an inlet to the turbine and for inlets to each impeller blade.

A method for designing and building a wheel that is simultaneously a turbine and an impeller with a plurality of impeller blades, wherein each impeller blade of the plurality of impeller blades is hollow along an entire length of the impeller blade and which leads into a peripheral circular chamber that operates as a fueled engine (THRA). The method includes building an evolving section of an inner channel of the impeller blades with a plurality of strips each having a neutral axis, wherein each impeller blade rests on a profile of a plurality of profiles of a corresponding neutral axis, the profile built for an inlet to the turbine and for inlets to each impeller blade.

An engine, a rotary device, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the detonation and/or combustion chamber, a fuel supply inlet configured to provide the fuel to the detonation and/or combustion chamber, at least two rotating arms extending radially from the detonation and/or combustion chamber and configured to exhaust detonation gases from detonating the fuel in the detonation and/or combustion chamber and provide a rotational thrust and/or force, the rotating arms having inner and outer walls and a nozzle at a distal end thereof, the nozzle being at or having an angle configured to provide the rotational thrust and/or force, and a plurality of cooling coils between the inner and outer walls. Alternatively, the rotary device may include a rotary disc.

An engine, a rotary device, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the detonation and/or combustion chamber, a fuel supply inlet configured to provide the fuel to the detonation and/or combustion chamber, at least two rotating arms extending radially from the detonation and/or combustion chamber and configured to exhaust detonation gases from detonating the fuel in the detonation and/or combustion chamber and provide a rotational thrust and/or force, the rotating arms having inner and outer walls and a nozzle at a distal end thereof, the nozzle being at or having an angle configured to provide the rotational thrust and/or force, and a plurality of cooling coils between the inner and outer walls. Alternatively, the rotary device may include a rotary disc.

A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.

The purpose of the present invention is to minimize fluid leakage and pressure leakage, and a turbine apparatus of the present invention comprises: a turbine (510) rotating together with a turbine shaft (513) in response to an inflow of fluid; a turbine cover (520) coupled to an upper end of the turbine (510) to seal the turbine (510); a lower nozzle plate (350) and an upper nozzle plate (370) coupled to each other in the turbine (510); a plurality of nozzles (380) coupled between the lower nozzle plate (350) and the upper nozzle plate (370) to control the amount of fluid flowing into the turbine (510); a through pipe (356) coupled to the center of an upper surface of the lower nozzle plate (350) and passing through the lower nozzle plate (350) and the upper nozzle plate (370); and a control pipe (322) rotating inside the through pipe (356) for opening and closing the nozzles (380).

The purpose of the present invention is to minimize fluid leakage and pressure leakage, and a turbine apparatus of the present invention comprises: a turbine (510) rotating together with a turbine shaft (513) in response to an inflow of fluid; a turbine cover (520) coupled to an upper end of the turbine (510) to seal the turbine (510); a lower nozzle plate (350) and an upper nozzle plate (370) coupled to each other in the turbine (510); a plurality of nozzles (380) coupled between the lower nozzle plate (350) and the upper nozzle plate (370) to control the amount of fluid flowing into the turbine (510); a through pipe (356) coupled to the center of an upper surface of the lower nozzle plate (350) and passing through the lower nozzle plate (350) and the upper nozzle plate (370); and a control pipe (322) rotating inside the through pipe (356) for opening and closing the nozzles (380).

A rotary detonation rocket engine generator system comprises an axial drive shaft coupled to an electrical generator, two support arms extending radially from the axial drive shaft, and two detonation rocket engines supported at by the support arms. In response to ignition and combustion of a fuel supplied to the detonation rocket engines, a thrust force from the detonation rocket engines causes rotation of the axial drive shaft to drive the electrical generator. Fuel (and optionally other fluids) can be supplied through channels of the axial drive shaft and the support arms to the detonation rocket engines. A housing can enclose the detonation rocket engines, the support arms, and a portion of the axial drive shaft, which can be oriented vertically. One or more support arms and associated detonation rocket engines can be incorporated into a particular assembly. A method of producing electricity with the generator system is provided.

A fluidic actuator is configured to be mounted to an airfoil surface. The actuator includes a rotor supported within a housing. The rotor contains at least one generally radially extending nozzle that converges from an entry at an interior circumference of the rotor to an exit at an exterior circumference thereof, the converging shape of the nozzle assuring high velocity airflow at the nozzle exit. In one form, each nozzle also includes a curved path by which high-pressure air is enabled to induce spinning of the rotor. The fluidic actuator further includes a diffuser through which high-pressure air from the nozzles is cyclically ejected from those of the nozzles instantaneously exposed to the diffuser. In one form, the rotor spins at 300 revolutions per second and provides nozzle ejections effective to avoid boundary layer separation; i.e. to maintain an attached boundary layer flow over the airfoil.