A steam turbine includes: a rotor shaft including a shaft core that rotates about an axis and disk portions that are fixed to the shaft core and expand toward a radially outer side in the shaft core; and a plurality of rotor blades that are fixed to outer peripheries of the disk portions and are disposed in a circumferential direction of the shaft core. A first surface that is toward a first direction including a directional component toward a radially inner side of the shaft core is formed on each of the rotor blades, and a second surface that is toward a second direction including a directional component toward the radially outer side and faces the first surface is formed on each of the disk portions.

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 exhaust air energy recovery system configured for efficiently extracting energy from an exhaust stack of a building, duct, mine, server, or the like. The system includes an exhaust stack through which exhaust air moves and a turbine assembly connected to the exhaust stack by one or more legs. The turbine assembly is configured to generate energy from the exhaust air, and the turbine assembly includes a generator configured to convert energy based on the exhaust air; a turbine rotor connected to the generator; and a hub portion interposed between the generator and the lower blade plate.

A nozzle for use with a rotor blade for a reaction drive type helicopter includes a first wall, a second wall opposing the first wall, and sidewalls extending between the first wall and the second wall enclosing a cavity having an upstream end and a downstream end. The nozzle includes an inlet section for receiving a gasflow at the upstream end. The distance between the first wall and the second wall reduces to a throat downstream of the inlet section. An expansion section extending from the throat, downstream thereof.

An apparatus and method of cooling a rotatable member enclosed within a casing are provided. The gas compressor includes a rotor, a plurality of stages of compression extending along said rotor from an inlet stage configured to receive a flow of relatively low pressure gas to an outlet stage configured to discharge a flow of relatively high pressure gas, a casing at least partially surrounding said plurality of stages, and a conduit extending radially inwardly from said casing to an area proximate said rotor.

A reaction turbine operates on the heat released from the condensation of steam, combined with inherent steam pressure and temperature heads. A series of rotors, each containing multiple curved internal channels, provide compressive boosts between successive stages, while avoiding excessive self-compression. Compressive effects and shock waves generated within these channels provide high levels of condensation, thereby releasing immense amounts of heat. The resulting hot vapor and condensate droplets are then ejected tangentially at the periphery of the rotors to generate thrust. The exhaust steam from the last stage is then compressed and returned to the engine inlet to be mixed with the incoming fresh steam, thereby efficiently completing the system cycle without the need of large cooling towers for condensation.

A combination including a seal (36-38) for sealing a gap (s) between blade platforms (11, 21) of two adjacent blades of a turbomachine and a reducer (31; 32-34) for reducing vibrations of at least one of the blades, the seal including at least one rib (36) having a rib thickness and at least one wall (37) having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing (32) having at least one cavity (33) in which at least one tuning element (34) is disposed with play for impacting contact with the tuning-element guide housing.

A gas turbine having an axially adjustable rotor, has the following components: at least one external compressor air bleed for bleeding compressor air; a control valve for adjusting the amount of compressor air bled via the at least one external compressor air bleed; an axial thrust piston that can be supplied with the compressor bleed air via a supply line in such a way that a different axial compensation thrust is applied to same when the amount of compressor bleed air is adjusted; and a radial bearing which cooperates with the axial thrust piston for bearing purposes, and which can also be directly or indirectly supplied with the compressor bleed air via the supply line.

A rotor support system for a gas turbine engine may generally include a bearing assembly and a load reduction member configured to be coupled between the bearing assembly and a support frame of the engine. The load reduction member may include a fuse portion configured to fail when a load transmitted through the load reduction member exceeds a predetermined load threshold. The system may also include a load recoupling member provided between the bearing assembly and the support frame. The load recoupling member may be formed from a super-elastic shape memory alloy that allows the load recoupling member to undergo recoverable deformation without failing when the fuse portion fails such that the load recoupling member maintains a mechanical connection between the bearing assembly and the support frame.

Disclosed is a reaction-type steam turbine, including: a housing provided at a first side thereof with a steam inlet tube and at a second side thereof with a steam outlet tube, the housing having a space formed therein; and a turbine shaft provided to pass through the space of the housing, with a plurality of disk blades fitted over the turbine shaft, wherein a guide blade assembly is coupled to the turbine shaft at a position between a duct of the steam inlet tube and the disk blades, the guide blade assembly guiding steam introduced through the steam inlet tube into the space of the housing toward the disk blades.