A rotary machine assembly for a turbomachine, such as a rotor, having a rotor wheel where a plurality of circumferentially spaced female dovetail slots are obtained. The rotary machine assembly also comprises a plurality of blades. Between each blade and the adjacent one there is an interface angle. Each blade comprises a male dovetail, configured to fit with a corresponding female dovetail slot of the rotor wheel along an insertion direction. The female dovetail slots are shaped so that the insertion direction of each male dovetail is convergent with the rotation axis of the rotor wheel, so as to form with it an insertion angle, so as to insert gradually all the male dovetails into the female dovetail slots and packing them also gradually. A method for assembling a rotary machine assembly, which does not require any specific tool, is also disclosed.

Disclosed is a steam turbine capable of reducing the load of a bearing supporting a turbine shaft transmitting rotational driving force of a plurality of nozzle-equipped rotary bodies arranged in multiple stages. The steam turbine includes a housing (110); a turbine shaft (120) pivotably supported by a bearing (121) in the housing; and a plurality of dish-shaped nozzle-equipped rotary bodies (130) integrally combined with the turbine shaft (120), provided with one or more nozzle holes (131) from which working fluid is ejected so that the nozzle rotations bodies (130) can be rotated, and stacked in an axial direction of the turbine shaft (120). The nozzle hole (131) is inclined with respect to a normal direction n of the periphery surface of the nozzle-equipped rotary body (130) and is inclined toward an axial direction c of the turbine shaft (120).

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 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 air cycle machine (ACM) compressor housing includes a body including an exterior surface and an interior portion. An inlet is integrally formed with the body. The inlet includes an inlet passage fluidically connected with the interior portion. An outlet is integrally formed with the body. The outlet includes an outlet passage fluidically connected with the interior portion. A bypass is integrally formed with the body. The bypass includes a bypass passage fluidically connected with the interior portion. The bypass passage includes a first end portion extending outwardly from the body, a second end portion and an intermediate portion extending therebetween. The first end portion includes a wall thickness of between about 0.330-inch (8.382-mm) and 0.390-inch (9.906-mm).

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 air cycle machine (ACM) compressor housing includes a body including an exterior surface and an interior portion. An inlet is integrally formed with the body. The inlet includes an inlet passage fluidically connected with the interior portion. An outlet is integrally formed with the body. The outlet includes an outlet passage fluidically connected with the interior portion. A bypass is integrally formed with the body. The bypass includes a bypass passage fluidically connected with the interior portion. The bypass passage includes a first end portion extending outwardly from the body, a second end portion and an intermediate portion extending therebetween. The first end portion includes a wall thickness of between about 0.330-inch (8.382-mm) and 0.390-inch (9.906-mm).

A reaction-type turbine according to the present invention is configured in that a portion of a rotary shaft module which penetrates through a side with an inlet portion of a housing has a diameter larger than the diameters of other portions. Thus, the pressurized area in which a working fluid applies pressure to a rotary shaft in the direction opposite to the working fluid flow direction increases, thus increasing force in the direction opposite to the working fluid flow direction. As a result, axial direction force applied to the rotary shaft in the working fluid flow direction may be reduced. Therefore, the reaction-type turbine of the present invention has the advantages of eliminating the necessity of installing a separate thrust bearing for supporting axial force in the working fluid flow direction.

A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.