A radial turbine includes a housing, a rotor mounted on a shaft, an inlet channel for supplying a defined working medium, and an outlet channel. The rotor includes working cavities, with a generally spiral shape, which conduct the defined working medium from the inlet channel to the outlet channel, located near the center of the rotor. The working cavities have a generally rectangular cross-section, with a width (W), parallel to an axis of rotation of the rotor, and a height (H), parallel to a radius of the rotor. The width (W) is greater than the height (H), and the height (H) is not greater than six times a thickness of a boundary layer of the defined working medium.

An intake structure of a compressor includes an intake duct forming an intake port opening in a direction away from a central axis of the compressor and a bellmouth forming an annular channel expanding from an inlet of the compressor toward an inner space of the intake duct. The bellmouth includes a plurality of struts connecting an inner casing positioned inside the annular channel and an outer casing positioned outside the annular channel. At least one of a plurality of transverse struts, of the plurality of struts, which are located on both sides of a center plane passing through the central axis of the compressor and the center of the intake port has a trailing edge positioned on a virtual plane passing through the central axis of the compressor and a leading edge positioned on a side of the intake port with respect to the virtual plane.

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.

A turbine of an organic Ranking cycle (ORC) is described. The turbine includes a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor blades. The rotor blades are sustained by corresponding supporting disks. A main supporting disk is directly coupled to the shaft in an outer position with respect to the bearings, and the remaining supporting disks are constrained to the main supporting disk, and one to the other in succession, but not directly to the shaft. Some of the remaining supporting disks are constrained to the main supporting disk and cantileverly extend from the same side of the bearings that support the shaft, so that the center of gravity of the rotor part of the turbine is shifted more towards the bearings.

The present invention provides a rotary machine intake casing which, by using a simple configuration, makes it possible to reduce asymmetry between the flow speed of air flowing in a forward direction relative to the direction of rotation of a rotating shaft of a compressor and the flow speed of air flowing in the opposite direction. Thus, a rotary machine single-suction intake device equipped with an upstream duct (121) having a suction port (121a) opening in a direction that intersects the rotational axis of the compressor, and an intake duct body section (102) for guiding air to the compressor after the air has passed into the upstream duct (121), and connected to the upstream duct (121), wherein the channel cross-sectional area on the forward direction side (A) relative to the rotational direction of the rotating shaft differs from the channel cross-sectional area on the opposite direction side (B) relative thereto, according to the flow distortion trend of the air passing through the interior of the intake duct body section (102), so as to equalize the flow speed distribution of air passing through the forward direction side (A) relative to the rotational direction of the rotating shaft and the flow speed distribution of air passing through the opposite direction side (B) relative thereto.

A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.

A compressor (2) characterized by being equipped with: a rotary shaft (12); multiple impellers attached to the rotary shaft; a main flow path that guides a fluid from the prior-stage impeller to the latter-stage impeller; a chamber (31) that forms a circle centered around the axial line and connects to the main flow path; a suction nozzle (32) that guides the fluid from the outer circumferential side toward the inner circumferential side in the chamber; multiple movable vanes provided in the main flow path at intervals in the circumferential direction of the axial line and capable of moving and thereby adjusting the flow volume of the fluid passing through the main flow path; and a drive mechanism (42) that is provided at one side in the circumferential direction of the suction nozzle (32) within the chamber (31), and that changes the angle of the multiple movable vanes. In addition, of the one side and the other side in the circumferential direction within the chamber (31), the suction nozzle (32) is inclined toward the other side so as to increase the flow volume of the fluid toward the other side.

A turbine wheel for low-pressure ratio applications is disclosed. The ratio of the outlet area of the wheel (A2) to the inlet area of the wheel (A1) is less than approximately 0.4. In an embodiment, the wheel is a radial or mixed-flow wheel.

An object is to provide a mixed flow turbine, wherein intermediate blades having an intermediate height are provided between main blades of the mixed flow turbine, thus improving an impulse blade turbine characteristic and reducing the moment of inertia for a rotor blade as a whole, thereby improving the efficiency and transient response. The mixed flow turbine includes: a turbine rotor blade 11; a turbine housing 3; a scroll partition wall 17 dividing a scroll chamber 13; a shroud-side inflow passageway 35 formed on the side of a shroud-side partition wall surface 25; and a hub-side inflow passageway 29 formed on the side of a hub-side partition wall surface 23, wherein the rotor blade 11 includes: main blades 37 formed with a height spanning the entire extent between a hub outer circumferential surface 31 and the inner periphery surface of a shroud portion 15; and intermediate blades 39 arranged in the circumferential direction between the main blades 37 and arranged so as to extend from the inlet portion of the main blades 37 to an intermediate portion and having an intermediate height with respect to the height of the main blades 37, wherein a fluid from the hub-side inflow passageway 29 flows in through front edges of the intermediate blades 39.

A process assembly includes an air mover assembly having a rotor assembly with rotor blades extending from a rotor hub and configured to cause an air flow to move over at least a portion of a process device to facilitate a process. The process device includes at least one of a heat exchanger or a direct air carbon capture device. The air mover assembly may be a wind turbine air mover assembly including a wind turbine rotor assembly. Each rotor blade may include a body structure defining root and airfoil sections extending along respective first and second span portions of the rotor blade. A ratio between the airfoil profile chord and the profile thickness and a twist angle between the airfoil profile chord and a root profile chord of the root section may vary along one or more portions of the second span portion.