A thermoacoustic electric generator system includes: a turbine including a turbine blade provided in an inside of a branched tube in a tube component and rotating by thermoacoustic oscillation of working gas in a thermoacoustic engine, and a turbine rotational shaft configured to be coupled to the turbine blade, penetrate a tube wall of the branched tube, and extend from the inside to an outside thereof; and a generator provided on the outside of the branched tube in the tube component, coupled to the turbine rotational shaft of the turbine, and converting rotational energy of the turbine blade to electric energy.

A steam turbine includes a rotating shaft (1); a rotor blade (4) having a platform (43) and a rotor blade main body (40); a casing (2); a stationary blade (7) having a stationary blade main body (70) and a stator shroud (71); and a projecting portion (45A) that projects from the platform (43) toward a upstream side in a central axis direction (Da). The projecting portion (45A) has, on a side thereof facing a radially inner side, a guide surface (45f) that gradually inclines or curves radially inward from a base end portion (45s) on the platform (43) side to a tip end portion (45t) on an upstream side in the central axis direction (Da).

A steam turbine includes a rotating shaft (1); a rotor blade (4) having a platform (43) and a rotor blade main body (40); a casing (2); a stationary blade (7) having a stationary blade main body (70) and a stator shroud (71); and a projecting portion (45A) that projects from the platform (43) toward a upstream side in a central axis direction (Da). The projecting portion (45A) has, on a side thereof facing a radially inner side, a guide surface (45f) that gradually inclines or curves radially inward from a base end portion (45s) on the platform (43) side to a tip end portion (45t) on an upstream side in the central axis direction (Da).

This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extension ring (160) coupled to the diaphragm and positioned adjacent to the tip shroud (152), and a tip balance slit (200).

This application provides controlled tip balance slits (200) for turbines. An example leakage flow control system (110) for a turbine may include a flow runner (150) with a tip shroud (152), a diaphragm or a guide blade (130), an extension ring (160) coupled to the diaphragm and positioned adjacent to the tip shroud (152), and a tip balance slit (200).

An internal combustion engine includes an exhaust gas passage, a water-cooled cylinder head and a turbocharger. The turbocharger includes: a compressor impeller; an axial flow turbine wheel coupled to the compressor impeller through a rotational shaft; a bearing that supports a portion of the rotational shaft located between the compressor impeller and the turbine wheel; and a housing that houses at least the compressor impeller and the bearing among the compressor impeller, the bearing and the turbine wheel. The turbine wheel is coupled to the rotational shaft such that the outlet of turbine blades of the turbine wheel is located on the side of the compressor impeller. The housing is fastened to the cylinder head, directly or with a first gasket interposed between the housing and the cylinder head, such that the turbine wheel is opposed to the cylinder head.

An internal combustion engine includes an exhaust gas passage, a water-cooled cylinder head and a turbocharger. The turbocharger includes: a compressor impeller; an axial flow turbine wheel coupled to the compressor impeller through a rotational shaft; a bearing that supports a portion of the rotational shaft located between the compressor impeller and the turbine wheel; and a housing that houses at least the compressor impeller and the bearing among the compressor impeller, the bearing and the turbine wheel. The turbine wheel is coupled to the rotational shaft such that the outlet of turbine blades of the turbine wheel is located on the side of the compressor impeller. The housing is fastened to the cylinder head, directly or with a first gasket interposed between the housing and the cylinder head, such that the turbine wheel is opposed to the cylinder head.

Disclosed is a turbine vane having an airfoil in a cross section including a leading edge, a trailing edge, and a pressure surface and a suction surface connecting the leading edge and the trailing edge, the airfoil extending radially from a platform part to an end wall, wherein the trailing edge of the airfoil is provided with a cutback cut in a direction radially perpendicular to both the pressure surface and the suction surface.

The combined radial-axial turboexpander (1) comprises a casing (3) and a shaft (5) arranged in the casing (3) for rotation therein. A radial impeller (25) and an axial expansion wheel (43) are mounted on the shaft (5). The axial expansion wheel (43) is arranged downstream of the radial impeller (25). A working fluid expands sequentially in the radial impeller and in the axial expansion wheel.

The combined radial-axial turboexpander (1) comprises a casing (3) and a shaft (5) arranged in the casing (3) for rotation therein. A radial impeller (25) and an axial expansion wheel (43) are mounted on the shaft (5). The axial expansion wheel (43) is arranged downstream of the radial impeller (25). A working fluid expands sequentially in the radial impeller and in the axial expansion wheel.