The present invention provides a vertical, axial flow oil pump (10). The oil pump includes: a casing (11), the casing having a cylindrical shape as a whole and being able to rotate around its own central axis (O); a suction port (12), located at a lower end of the casing in an axial direction, and configured to suck oil into the oil pump; a discharge port (13), located at an upper end of the casing in the axial direction, and configured to discharge the oil from the oil pump to outside; and an impeller (14), provided in and formed integrally with the casing. The impeller rotates together with the casing when the casing rotates, so that the oil is flowed from the suction port to the discharge port. The present invention also provides a scroll compressor having the oil pump.

A turbopump includes: a main shaft rotatably supported; a pump section including an impeller attached to one end of the main shaft; and a turbine section including: a disk attached to the other end of the main shaft, rotor blades provided on an outer periphery of the disk, and nozzles provided inclined to an entrance plane of a blade cascade constituted of the rotor blades, the nozzles having axisymmetric cross sections and arranged in at least two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft.

A turbopump includes: a main shaft rotatably supported; a pump section including an impeller attached to one end of the main shaft; and a turbine section including: a disk attached to the other end of the main shaft, rotor blades provided on an outer periphery of the disk, and nozzles provided inclined to an entrance plane of a blade cascade constituted of the rotor blades, the nozzles having axisymmetric cross sections and arranged in at least two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft.

An electronically speed controlled pulsed supersonic turbine engine powering automotive, drone and electric power generation, energised by breathable, clean renewable energy airflow from 2700 psi integral air-tank energising the engine continuously for 3 hours, replacing the toxic fossil gasoline-diesel energised internal combustion engine with carbon emissions that affects climate change. The turbine blades are turning by pulsed impulse of supersonic airflow from sequentially energised eight manifolds of de Laval convergence-divergence-CD with sonic choking nozzle and supersonic divergence airflow impulsing turbine blades turning them within divergence shroud to atmospheric pressure with turbine nose with engine output shaft supported with bearings supported by the air-tank. An electric pulse generator controls engine shaft speed with voltage pulses to solenoid valves commanding spool valves with airflow from the air-tank with output shaft magnetic speed sensing signal sent back to controller in closed loop adjusting to desired set with pulse amplitude and time duration.

A machine train for producing nitric acid includes: a steam turbine having a steam turbine rotor rotating at a first rotational speed; a first compressor having a first compressor rotor rotating at a second rotational speed; a second compressor having a second compressor rotor rotating at a third rotational speed; and an expander having an expander rotor rotating at a fourth rotational speed. The steam turbine drives the first compressor. The rotor of the first compressor drives the second compressor. The expander drives the second compressor. The second compressor is configured and efficiency optimized with respect to its third rotational speed such that during operation of the machine train the first rotational speed of the steam turbine, the second rotational speed of the first compressor, the third rotational speed of the second compressor and the fourth rotational speed of the expander are equal,

A machine train for producing nitric acid includes: a steam turbine having a steam turbine rotor rotating at a first rotational speed; a first compressor having a first compressor rotor rotating at a second rotational speed; a second compressor having a second compressor rotor rotating at a third rotational speed; and an expander having an expander rotor rotating at a fourth rotational speed. The steam turbine drives the first compressor. The rotor of the first compressor drives the second compressor. The expander drives the second compressor. The second compressor is configured and efficiency optimized with respect to its third rotational speed such that during operation of the machine train the first rotational speed of the steam turbine, the second rotational speed of the first compressor, the third rotational speed of the second compressor and the fourth rotational speed of the expander are equal,

An object is to provide an axial flow turbine of radial-inflow type whereby it is possible to suppress a decrease in turbine efficiency due to tip leakage, and a turbocharger having the same. An axial flow turbine of radial-inflow type includes a housing having a scroll part for swirling working fluid flowing into the housing (40) along a circumferential direction of a rotation shaft and a bend part (52) for changing a flow direction of the working fluid flowing inwardly in the radial direction from the scroll part into a direction along the axial direction to direct the working fluid to turbine blades (30). The bend part includes a tip-side inner wall surface (60) of a bend shape at least in a region at an upstream side, in the axial direction, of a portion (36H) of a leading edge (36) of the turbine blades, the portion being adjacent to a hub. The bend shape of the tip-side inner wall surface along the axial direction has a minimum curvature radius R.sub.min at a position X.sub.Z near the turbine blades, and a curvature radius R (>R.sub.min) at the upstream side of the position X.sub.Z.

An object is to provide an axial flow turbine of radial-inflow type whereby it is possible to suppress a decrease in turbine efficiency due to tip leakage, and a turbocharger having the same. An axial flow turbine of radial-inflow type includes a housing having a scroll part for swirling working fluid flowing into the housing (40) along a circumferential direction of a rotation shaft and a bend part (52) for changing a flow direction of the working fluid flowing inwardly in the radial direction from the scroll part into a direction along the axial direction to direct the working fluid to turbine blades (30). The bend part includes a tip-side inner wall surface (60) of a bend shape at least in a region at an upstream side, in the axial direction, of a portion (36H) of a leading edge (36) of the turbine blades, the portion being adjacent to a hub. The bend shape of the tip-side inner wall surface along the axial direction has a minimum curvature radius R.sub.min at a position X.sub.Z near the turbine blades, and a curvature radius R (>R.sub.min) at the upstream side of the position X.sub.Z.

A weldment member for a gas turbine engine including a forward welding member and an aft welding member. The forward welding member has an annular shape with a forward welding face formed at one end. The forward welding face has a forward radiographic marking hole formed therein. The aft welding member has an annular shape with an aft welding face formed at one end. The aft welding face has an aft radiographic marking hole formed therein. The forward welding face is aligned with the aft welding face and the forward radiographic marking hole is angularly offset from the aft radiographic marking hole.

A weldment member for a gas turbine engine including a forward welding member and an aft welding member. The forward welding member has an annular shape with a forward welding face formed at one end. The forward welding face has a forward radiographic marking hole formed therein. The aft welding member has an annular shape with an aft welding face formed at one end. The aft welding face has an aft radiographic marking hole formed therein. The forward welding face is aligned with the aft welding face and the forward radiographic marking hole is angularly offset from the aft radiographic marking hole.