Rocket-engine turbopump

A rocket-engine turbopump comprising:

• 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 and circular cross sections and arranged in two rows along a circumferential direction of the main shaft in a plane orthogonal to the main shaft, wherein outlets of the nozzles in one of the two rows and outlets of the nozzles in the other of the two rows are alternately positioned around the main shaft so that a phase shift between ejection areas of the nozzles in the one of the two rows and ejection areas of the nozzles in the other of the two rows in the entrance plane is within a range of an angle from ¼ to ¾ of a circumferential angle defined by each ejection area with respect to a center of the main shaft.