Mitsubishi Heavy Industries Limited

Kenichi Niu

Tatsuya Kimura

Takeshi Sano

Koichi Ishizaka

Shinji Fukao

Yuya Fukuda

Yoshihiro Kawamata

A centrifugal fluid machine includes an impeller () that has a front shroud () arranged on one side in an axial direction, a rear shroud () arranged on the other side in the axial direction, and a plurality of blades () provided side by side in a circumferential direction between the front shroud and the rear shroud and is rotatably supported within a casing (); a suction passage (A) that allows a fluid to be sucked therethrough in the axial direction toward the impeller with the rotation of the impeller; a discharge passage (B) that allows a fluid delivered under pressure by the impeller with the rotation of the impeller to be discharged in a direction intersecting the axial direction of the impeller; and a first flow path (A) that communicates with the discharge passage, leads to the suction passage through a gap between the casing and the rear shroud, and an opening (Aa) that opens toward the downstream side of the suction passage in a suction direction of a fluid. The opening area of the opening is set so that the ejection speed (Vs) of a fluid ejected from the opening to the suction passage is matched with the suction speed (V) of a fluid sucked into the suction passage.

Centrifugal fluid machine

A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

Rocket nozzle and control method for combustion gas flow in rocket engine

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Tokyo, Japan

Kenichi Niu