Ishikawajima-Harima Heavy Industries Co., Ltd.

Research Institute of Advanced Material Gas-Generator, Ltd.

Kaoru Chiba

Hideo Kobayashi

Katsuyoshi Takahashi

Ikuhisa Mizuta

Shigemichi Yamawaki

Motohide Murayama

Hidemi Toh

Shigeharu Ohyagi

A pulse detonation engine system () for driving a turbine is comprises a detonation generator section () including a detonation tube () having a tubular hollow section for permitting detonation to be generated therein during combustion stage of a mixture gas combined with a gas and a fuel, a gas supply section () for feeding the gas into the tubular hollow section of the detonation tube () at given time intervals, a fuel valve () for feeding the fuel into the tubular hollow section of the detonation tube () at the given time intervals, and an ignition plug () for igniting the mixture gas in the tubular hollow section of the detonation tube (), and a pulse detonation driven turbine () driven directly or indirectly by energy of detonations that are intermittently generated in the tubular hollow section of the detonation tube ().

Pulse detonation engine system for driving turbine

An axial flow compressor is disclosed. The axial flow compressor has a casing defining a compression passage therein. The casing has an inner surface and a center axis extending along the elongated direction of the casing. A plurality of rotor blades fixed to a disk rotate in the compression passage around the center axis. Each of the rotor blades has a tip, and the tip defines a rotation area having a width extending in the direction along the center axis. A circular concavity is formed on the inner surface of the casing extending completely around the inner surface. The circular concavity has a continuous curved shape in a sectional view, and the circular concavity is formed at a portion corresponding to a front part of the rotation area of the rotor blades.

Axial flow compressor

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Tokyo, Japan

Kaoru Chiba