Abstract: A pulse detonation engine system (1) for driving a turbine is comprises a detonation generator section (5) including a detonation tube (7) 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 (17) for feeding the gas into the tubular hollow section of the detonation tube (7) at given time intervals, a fuel valve (19) for feeding the fuel into the tubular hollow section of the detonation tube (7) at the given time intervals, and an ignition plug (15) for igniting the mixture gas in the tubular hollow section of the detonation tube (7), and a pulse detonation driven turbine (9) driven directly or indirectly by energy of detonations that are intermittently generated in the tubular hollow section of the detonation tube (7).

Abstract: A gas turbine engine includes a front cooling plate provided on a front stationary section in the vicinity of a front side of a turbine disc, a front cooling passage formed between an opposing surface of the front cooling plate and a front surface of a rim of the turbine disc, a rear cooling plate provided on a rear stationary section in the vicinity of a rear side of the turbine disc, and a rear cooling passage formed between an opposing surface of the rear cooling plate and a rear surface of the rim of the turbine disc.

Abstract: A pulse detonation engine system (1) for driving a turbine is comprises a detonation generator section (5) including a detonation tube (7) 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 (17) for feeding the gas into the tubular hollow section of the detonation tube (7) at given time intervals, a fuel valve (19) for feeding the fuel into the tubular hollow section of the detonation tube (7) at the given time intervals, and an ignition plug (15) for igniting the mixture gas in the tubular hollow section of the detonation tube (7), and a pulse detonation driven turbine (9) driven directly or indirectly by energy of detonations that are intermittently generated in the tubular hollow section of the detonation tube (7).

Abstract: A blade 10 is composed of a front blade portion 10a, a rear blade portion 10b and a middle blade portion 10c. The belly side of the middle blade portion 10c forms a recess towards the back side. High-temperature gas flowing along the belly side of the blade 10 branches once at the front edge portion to the rear edge portion and alongside the belly side, into separate flows. These separated high-temperature gas flows are merged again at the rear edge portion, thereby a separation region S is formed.

Abstract: A gas turbine engine includes a front cooling plate (85) provided on a front stationary section (69) in the vicinity of a front side of a turbine disc (55), a front cooling passage (87) formed between an opposing surface of the front cooling plate (85) and a front surface of a rim of the turbine disc (55), a rear cooling plate (93) provided on a rear stationary section (81) in the vicinity of a rear side of the turbine disc (55), and a rear cooling passage (95) formed between an opposing surface of the rear cooling plate (93) and a rear surface of the rim of the turbine disc (55).

Abstract: A blade 10 is composed of a front blade portion 10a, a rear blade portion 10b and a middle blade portion 10c. The belly side of the middle blade portion 10c forms a recess towards the back side. High-temperature gas flowing along the belly side of the blade 10 branches once at the front edge portion to the rear edge portion and alongside the belly side, into separate flows. These separated high-temperature gas flows are merged again at the rear edge portion, thereby a separation region S is formed.