Abstract: To provide a ceramic heat exchanger which has reduced joints, and thus, is easy to produce and less likely to leak and a method of producing same. The ceramic heat exchanger 1 according to the present invention comprises a body 2 having first channels 21 for a high-temperature medium to flow and second channels 22 for a low-temperature medium to flow, and lids 3 each having openings 31, joined to the body 2 at opposite ends 2a, 2b with the openings 31 connected to the first channels 21, the body 2 further having inlet channels 23 formed in a first channel 21 outlet-side end portion 2a to allow the low-temperature medium to enter the body at a side thereof and flow into the second channels 22, and outlet channels 24 formed in a first channel 21 inlet-side end portion 2b to allow the low-temperature medium to flow out of the second channels 22 and leave the body at the side thereof.

Abstract: A gas turbine combustor includes inner and outer liners that are concentric and cylindrical, and an end liner closing between upstream ends thereof and forming a hollow cylindrical combustion chamber therein, and a swirling air flow forming device introducing combustion air about the end liner from outside and forming a swirling air flow, a fuel ejector ejecting fuel in the swirling direction to form a premixed swirling flow, and an igniter igniting the premixed swirling flow to form a tubular flame surface. The combustion chamber includes a primary combustion chamber, a secondary combustion chamber disposed downstream of the primary combustion chamber, and an annular restrictor reducing the outer diameter of the primary combustion chamber and disposed therebetween. A diluting air hole, supplying diluting air along a flow of the combustion gas passing through the restrictor, is disposed downstream of the restrictor in the inner liner.

Abstract: To provide a ceramic heat exchanger which has reduced joints, and thus, is easy to produce and less likely to leak and a method of producing same. The ceramic heat exchanger 1 according to the present invention comprises a body 2 having first channels 21 for a high-temperature medium to flow and second channels 22 for a low-temperature medium to flow, and lids 3 each having openings 31, joined to the body 2 at opposite ends 2a, 2b with the openings 31 connected to the first channels 21, the body 2 further having inlet channels 23 formed in a first channel 21 outlet-side end portion 2a to allow the low-temperature medium to enter the body at a side thereof and flow into the second channels 22, and outlet channels 24 formed in a first channel 21 inlet-side end portion 2b to allow the low-temperature medium to flow out of the second channels 22 and leave the body at the side thereof.

Abstract: A gas turbine combustor is provided which can accomplish stable high-load combustion, high combustion efficiency, a low concentration of CO, and NOx in a small-sized combustion chamber. The gas turbine combustor includes an inner liner 12 and an outer liner 14 being concentric and cylindrical and an end liner 16 closing between upstream ends thereof and forms a hollow cylindrical combustion chamber 18 therein. The gas turbine combustor further includes a swirling air flow forming device 22 introducing combustion air 7a into the vicinity of the end liner in the combustion chamber 18 from the outside and forming a swirling air flow, a fuel ejector 24 ejecting fuel 8 in the swirling direction to form a premixed swirling flow, and an igniter 26 igniting the premixed swirling flow to form a tubular flame surface 11.

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 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).