Abstract: A combustor includes: a combustion liner having a combustion chamber formed therein; and a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide grooves that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

Abstract: A power generation system having a gas turbine engine that utilizes sunlight, includes a compressor configured to compress an air which is a working medium, a solar heater configured to heat the air compressed by the compressor, utilizing sunlight as a heat source, a hydrogen combustor configured to burn the air compressed by the compressor utilizing hydrogen as a fuel, a turbine configured to output a motive power from a high-temperature gas heated by at least one of the solar heater and the hydrogen combustor, a power generator configured to be driven by the turbine, and at least one hydrogen-generating unit configured to generate hydrogen by utilizing an output of the turbine or exhaust heat from the turbine to decompose a water, and supply the hydrogen so generated to the hydrogen combustor.

Abstract: In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.

Abstract: A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.

Abstract: A combustor includes: a combustion liner having a combustion chamber formed therein; and a fuel injector mounted to a top portion of the combustion liner, and including a fuel injection member having a plurality of fuel injection annular portions and an air guide member including a plurality of combustion air annular portions that guide air for combustion. The fuel injection annular portions and the combustion air annular portions are arranged concentrically and alternately. The fuel injector injects fuel and air into the combustion chamber. Each of the fuel injection annular portions includes a plurality of fuel injection holes that are open in a radial direction thereof, and each of the combustion air annular portions includes a plurality of air guide grooves that are open in an axial direction thereof, and guide the air to the fuel jetted from the fuel injection holes.

Abstract: Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.

Abstract: A combined-type gas turbine engine system is provided which achieves high efficiency by very effectively using exhaust heat from a gas turbine engine. In a gas turbine engine system including: a compressor for compressing a first working medium; a heater for heating the compressed first working medium by an external heat source; a turbine for outputting power from the first working medium; an intermediate cooler provided at the compressor for cooling the first working medium compressed by a low-pressure compression part of the compressor and supplying the first working medium to a high-pressure compression part of the compressor; and an exhaust heat boiler using as a heating medium an exhaust gas from the turbine, a Rankine cycle engine using the intermediate cooler and the exhaust heat boiler as heat sources and a cooling medium of the intermediate cooler as a second working medium.

Abstract: In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.

Abstract: A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.

Abstract: A power generation system having a gas turbine engine that utilizes sunlight, includes a compressor configured to compress an air which is a working medium, a solar heater configured to heat the air compressed by the compressor, utilizing sunlight as a heat source, a hydrogen combustor configured to burn the air compressed by the compressor utilizing hydrogen as a fuel, a turbine configured to output a motive power from a high-temperature gas heated by at least one of the solar heater and the hydrogen combustor, a power generator configured to be driven by the turbine, and at least one hydrogen-generating unit configured to generate hydrogen by utilizing an output of the turbine or exhaust heat from the turbine to decompose a water, and supply the hydrogen so generated to the hydrogen combustor.

Abstract: A gas turbine engine system is provided which achieves high efficiency while using sunlight as a heat source. In a gas turbine engine system including: a compressor configured to compress a first working medium; a heater configured to heat the compressed first working medium by an external heat source; a turbine configured to output power from the first working medium; and an intermediate cooler provided at the compressor and configured to cool the first working medium compressed by a low-pressure compression part of the compressor and supply the first working medium to a high-pressure compression part of the compressor, an organic Rankine cycle engine using, as a second working medium, an organic substance which is a cooling medium of the intermediate cooler is provided.

Abstract: A combined-type gas turbine engine system is provided which achieves high efficiency by very effectively using exhaust heat from a gas turbine engine. In a gas turbine engine system including: a compressor for compressing a first working medium; a heater for heating the compressed first working medium by an external heat source; a turbine for outputting power from the first working medium; an intermediate cooler provided at the compressor for cooling the first working medium compressed by a low-pressure compression part of the compressor and supplying the first working medium to a high-pressure compression part of the compressor; and an exhaust heat boiler using as a heating medium an exhaust gas from the turbine, a Rankine cycle engine using the intermediate cooler and the exhaust heat boiler as heat sources and a cooling medium of the intermediate cooler as a second working medium.

Abstract: Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.

Abstract: A film cooling structure includes a wall surface which faces a gas-flow passage for high-temperature gas. One or more than one pair of jetting holes are formed on the wall surface so as to respectively jet cooling media into the gas-flow passage. The pair of jetting holes respectively have jetting directions in which the cooling media are jetted from the pair of jetting holes into the gas-flow passage. The jetting directions of the pair of jetting holes are respectively set so as to respectively form swirls in directions in which the cooling media are mutually pressed against the wall surface.

Abstract: A film cooling structure includes a wall surface which faces a gas-flow passage for high-temperature gas. One or more than one pair of jetting holes are formed on the wall surface so as to respectively jet cooling media into the gas-flow passage. The pair of jetting holes respectively have jetting directions in which the cooling media are jetted from the pair of jetting holes into the gas-flow passage. The jetting directions of the pair of jetting holes are respectively set so as to respectively form swirls in directions in which the cooling media are mutually pressed against the wall surface.