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: 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 load-lock apparatus includes a vessel arranged to change a pressure between a pressure corresponding to the vacuum chamber and the atmospheric pressure, a pressure adjusting mechanism which adjusts a pressure in the vessel to a pressure corresponding to the vacuum chamber and the atmospheric pressure, a cooling member having a cooling mechanism and arranged in the vessel to cool a substrate by having the substrate placed on or in proximity to the cooling member, a substrate deformation detection unit for detecting deformation of the substrate in the vessel, and a controller which reduces a cooling rate of the substrate when the substrate deformation is detected during a substrate cooling period until the vessel is adjusted to have the atmospheric pressure after the vessel is adjusted to have a pressure corresponding to the vacuum chamber and a high temperature substrate is loaded into the vessel from the vacuum chamber.

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.

Abstract: A steam-injection type gas turbine system provided with a waste-heat boiler uses surplus steam effectively for cooling the stationary blades of a turbine. The steam-injection type gas turbine system includes an air compressor (2) for compressing air, a combustor (3) for mixing a fuel with compressed air to burn the fuel, a turbine (4) driven by the energy of a combustion gas produced by the combustor (3), a waste-heat boiler (10) using an exhaust gas (G) discharged from the turbine (4) as a heat source, a steam supply system (23) for distributing steam generated by the waste-heat boiler (10) to the combustor (3), the stationary blades (68B) of the turbine (4) and external steam loads (22), and a steam distribution adjusting means (32) for preferentially supplying steam to the external steam loads (22), adjusting the rate of supply of steam to the combustor (3) and supplying the rest of the steam to the stationary blades (68B).

Abstract: To reduce the heating temperature and electric power consumption, maintain the quality of cloth and thoroughly dry the cloth, the cloth is heated and dried while it travels over a press roller, is wound round a surface roller through a pressure contact portion, is guided to a pressure contact portion between the surface roller and the other press roller, and travels round the other press roller.

Abstract: An indentation hardness tester determines positions of edge points of an indentation and calculates a hardness number from the length of diagonals of the indentation measured from the position of apexes of the indentation. The positions of apexes of the indentation are detected, for example, from intersection points of lines which approximate sides of the indentation. The indentation hardness tester may comprise a bright field/dark field switching part to obtain a clear image of the indentation.

Abstract: A method for ultrasonically detecting flaws in a welded portion of a pipe by using an ultrasonic wave phased array probe having an array of a plurality of transducer elements for emitting and receiving ultrasonic wave beams, wherein at least one monitoring probe is located in the vicinity of the welded portion to receive the ultrasonic wave beam, whereby peak values of the ultrasonic wave beams are detected within a predetermined gate, a maximum peak value of the detected peak values is determined to determine a pilot beam having the maximum peak value, and effective beams which reach the portion of the welding portion to be tested are determined from the determined pilot beam.

Abstract: A microwave and luminous probe which employs a coaxial cable in place of a waveguide. The coaxial cable includes a transparent insulator interposed between an inner conductor and an outer conductor. Accordingly, a microwave is propagated between the inner and outer conductors, while light is transmitted by the transparent insulator.

Abstract: A microwave and luminous probe for use in a system for detecting the piston position in an internal combustion engine and the light emitted in a combustion chamber thereof on the basis of a microwave signal and a luminous signal includes a hollow cylindrical case body fitted into the combustion chamber, internal and external conductors coaxially inserted within the case body and having different diameters from each other in the ratio of from 1:1.5 to 1:4, an annular passage defined by an annular space formed between the internal and external conductors and serving as microwave and light transmitting members, and a dipole antenna composed of a metal tube forming the internal conductor protruded from the annular passage in the range of from 1/8 to 3/8 of the wavelength of the microwave. The probe detects the light emitted by combustion in the combustion chamber with high accuracy.