Kawasaki Jukogyo Kabushiki Kaisha

B&b Agema Gmbh

Takao Sugimoto

Karsten Kusterer

Ryozo Tanaka

Dieter Bohn

Masahide Kazari

Kazuhiko Tanimura

Tomoki Taniguchi

Gang Lin

Nurettin Tekin

Anas Elyas

Hiroshi Morishita

Rene Braun

Takeshi Horiuchi

Koichiro Tsuji

Koji Sambonsugi

Masamoto Tazaki

Koichiro 3312 Kawajyu-Kusugaoka-Seiun-Ryo Tsuji

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.

Sunlight-utilizing gas turbine power generation system provided with hydrogen-generating unit

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.

Turbine blade cooling structure

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.

Double-jet film cooling structure and method for manufacturing same

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.

Double-jet type film cooling structure

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.

Gas turbine engine system equipped with Rankine cycle engine

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.

Double jet film cooling structure

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 ( ) for compressing air, a combustor ( ) for mixing a fuel with compressed air to burn the fuel, a turbine ( ) driven by the energy of a combustion gas produced by the combustor ( ), a waste-heat boiler ( ) using an exhaust gas (G) discharged from the turbine ( ) as a heat source, a steam supply system ( ) for distributing steam generated by the waste-heat boiler ( ) to the combustor ( ), the stationary blades ( B) of the turbine ( ) and external steam loads ( ), and a steam distribution adjusting means ( ) for preferentially supplying steam to the external steam loads ( ), adjusting the rate of supply of steam to the combustor ( ) and supplying the rest of the steam to the stationary blades ( B).

Steam-injection type gas turbine

A coupling device for transmitting rotational torque in only one direction from a drive member to a driven member has first and second flange members and an elastic circular compression member. The compression member has projections on the periphery which are grabbed by claws on the flange members. There are several pairs of claws, one claw of each pair being attached to the first flange and the other claw being attached to the second flange. The first and second flanges are connected to the drive and driven members, respectively. As the drive member rotates in its only rotating direction, torque is transmitted between the paired claws via the elastic projections between the paired claws. The elastic member also has smaller projections which extend between the claws of adjacent pairs and are therefor free of compression during rotation.

Growing community of inventors

Kobe, Japan

Takao Sugimoto