Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Ichiro Fukue

Yasuoki Tomita

Eiji Akita

Kiyoshi Suenaga

Hideaki Sugishita

Shigemi Mandai

Kazuo Uematsu

Hidetaka Mori

Satoshi Tanimura

Tetsuo Gora

Koji Watanabe

Katsunori Tanaka

Shinji Akamatsu

Koichi Nishida

Keizo Tsukagoshi

Yukihiro Hashimoto

Hideki Haruta

Masataka Ota

Hiroyuki Nishida

Hiroji Tada

Hitoshi Kawabata

Teruya Tachibana

Nobuo Sato

Masahiko Mori

Tomohisa Takasaki

Nobuo Satoh

Jyunichiro Masada

Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor and led into combustor A mixture of H and CO as fuel added with O is burned to generate high temperature gas, which works at high temperature turbine flows through heat exchangers and returns partly to the compressor and enters partly low pressure turbine of bottoming system to work. Condensed water from condenser of the bottoming system is pressurized by pressure pump and flows through the heat exchangers to become high temperature steam and to work at high pressure turbine Exhaust gas thereof is mixed into the combustor A mixture of methanol and water is supplied into reformer to absorb heat from the heat exchanger to be reformed into H and CO , which is supplied into the combustor A high temperature portion of the high temperature turbine is cooled by cooling medium extracted from compressor outlet and high pressure turbine outlet thereby reliability of the high temperature turbine is enhanced.

Combined cycle power plant

Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor and led into combustor . A mixture of H and CO as fuel added with O is burned to generate high temperature gas, which works in high temperature turbine , flows through heat exchangers and returns partly to the compressor and enters partly low pressure turbine of a bottoming system to work. Condensed water from condenser of the bottoming system is pressurized by pressure pump and flows through the heat exchangers to become high temperature steam and to work in high pressure turbine . Exhaust gas thereof is mixed into the combustor . A mixture of methanol and water is supplied into reformer to absorb heat from the heat exchanger to be reformed into H and CO , which is supplied into the combustor . A high temperature portion of the high temperature turbine is cooled by cooling medium extracted from the compressor outlet and high pressure turbine outlet thereby reliability of the high temperature turbine is enhanced.

Provided is turbine plant using methanol as fuel in which working fluid is compressed by compressor,and led into combustor,. A mixture of H,and CO,as fuel added with O,is burned to generate high temperature gas, which works at high temperature turbine,, flows through heat exchangers,and returns partly to the compressor,and enters partly low pressure turbine,of bottoming system to work. Condensed water from condenser,of the bottoming system is pressurized by pressure pump,and flows through the heat exchangers,to become high temperature steam and to work at high pressure turbine,. Exhaust gas thereof is mixed into the combustor,. A mixture of methanol and water is supplied into reformer,to absorb heat from the heat exchanger,to be reformed into H,and CO,, which is supplied into the combustor,. A high temperature portion of the high temperature turbine,is cooled by cooling medium extracted from compressor,outlet and high pressure turbine,outlet thereby reliability of the high temperature turbine,is enhanced.

Combined cycle power plant with fuel reformer

Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (,) being stopped, water purge system (,) having stop valve (,) supplies water into fuel system including liquid fuel system (,) and fuel nozzle (,) and liquid fuel remaining therein is purged by water into combustion chamber (,) from the fuel nozzle (,).

Gas turbine combustion system and combustor ignition method therefor

A gas turbine moving blade platform having a simplified cooling structure for effecting uniform cooling of the platform. The platform (,) includes cavities (,) and an impingement plate (,) provided below the cavities (,). A cooling hole (,) communicates with cavity (,), cooling hole (,) communicated with cavity (,) and cooling holes (,) communicate with cavity (,) and all of the cooling holes pass through the platform (,) at an inclined angle. Cooling air (,) flows into the cavities (,) through holes (,) in the impingement plate (,) for effecting impingement cooling of platform (,) plane portion. The cooling air (,) further flows through the cooling holes (,) to blow outside angularly upward for cooling peripheral portions of the platform. Thus, the platform is cooled uniformly, no lengthy and complicated cooling passage is provided, and workability is enhanced.

Gas turbine moving blade platform

A gas turbine moving blade platform having a simplified platform cooling structure. A cooling effect of the platform side end portions is increased resulting in uniform cooling of the entire platform. Cooling passages (,) are bored in the platform (,) front portion so as to communicate with a cooling air passage (,) of the moving blade (,) and open at both platform side end surfaces. The openings are closed by inserting covers (,) therein. Cooling passages (,) are bored in platform (,) side end portions so as to communicate with the front end cooling passages (,), respectively, and open in the platform rear end surface. A plurality of cooling holes (,) are bored so as to communicate with the cooling passage (,) and open at the platform side end surface. Thus, the entire platform is cooled uniformly and the platform side portions are cooled by the cooling holes (,) so that an effective cooling performance is ensured and also the workability of the cooling lines is enhanced.

In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade is enhanced. An inner cavity 10 is formed in the blade over the entire length thereof. A multiplicity of pin fins 5 are provided in the inner cavity, being fixed to wall thereof. An enlarged cavity 6 is formed in the shroud 2 of a terminal end of the blade 1. Cooling air entering the inner cavity 10 of the blade 1 flows into the enlarged cavity 6 and flows out of the shroud 2 downwardly through holes 7 of a peripheral portion of the enlarged cavity 6. The entire portion of the shroud 2 is cooled uniformly, and the cooling effect of the entire blade is enhanced by an enhanced heat transfer rate in the blade and by uniform cooling of the entire shroud.

Gas turbine moving blade

A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and is constructed such that the cooling gas can flow in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade.

Gas turbine rotor blade

A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air is supplied to the casing, allowed to pass through moving blades, and removed to the outside of casing after cooling the moving blades; a cooler for cooling the cooling gas in the first and second closed circuits; and a booster for pressurizing and circulating the cooling gas cooled by the cooler. Also, A gas turbine comprises: a first closed circuit in which cooling air cooled after being extracted from a combustor plenum is allowed to pass through stationary blades successively to cool the stationary blades, and then recovered and returned to a compressor on the upstream side of the combustor plenum; and a second closed circuit in which cooling air cooled after being extracted from the combustor plenum is allowed to pass through moving blades successively to cool the moving blades, and then recovered and returned to the compressor.

System for cooling blades in a gas turbine

A movable gas turbine blade includes a platform (10) which is provided with a groove (15). The groove is located on a blade trailing side of the platform. Also, the groove is rounded and has a depth which does not enter a stress line of the platform caused by a load on the blade. The groove functions to suppress a high thermal stress arising at a connection portion of a blade trailing edge and the platform of the gas turbine air cooled moving blade during unsteady (start and stop) operation of the turbine.

A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.

Combustor for gas turbines with diverging pilot nozzle cone

A burner apparatus which comprises a pilot burner including a nozzle and swirlers disposed around the nozzle, and a plurality of main burners which are arranged around the pilot burner and each of which comprises a nozzle and swirlers disposed around the nozzle; and the angle of the swirlers for the pilot burner is set larger than the angle of the swirlers for the main burner so that the angles of the two types of swirlers cross. NOx production can be considerably reduced with a very simple structure based on the present invention for combustion in boilers and gas turbines.

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Takasago, Japan

Ichiro Fukue