Mitsubishi Heavy Industries Limited

Yutaka Kawata

Shigemi Mandai

Katsunori Tanaka

Kuniaki Aoyama

Takashi Kawano

Satoshi Tanimura

Koichi Nishida

Eisaku Ito

Kazutaka Mori

Tanehiro Shinohara

Satoshi Takiguchi

Masaki Ono

Taiji Torigoe

Ikuo Okada

Masanori Yuri

Koji Takahashi

Koichi Ishizaka

Ichiro Nagano

Eiji Akita

Kouichi Akagi

Kazufumi Ikeda

Atsushi Maekawa

Yutaka Ozawa

Zenichi Yoshida

Masataka Ohta

Masaharu Nishimura

Nobuhiro Kunitake

Yoshiaki Tsukuda

Hisato Arimura

Takahiro Ohta

Katsumi Namba

Masahiko Toyoda

Keijirou Saitoh

Koji Takeshita

Soichiro Tomimoto

Akihiro Kawaguchi

Setunori Sakakibara

Hidehiko Nakane

Hidemi Niinai

There are provided a thermal barrier coating material and a thermal barrier coating member that can suppress spalling when used at a high temperature and have a high thermal barrier effect, a method for producing the same, a turbine member coated with a thermal barrier coating, and a gas turbine. The thermal barrier coating member comprises a heat resistant substrate, a bond coat layer formed thereon, and a ceramic layer formed further thereon, wherein the ceramic layer comprises an oxide which consists of an oxide represented by the general formula AZrOdoped with a predetermined amount of CaO or MgO and has 10 volume % or more of a pyrochlore type crystal structure, where A represents any of La, Nd, Sm, Gd, and Dy.

Thermal barrier coating member, method for producing the same, thermal barrier coating material, gas turbine, and sintered body

A premixed combustion burner for a gas turbine can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has a fuel nozzle, a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle, and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle. The swirler vanes gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vanes.

Premixed combustion burner for gas turbine

In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor () is provided with a first box body (), which is installed outside an object body () such as a combustor basket (), a transition piece () or a bypass duct () so as to form a first internal space () having a predetermined capacity; and a first throat () having a predetermined length which has one end () open to a side wall () of the object body () and has the other end () open to a first internal space (); wherein, a first resistive element () having a multiple number of through-holes is inserted and engaged to one end (). Fluid particles serving as vibration elements of combustion vibration caused in a combustion region are effectively trapped by the first resistive element () and at the same time resonate with the air of the first internal space () being connected through the first throat () and vibrate in the neighborhood of the first resistive element (), thereby damping vibration amplitude thereof.

Gas turbine combustor and a gas turbine equipped therewith

There is provided a combustor comprising a fuel nozzle which is comprised of a rodlike body which has a fuel passage and which is located in an air passage; a plurality of hollow members which are connected to the fuel passage and which extend in radial directions from the rodlike body into the air passage; at least one injection port formed in each hollow member to inject a fuel from the fuel passage into the air passage; and a projection which extends from a farmost inner wall of each hollow member that is most distant from an axis of the rodlike body to the injection port that is most distant from the axis. A hole for leaking fuel that is connected to an air passage may be formed in a farmost inner wall of the hollow member that is more distant from an axis of a rodlike body than the injection port that is most distant from the axis, or may be formed to be adjacent to all the injection ports on an upstream or downstream side in the direction of the airflow. Thus, a vortex does not occur in the hollow column.

Combustor containing fuel nozzle

A gas turbine combustor has homogenous air inflow by elimination of turbulence from the air, reducing combustion instability. A combustor has, at its center, a pilot nozzle and eight main nozzles around the pilot nozzle . The air flows in around the individual nozzles and to the leading end of the combustor so that it is used for combustion. An annular flow ring , having a semicirculat section, is disposed at the upstream end portion of a combustion cylinder , and a porous plate and a surrounding rib are disposed downstream of the flow ring . The air inflow is smoothly turned at first by the flow ring and then straightened by the porous plate so that the air flows without any disturbance around the individual nozzles and to the leading end, thereby reducing combustion instability.

Gas turbine and gas turbine combustor

A combustor can simultaneously reduce the amount of NOx exhaust and combustion oscillation. The combustor has an internal cylinder which accommodates a premixing nozzle and an external cylinder which accommodates the internal cylinder, and includes an air flow passage which supplies air from a compressor to the premixing nozzle. The air flow passage is provided with a punched metal plate near the maximum velocity fluctuation position whereat the velocity fluctuation of the air flow increases to a maximum.

Combustor, a gas turbine, and a jet engine

A gas turbine combustor improves the fuel distribution from a main fuel nozzle, suppressing fluctuations of internal pressure and elevation of inner tube metal temperature, and enhancing the combustion stability and durability of the combustor. The gas turbine combustor is a multi-nozzle type premixing combustor with a nozzle outer tube ( ) for forming and injecting a premixed gas of main fuel and combustion air divided and disposed in plural sections around a cone ( ) for forming a diffusion flame by reaction between pilot fuel and combustion air disposed in a center of a section of a combustor inner tube ( ). Nozzle holes ( ) of a main fuel nozzle ( ) are formed in three positions at equal intervals on the nozzle main body wall, and one of them is disposed at the outer periphery of the combustor inner tube ( ) on a diametral line linking between the center of the combustor inner tube ( ) and the center of the main fuel nozzle ( ), whereby the fuel distribution to the outer periphery is decreased.

Gas turbine fuel injector with unequal fuel distribution

A shaft seal having a high abrasion resistance is disclosed, by which the leakage of the gas from the high-pressure side to the low-pressure side can be reduced. In the shaft seal, flexible leaves are multi-layered to form a ring shape. The shaft seal is mainly arranged around the rotation shaft of a gas turbine or the like. The relevant turbine comprises a casing, a compressor, a rotation shaft, moving blades attached to the rotation shaft, and stationary blades attached to the casing in a manner such that the stationary blades face the moving blades, wherein the shaft seals are provided between a plurality of stationary blades and the rotation shaft wherein the leaves of each shaft seal contact the rotation shaft. Under the rated operating conditions, the top ends of the leaves slightly separate from the surface of the rotation shaft due to the dynamic pressure generated by the rotation of the rotation shaft. When the turbine is not operated, the top ends of the leaves contact the rotation shaft again due to the elastic restoring force of the leaves.

Shaft seal and turbine using the same

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Hyogo, Japan

Yutaka Kawata