Mitsubishi Heavy Industries Limited

Masao Terazaki

Yasuoki Tomita

Eiji Akita

Hideyuki Satou

Yoshiyuki Kanezawa

Masaki Ono

Yukihiro Hashimoto

Masahito Kataoka

Masayuki Takahama

Hideki Murata

Kouji Watanabe

Hiroya Takaya

Hideto Horikawa

A compressor compresses air to produce compressed air. A mixture of fuel and the compressed air is combusted in a combustor to produce combustion gas. The combustion gas is supplied to a turbine to obtain rotational power. High-temperature gas accumulated in a space partitioned by an exhaust-side bearing portion that rotatably supports a turbine shaft and an exhaust diffuser is discharged through an exhaust gas passage. The high-temperature gas is sucked into the exhaust gas passage by exhaust gas flowing in the exhaust diffuser.

Gas turbine

A mounting structure for an air separator in a gas turbine includes an air separator and a rotor blade rotary disk. The air separator includes a cylindrical member with a flange at one end. The rotor blade rotary disk has on its outer face a disk recess portion forming an annular recess around the axial center of the rotor. A sealing face is formed on a contact face between a flange outer peripheral face that is provided on an outer periphery of the flange to be parallel to the axial center of the rotor and a disk recess inner peripheral face opposed to the flange outer peripheral face, that is provided on the disk recess portion and is parallel to the axial center of the rotor and formed around the axial center in an annular shape.

Mounting structure for air separator, and gas turbine

A plate springhaving a hook-shaped cross section from the lower part is installed in the neighborhood of one end 'b' of an impingement-cooling plate. One end 'c' on the lower side is fixed to a ribby welding, while the other end &#x201c;b&#x201d; on the upper side is free, which makes it closely contact with the neighborhood of the other end &#x201c;b&#x201d; of the impingement-cooling plateby the elastic force thereof. This state makes it possible to seal a gap formed between the impingement-cooling plateand a transition pieceon the side of a rib, preventing thermal stress generated in the rib, for example, from affecting the impingement-cooling plate

Cooling structure of gas turbine tail pipe

In a gas turbine having a plurality of moving blades provided on a rotary shaft in a circumferentially adjoining condition, a seal pin is provided in a spacing between the shanks of the adjacent moving blades for preventing leakage of cooling air from a blade root portion side to an airfoil side; an arcuately depressed portion is formed on the shank of each of the moving blades; and vibration of each of the moving blades is suppressed in such a manner that the seal pin serves as a spring system while the airfoil portion, the platform, the shank, and the blade root portion serve as a mass system.

Moving blade and gas turbine using the same

A gas turbine combustion apparatus has a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each combustor comprising a combustor inner tube and a combustor transition pipe, but lacks a turbine bypass mechanism for controlling the amount of compressed air discharged from a compressor into the turbine casing chamber. The combustion apparatus comprises an exhaust port member fitted into a manhole opening in the casing and communicating with the outside of the turbine casing chamber, bleeding pipes for uniformly bleeding compressed air discharged into the turbine casing chamber, a circular pipe for recovering compressed air bled by the bleeding pipes and discharging the compressed air to the exhaust port member, and an opening and closing valve for controlling the amount of exhaust which the circular pipe discharges to the outside of the turbine casing chamber via the exhaust port member, thereby possessing a turbine bypass mechanism.

Gas turbine combustion apparatus

The present invention provides a stationary blade of integrated segment construction, in which a thermal barrier coating can be applied to the whole blade surface and excessive stress can be avoided in a shroud. A plate seat connector is provided at each end face portion of an inside shroud and an outside shroud attached to outside and inside ends of gas turbine stationary blade. Several stationary blades are integrated by joining the plate seat connectors of the adjacent shrouds by means of bolts and nuts to provide a stationary blade of integrated segment construction.

Stationary blade of integrated segment construction and manufacturing method therefor

A mechanism for cooling the platform for the drive blades of a gas turbine uses a simple configuration which reliably cools the platform. The mechanism includes cooling channels in the interior of the platform which open out from one of the cooling air channels for cooling the turbine blades and which exit the platform through the edge nearest the tail. Cooling channels in the platform open out from the entrance to blade cooling channels, travel from the head of the blade along the blade sides, and exit through the edge near the tail of the blade. This structure diverts a portion of the cooling air entering the blade from the cooling channel in the base in order to cool the platform. Cooling air channels may extend from an enclosed air space below the platform to the upper surface of the platform at the front or rear side of the blade. Air channels may also extend on the rear of the turbine blade obliquely from the underside of the platform to the trailing edge of the platform. These channels or combinations thereof constitute a cooling structure through which air can flow to cool a platform for the drive blades of a gas turbine in an efficient and effective manner.

Growing community of inventors

Hyogo, Japan

Masao Terazaki