Mitsubishi Heavy Industries Limited

Hiroji Tada

Yukihiro Hashimoto

Yasuoki Tomita

Tadayuki Hanada

Keizo Tsukagoshi

Koichi Akagi

Hirokazu Hagiwara

Ichiro Fukue

Mitsuru Kondo

Masahito Kataoka

Masahiko Mori

Osamu Morii

Kunihiro Shimizu

Tomohiro Imae

Jyunichiro Masada

To provide a bearing support structure and a gas turbine that prevent damage of device induced by a rotor shaft when the rotor shaft is unbalanced, the bearing support structure and the gas turbine includes: a casing () formed in a cylindrical shape; a bearing unit () formed in a cylindrical shape and housed in the casing (); a rotation shaft () rotatably supported by the bearing unit (); and a reaction-force decreasing unit () that connects the casing and the bearing unit, and is configured to decrease a radial reaction force on the bearing unit side.

Bearing support structure and gas turbine

A gas turbine stationary blade unit in which two stationary blades are formed in a single segment by divided shrouds functions to lessen the occurrence of cracks. Two stationary blades 1a, 1b are fixed to an outer shroud and an inner shroud, respectively. Each shroud is divided into two sections 2a, 2b and 3a, 3b. Flanges 4a, 4b are provided to connect the section together by bolts via boltholes 7. Likewise, flanges 5a, 5b are provided to form a similar connection or joint. If the two stationary blades 1a, 1b are fixed in a single segment by the shrouds which are not divided, a restraining force becomes larger, local stress occurs due to thermal stress and the frequency of crack occurrence increases. However, since the shrouds are divided respectively into two parts and jointed together by bolts, the crack occurrence is lessened. Also, pinholes are provided in opposing faces at the divided portion of the shrouds. Also, pins are inserted into the pinholes for connection of the divided shrouds, thereby relative movement between the divided shrouds is prevented and a strong jointed blade unit is provided.

Gas turbine stationary blade unit

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.

Gas turbine moving blade

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Takasago, Japan

Hiroji Tada