Mitsubishi Heavy Industries Limited

Jun Kubota

Koichi Akagi

Sunao Umemura

Yasuoki Tomita

Yoichi Iwasaki

Shunsuke Torii

Yasuhiro Ojiro

Koji Watanabe

Kiyoshi Suenaga

Satoshi Tanimura

Hiroyuki Aoki

Shigemi Mandai

Tatsuo Ishiguro

Masaki Ono

Masamitsu Kuwabara

Sunao Aoki

Yukihiro Hashimoto

Kouichi Akagi

Mitsuru Inada

Yoshichika Sato

Hisato Arimura

Hiroyuki Nishida

Akihiko Shirota

In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.

Cooling structure for a gas turbine

A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface. By the above construction, thermal stresses due to temperature differences between the blade and the platform during gas turbine stoppage are made smaller and occurrence of cracks is prevented.

Gas turbine moving blade

Gas turbine combustor by-pass valve device for opening and closing a by-pass valve is improved to uniformly control air supply into a combustion area for appropriate combustion. A drive shaft,for opening and closing a driven by-pass valve,is provided in turbine casing,where an outside obstruction is located which would interfere with a projecting drive shaft,. The driven shaft,has a short length to be provided in the turbine casing,. An adjacent main driving shaft,for opening and closing main driving by-pass valve,is provided adjacent to the driven shaft,. Link mechanism,is provided between the adjacent main driving shaft,and the driven shaft,so that rotary movement of adjacent main driving shaft,driven by outside drive means via the drive shaft,is transmitted to the driven shaft,and, thus, to the driven by-pass valve,. Thus, partial drive shafts,are made shorter so as not to project outside of the turbine casing,and interfere with outside obstruction, but all the by-pass valves,provided along circumferential direction of the turbine casing,can be operated to be opened and closed uniformly.

Gas turbine combustor by-pass valve device

Rotating machine seal device is improved so that seal plate is fitted to rotating portion firmly, thereby self-induced vibration of the seal plate is reduced and occurrence of abrasion or thinning of the seal plate due to the self-induced vibration and sealing deterioration accompanying therewith are prevented. In rotating machine seal device having seal plate (,) inserted into groove (,) provided in disc portion (,) driven rotationally, said seal device being for sealing fluid between fluid passage (,) on outer circumferential side of said groove (,) and fluid passage (,) on inner circumferential side of said groove (,), said seal plate (,) is divided into plural pieces along circumferential direction thereof to be inserted into said groove (,) of the disc portion (,) and spring plate (,) is disposed on inner circumferential side of said seal plate (,) so that said seal plate (,) is pressed against seal surface (,) of said groove (,) by spring force of said spring plate (,). Also, said seal plate is divided into plural pieces and one piece (,&prime;) has projection portion (,) and another piece (,) has groove portion (,) so that they are mated with each other to be inserted into said groove (,).

Seal apparatus for rotary machines

Gas turbine combustor by-pass valve device for opening and closing by-pass valve is improved to control uniformly air supply into combustion area for appropriate combustion. Drive shaft,for opening and closing driven by-pass valve,is provided in turbine casing,where outside obstruction is located to interfere with projecting drive shaft,The driven shaft,is made in short length to be provided in the turbine casing,Adjacent main driving shaft,for opening and closing main driving by-pass valve,is provided adjacently to the driven shaft,Link mechanism,is provided between the adjacent main driving shaft,and the driven shaft,thereby rotary movement of adjacent main driving shaft,driven by outside drive means via the drive shaft,is transmitted to the driven shaft,and thus to the driven by-pass valve,Thus, partial drive shafts,are made shorter not to project outside of the turbine casing,to interfere with outside obstruction and still all the by-pass valves,provided along circumferential direction of the turbine casing,can be operated to be opened and closed uniformly.

Gas turbine combustor tail tube cooling structure is improved so that temperature distribution along tail tube axial direction is made gentle and large thermal stress is prevented from occurring resulting in enhancement of safety and reliability of the combustor tail tube. Supply jacket (,) is disposed between upstream side discharge jacket (,) and downstream side discharge jacket (,). The upstream side discharge jacket (,) is disposed apart from tail tube inlet (,) at position close to by-pass passage (,) so as to form non-cooled zone (A) in the vicinity of the tail tube inlet (,). On the downstream side thereof, the supply jacket (,) is disposed at position in tail tube (,) contracting portion and near the downstream side discharge jacket (,) so as to shorten length of cooling pipes there.

Cooling structure for combustor tail pipes

In a pilot burner fuel nozzle for a premixed type combustor, diffusion pilot fuel injection ports (fuel holes 101) are disposed unevenly in the circumferential direction, whereby a nonuniform pilot flame is formed in the circumferential direction in the premixed type combustor. Thereupon, the heat is distributed in the axial direction, so that oscillated combustion does not occur, by which stable combustion can be maintained.

Pilot burner fuel nozzle with uneven fuel injection for premixed type

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Takasago, Japan

Jun Kubota