Mitsubishi Heavy Industries Limited

Kabushiki Kaisha Ricoh

Shikibo Ltd.

Mitsuru Kondo

Katsunori Tanaka

Satoshi Hada

Shigemi Mandai

Tatsuo Ishiguro

Masaki Ono

Tetsu Konishi

Kentaro Shindo

Yoshifumi Iwasaki

Kazuharu Hirokawa

Tadayuki Hanada

Ryotaro Magoshi

Koichi Ishizaka

Yukihiro Hashimoto

Akira Fukushima

Kouichi Akagi

Hirokazu Hagiwara

Nozomu Kawasetsu

Hiroshi Sakai

Mitsuo Hasegawa

Tetsuro Hirokawa

Masayasu Ishibashi

Toshihiko Misawa

Takeshi Tanamura

Hiroji Tada

Eigo Kato

Hironobu Hakoda

Hiroshi Shimizu

Osamu Morii

Tetsuya Iwamoto

Tomohiro Imae

Kunihiro Shimizu

Sousuke Nakamura

Takehiko Shimizu

Kazuo Nakajima

Tetsuya Ozawa

A toroidal pressure vessel having extremely high pressure resistance has laminated latitudinal reinforcing fiber layers to improve a strength in a latitudinal direction of the pressure vessel. Moreover, putting reinforcing fibers constituting those laminated latitudinal reinforcing fiber layers in continuity enables further improvement of strength in the latitudinal direction of the pressure vessel, for example compared with a case where the reinforcing fibers are divided for each layer.

Pressure vessel and method of manufacturing the same

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

An object of the present invention is to provide a gas turbine combustor with improved fatigue resistance of a combustor. It is possible to intentionally reduce a stiffness of each of flanges of upper and lower walls of an end portion (outlet) of the tail pipe of the gas turbine combustor. It is possible to reduce a stiff difference between the upper and lower walls of the end portion (outlet) of the tail pipe section and side walls. Thus, it is possible to reduce compulsion deformation caused due to thermal stress generated in the end portion (outlet) of the tail pipe section on the operation of the conventional gas turbine combustor, and to reduce high stress easy to generate in the side plate. As a result, the gas turbine combustor with high fatigue resistance can be realized.

Gas turbine combustor

A valve () for supplying the external air to the inside of an upper casing () is provided to the upper casing (), and when the operation of a gas turbine is stopped, the external air is introduced from the upper casing () to the inside of the casing (). When the external air is introduced from the upper casing (), the upper casing () is cooled to prevent thermal deformation of the casing ().

Casing and gas turbine

A rotary shaft axial elongation measuring method and device enable accurate measuring of rotary shaft axial elongation regardless of the amount of the elongation. Grooves ( ), arranged opposite to each other in a turned V shape along the axial direction, are provided in a rotational surface of the rotary shaft ( ) whose axial elongation is to be measured. A sensor ( ) is arranged opposite the rotational surface of the rotary shaft ( ). The sensor ( ) generates pulses upon passing of the groves ( ) following rotation of the rotary shaft ( ). As a circumferential interval between the grooves ( ) differs according to the axial directional position of the rotary shaft ( ), if the positions of the grooves ( ) at the position of the sensor ( ) change due to the axial elongation, the interval of the pulses generated by the sensor ( ) changes. Thus, by the change in the pulse generation interval, the axial elongation is measured.

Rotary shaft axial elongation measuring method and device

A gas turbine combustor transition piece outlet structure enabling a reduction in the temperature difference of a flange formed at the transition piece outlet. A flange is formed with a cooling medium channel along the inner circumference, cooling medium channels along the left and right side surfaces, and heating medium channels along the top and bottom surfaces. By cooling the inner circumference or the side surfaces of the flange by a cooling medium or heating the top and bottom surfaces of the flange by a heating medium, the temperature difference of the flange is reduced. Note that as the cooling medium, it is possible to use compressed air, low temperature steam, or fuel, while as the heating medium, it is possible to use high temperature steam or combustion gas.

Transition piece outlet structure enabling to reduce the temperature, and a transition piece, a combustor and a gas turbine providing the above output structure

The present invention provides a hollow structure with at least one flange which can eliminate the possibility of creating crackings due to the thermal fatigue, thereby improving the durability thereof. A hollow structure with an flange according to the present invention includes at least one annular flange fixedly attached around the hollow structure which has a temperature gradient in the direction of the thickness of the wall thereof, wherein said at least one annular flange including an outer portion formed of a metal material having a coefficient of linear expansion greater than that of the metal material forming another portion of said at least one annular flange.

Hollow structure with flange

A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets ( ) extend in the longitudinal direction of the tail tube of a gas turbine combustor along the entire circumference of the tail tube wall. The passage sectional area of the cooling jackets ( ) is varied depending on the metal temperature of parts of the tail tube ( ). For example, the passage sectional area of the cooling jackets ( ) formed at the rotor side wall and the mutually opposite side walls of the adjacent tail tube is larger than the passage sectional area of the cooling jackets ( ) formed at the casing side wall.

Cooling structure of a combustor tail tube

The transmitting and receiving sections are both energized, and the output of the transmitting section is connected to the input of the receiving section. The intensity of the transmitting section light source is varied, as by opening and closing a switch, and if the output of the receiving section is accurate in response to the light source variation, the transmitting and receiving sections are judged to be operating normally.

Internal test method for facsimile transceiver

Growing community of inventors

Takasago, Japan

Mitsuru Kondo