Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Aircraft Corporation

Kohei Hatano

Hiroharu Oyama

Takumi Matsumura

Hidetaka Haraguchi

Motonari Machida

Hideaki Sugishita

Hidekazu Uehara

Yoshihiro Kuwamura

Keisuke Matsuyama

Katsuhisa Hamada

Toyoharu Nishikawa

Kohei Ozaki

Azumi Yoshida

Takahiro Ota

Yasuo Matsunami

Naoyuki Umezu

Shuhei Kuroki

Ken Ishii

Toshikazu Shigetomi

Masayoshi Suhara

Shuhei Muto

Hikaru Kurosaki

Toyosei Aota

Ryutaro Fujisawa

Keisuke Kamitani

Yoshimasa Tsumura

A pipe supporting structure includes: a plate-like member being into contact with an outside surface of a pipe; a tube-like member having a tubular shape and configured to support the plate-like member; and a base configured to support the tube-like member, wherein the plate-like member includes a supported portion supported by the tube-like member and an inner side portion surrounded by the supported portion, and the inner side portion has a smaller heat capacity per unit volume than the supported portion.

Pipe supporting structure

A seal device for a turbine is disposed around a rotor so as to separate a high-pressure space and a low-pressure space and includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor. Each of the thin plates has a thin-plate tip surface facing the outer peripheral surface of the rotor; a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces; and a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces. The first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate.

Seal device for turbine, turbine, and thin plate for seal device

A seal device for a turbine includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor, each of the thin plates including a root portion disposed on an outer side in a radial direction of the rotor and supported on a stationary part of the turbine and a tip portion disposed on an inner side in the radial direction of the rotor and having a tip surface facing the outer peripheral surface of the rotor. Each of the thin plates is configured such that a width direction of the thin plate is parallel to an axial direction of the rotor at a side of the root portion, and the tip portion of each of the thin plates is configured such that an end on a side of the high-pressure space is positioned downstream of another end on a side of the low-pressure side.

A pressure vessel for a turbine is disclosed. A cylindrical shape of the pressure vessel is divided into two parts in a radial direction of the pressure vessel and the pressure vessel is connected in the cylindrical shape via flanges protruding outward in the radial direction of the pressure vessel at both divided ends of the pressure vessel. Increased thickness portions are defined in a portion excluding the divided ends and circular arc center portions farthest from the divided ends. The portion is between the divided ends and the circular arc center portions and the increased thickness portions increase radial thickness of the portion.

Pressure vessel and turbine

A heating step, in which a stainless member is heated to a temperature within or above a heating phase-transformation temperature range (Ar) in which the stainless member is phase-transformed, is executed. A cooling step in which the stainless member heated in the heating step is cooled to a temperature below a cooling phase-transformation temperature range (Mr) in which the stainless member is phase-transformed, is executed. In the cooling step, cooling of the stainless member is suppressed in a control temperature range including the cooling phase-transformation temperature range (Mr).

Method for heat treatment of stainless member, and method for producing forged stainless product

To reduce a time required for repairing a honeycomb core sandwich panel. A repair method according to the present invention is a repair method, in which a repair patchis disposed on a repair target portion that exists on the side of a repair surfaceA of a honeycomb core sandwich panel, the honeycomb core sandwich panelbeing formed by sandwiching a honeycomb structured corewith a plurality of cells between skinsand, the method including: a heating step of heating the repair patch; and a cooling step of cooling the honeycomb core sandwich panelfrom the side of a second surfaceB opposing the repair surfaceA of the honeycomb core sandwich panel

Method and apparatus for repairing honeycomb core sandwich panel

A steam turbine vane manufacturing method including: a groove processing step for forming a protective part joint surface on a steam turbine vane material that has been subjected to rough processing; a build-up welding step for forming, by build-up welding, a protective part build-up bead on the protective part joint surface; and a processing step for performing processing, by cutting the first steam turbine vane material that has been subjected to rough processing and the protective part build-up bead, to finish the first steam turbine vane material has been subjected to rough processing so that the first steam turbine vane material becomes a second steam turbine vane material that has been subjected to finishing processing. The first steam turbine vane material that has been subjected to rough processing is larger than the second steam turbine vane material that has been subjected to finishing processing.

Steam turbine vane manufacturing method

A method of manufacturing a turbine blade, the method comprising forming a forging by forging stainless steel; heat treating the forging; and cooling the forging after the heat treatment; wherein in the heat treatment and the cooling, a plurality of the forgings are arranged in alignment, and adjacent forgings of the plurality of forgings are disposed so that at least respective portions of portions of the adjacent forgings corresponding to a region from a portion corresponding to a platform of a turbine blade to a center in a longitudinal direction of the turbine blade face each other and warm each other via radiant heat.

Turbine blade manufacturing method

A method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade (), the forging is hot-forged such that the distance (the excess thickness amount) from the blade surface of the blade section () to the surface of the excess thickness section is substantially uniform along the entire periphery of a cross section of the blade section () and the excess thickness section () perpendicular to the blade length direction, and such that the amount of the excess thickness in the blade length direction, which is the thickness of the excess thickness section (), gradually increases toward the blade tip from a prescribed position.

Method for manufacturing turbine rotor blade

Growing community of inventors

Tokyo, Japan

Kohei Hatano