Mitsubishi Heavy Industries Limited

Mitsubishi Power, Ltd.

Ryuta Ito

Koichiro Iida

Shuji Tanigawa

Taro Tokutake

Yoshinori Wakita

Yoshifumi Tsuji

Satoshi Hada

Susumu Wakazono

Masaya Hatanaka

Hiroyuki Otomo

Takayuki Kurimura

Hiroshi Makigano

Yamato Shiramasa

Taku Hirayama

A method of manufacturing an additively manufactured object includes: checking, for an additively manufactured object including a plurality of internal passages, the presence or absence of a deposit in each inner wall surface of the plurality of internal passages; and selectively removing the deposit from the internal passage in which the deposit has been detected in the checking, among the plurality of internal passages.

Method of manufacturing additively manufactured object

A turbine blade includes a blade body, cooling passages extending in the blade height direction inside the blade body and connected to each other via folded portions, and a bypass portion that is provided in a partition wall portion partitioning a pair of adjacent cooling passages and that allows the pair of cooling passages to communicate with each other. The pair of cooling passages includes an upstream passage and a downstream passage. The turbine blade is provided with: a plurality of cooling holes formed in the blade body so as to be arranged along the blade height direction, that communicate with the downstream passage, and open in the surface of the blade body; a plurality of turbulators provided on the inner wall surface of the downstream passage and arranged along the blade height direction; or a thermal barrier coating that covers the surface of the blade body.

Turbine blade and gas turbine

A high-temperature component according to an embodiment is a high-temperature component which requires to be cooled by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; and a first partition wall disposed inside each of the cooling passages to partition the cooling passage into a plurality of first branch flow passages. The first partition wall includes an oblique portion formed such that, in an upstream side region of the first partition wall, a flow-passage cross-sectional area of the cooling passage as seen in an extension direction of the cooling passage gradually decreases from an upstream side toward a downstream side.

High-temperature component and method of producing the high-temperature component

A high-temperature component according to an embodiment is a high-temperature component which requires cooling by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; a header portion to which downstream ends of the plurality of first cooling passages are connected; and at least one outlet passage for discharging the cooling medium flowing into the header portion to outside of the header portion. A roughness of an inner wall surface of the at least one outlet passage is not greater than a roughness of an inner wall surface of the plurality of first cooling passages in a region where a flow-passage cross-sectional area of the outlet passage is the smallest.

A high-temperature component including a plurality of cooling passages through which the cooling medium can flow, a header connected to respective downstream ends of the plurality of cooling passages, and one or more outlet passages for discharging the cooling medium flowing into the header to outside of the header. The one or more outlet passages are less in number than the plurality of cooling passages. Respective minimum flow passage cross-sectional areas of the one or more outlet passages are not less than respective flow passage cross-sectional areas of the plurality of cooling passages in a connection between the header and the cooling passages. A sum of the respective minimum flow passage cross-sectional areas of the one or more outlet passages is less than a sum of the respective flow passage cross-sectional areas of the plurality of cooling passages in the connection between the header and the cooling passages.

High-temperature component, production method for high-temperature component, and flow rate control method

A ring-segment surface-side member is included in a ring segment disposed at a position opposite to a turbine blade on a stationary side of a gas turbine, serves as a part of a combustion gas flow path through which combustion gas flows, and is formed of a ceramic matrix composite. The ring-segment surface-side member includes: a surface portion forming the combustion gas flow path; a turned-back portion including a first part extending outward in a radial direction of the gas turbine from the surface portion and a second part extending toward a central line of the surface portion from an end part of the first part; and a protrusion portion extending outward from the turned-back portion in the radial direction of the gas turbine.

Ring-segment surface-side member, ring-segment support-side member, ring segment, stationary-side member unit, and method

A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up&#x3c;d_mid&#x3c;d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.

A turbine blade includes a blade body including a top plate at a tip portion which is outside of a turbine rotor in a radial direction of the turbine blade and has an outer surface configured to face an inner circumferential surface of a casing, and a tip thinning which protrudes radially outward in the radial direction of the turbine blade from the outer surface of the top plate and extends from a leading edge side of the blade body to a trailing edge side of the blade body. A protrusion amount of the tip thinning based on the outer surface of the top plate is 0.25 times or more and 2.00 times or less a diameter of a discharge port of a cooling hole which passes through the top plate.

A second outer surface () of a top plate () is recessed from a first outer surface () of the top plate () in the direction away from the inner peripheral surface () of a turbine casing () so that a step () is formed between the second outer surface () and the first outer surface (). At least part of the discharge opening (B) of a cooling hole () is disposed in the second outer surface (). The cooling hole () extends so as to be tilted relative to the second outer surface () so that the cooling hole () discharges a cooling medium to the upstream side of a combustion gas flowing between the second outer surface () and the inner peripheral surface () of the turbine casing ().

Turbine rotor blade and gas turbine

A turbine blade of the present invention includes a blade body mounted on a rotor body so as to extend outward from the rotor body in a radial direction of the rotor body and a chip shroud fixed to the outside of the blade body in the radial direction. A cooling passage which extends in the radial direction of the rotor body and in which a cooling medium circulates is formed in the blade body. The chip shroud includes a shroud body where a recess opened to the outside in the radial direction and communicating with the cooling passage is formed on an outer peripheral end face, and a plug that includes a plurality of plug pieces closing an opening of the recess in cooperation with each other by being inserted into mounting grooves formed on side surfaces of the recess.

Growing community of inventors

Tokyo, Japan

Ryuta Ito