Mitsubishi Heavy Industries Limited

Mitsubishi Chemical Corporation

Nippon Steel Sumitomo Metal Corporation

Nippon Steel Corporation

Sega Corporation

Mitsubishi Heavy Industries Marine Machinery & Equipment Co., Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Asahi Kasei Pharma Corporation

Mitsubishi Power, Ltd.

Olympus Medical Systems Corporation

Yasuhiro Wada

Shuji Yamamoto

Mitsuharu Yamagata

Hisao Urata

Yukihiro Iwasa

Yoshiyuki Tanaka

Keiichi Sato

Shohei Yoshida

Akinori Hayashi

Katsuhiro Fujita

Yoshihisa Ono

Shigeki Miura

Tetsuzou Ukai

Kazuki Abe

Hirokazu Takahashi

Makoto Takeuchi

Yasuyuki Watanabe

Kenji Uchida

Yoshihito Kobayashi

Seiji Nakano

Hiroshi Ogawa

Yoshitaka Hirata

Naoki Suzuki

Kentaro Hayashi

Keiichi Shiraishi

Takahide Itoh

Yoshihiro Tanabe

Toshifumi Sasao

Satoshi Kumagai

Hironaka Miyaki

Eitaro Takahashi

Taiyo Shirakawa

Akifumi Morimoto

Hiroaki Itagaki

Tetsuya Matsuo

Shohei Numata

Yasuharu Maruiwa

Takeo Saito

Tatsuya Hagita

Tetsuma Tatsumi

Hiroyuki Hosoya

Yoshihide Wadayama

Yuichiro Hirano

Hidetaka Nishimura

Yoshifumi Tanihara

Shota Igarashi

Fumito Hiratani

Keita Naito

Masayoshi Tagawa

Satoshi Makino

Noboru Okuyama

Kou Tanaka

Yasukazu Ogino

Yushi Ono

Naoto Fujiwara

Kei Yamanishi

Taisuke Iwanami

Seokcheol Kim

Tadaaki Kambara

Yusuke Yano

Provided is a bearing structure that can support a rotary shaft with a small number of components. The bearing structure includes: a cylindrical sleeve () provided so as to surround the outer circumference of a rotary shaft () that rotates about a center axis line (CL) and configured to rotate together with the rotary shaft (); thrust collars () provided so as to abut against both ends in the center axis line (CL) direction of the cylindrical sleeve (), respectively, having a larger diameter than the cylindrical sleeve (), and configured to rotate together with the rotary shaft (); and a compressor-side journal bearing () arranged on the outer circumference side of the cylindrical sleeve () and between the thrust collars ().

Bearing structure, turbocharger having the same, and assembly method of turbocharger

A transition piece includes a first flow passage group formed by arranging a plurality of intra-wall flow passages, a second flow passage group, and a plurality of dilution holes that penetrate a plate, and establish communication between a compressed air main flow passage and a combustion gas flow passage, each intra-wall flow passage of the first flow passage group and the second flow passage group having an inlet facing the compressed air main flow passage at an end portion on a side near the gas turbine, and having an outlet facing the combustion gas flow passage at an end portion on a side near the combustor liner, a dilution hole being located nearer to the inlet of an intra-wall flow passage of the second flow passage group than to the outlet of the intra-wall flow passage of the second flow passage group.

Transition piece, combustor, and gas turbine engine

Provided is a gas turbine combustor that can achieve improvement of the combustion stability. A gas turbine combustor includes a pilot burner of the diffusion combustion type, a pilot flow control valve that regulates a flow rate of fuel to be supplied to the pilot burner, a main burner of the premix combustion type arranged on an outer circumference side of the pilot burner, main flow control valves that regulate flow rates of fuel to be individually supplied to burner sectors into which the main burner is sectioned in a circumferential direction, and a controller configured to control the pilot flow control valve and the main flow control valves. The controller controls the main flow control valves such that, when fuel is to be supplied to all the burner sectors, a difference in fuel flow rate occurs between at least one burner sector and the other burner sectors among the burner sectors.

Gas turbine combustor having main fuel valves independently adjustable

A bearing device includes: a bearing housing; a floating metal having a cylindrical shape and disposed in a housing hole of the bearing housing and in which a rotational shaft is inserted; and a positioning pin for positioning the floating metal with respect to the bearing housing, the positioning pin being disposed along a radial direction of the rotational shaft. The positioning pin includes a first oil supply hole formed so as to penetrate the positioning pin and communicating with a first space between an inner peripheral surface of the floating metal and an outer peripheral surface of the rotational shaft, and a second oil supply hole formed inside the positioning pin so as to connect a second space to the first oil supply hole, the second space being disposed between an outer peripheral surface of the floating metal and an inner peripheral surface of the housing hole.

Bearing device and turbocharger

A press forming method includes a first process of obtaining a pressing force applied to each portion of a tool by an workpiece material during press forming while independently driving the respective each portion of the tool divided into multiple portions and press forming the workpiece material, and a second process of adjusting at least one of an applied driving force, an applied driving speed, and an applied driving timing for each portion of the tool to cause a processing portion of the workpiece material in which the state approaching an overload state is detected based on the pressing force to flow to other processing portions of the workpiece material.

Press forming method and tool for press forming

A gas turbine combustor is equipped with a transition piece assembly of the combustor, the transition piece assembly includes a transition piece, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the movement suppression mechanism and the aforementioned projection members fit together and thereby the aforementioned seal member is fixed to the frame.

Gas turbine combustor and transition piece assembly

A compression device includes a centrifugal compressor and a silencer. The centrifugal compressor includes a compressor assembly bolt fastening an inlet side of an inlet guide to a scroll casing. The silencer includes: a first side wall extending in a direction intersecting with a rotational axis of an impeller; an annular second side wall provided between the first side wall and the centrifugal compressor and surrounding the rotational axis; at least one silencer element provided in an ambient-air introduction space formed between the first side wall and the second side wall for guiding an ambient air to the inlet guide; and a silencer assembly bolt extending from the first side wall to the scroll casing in a direction along the rotational axis of the impeller and fastening the first side wall, the second side wall, and the scroll casing.

Compression device and supercharger

A flame produced within a premixer is promptly extinguished and a reduction in output power of a gas turbine associated with extinguishment is suppressed. In a gas turbine combustor including a diffusion burner and a premixed burner, the premixed burner is configured with a burner liner that surrounds the diffusion burner; a burner casing that surrounds the burner liner; a plurality of vanes that separate a cylindrical space between the burner liner and the burner casing into a plurality of premixers arranged side by side in a circumferential direction; a plurality of premixed fuel nozzles that inject a premixed fuel to the premixers; at least one thermometer installed to be buried in one of the vanes, and the like, and in a case in which a detection value of the thermometer exceeds a corresponding set value, an opening of each of premixed gas control valves is reduced and an opening of a diffusion gas control valve is increased in such a manner that a sum of flow rates of fuels supplied to the diffusion burner and the premixed burner remains unchanged.

Gas turbine combustor, gas turbine, and control method for gas turbine combustor

A method of manufacturing a mechanical part of the present invention includes a first process of forming, by performing a folding processing to an end portion of the material, a portion to be processed having a structure, in which a plurality of layers respectively having a thickness corresponding to a plate thickness of a material overlap each other, in the material such that a plate thickness direction of the layer is orthogonal to a plate thickness direction of the material; and a second process of changing, by performing a forging processing to the portion to be processed, a shape of the portion to be processed to a target shape while press-welding the layers of the portion to be processed to each other by plastic deformation.

Method of manufacturing mechanical part and mechanical part

A compressor-impeller fixing nut has a tubular shape, and includes: a curved-surface shaped portion disposed in a first range from a first end side in an axial direction, the curved-surface shaped portion having an outer diameter which increases toward a second end side in the axial direction and including an outer peripheral surface having a curved shape which protrudes outward in a radial direction in a cross section along the axial direction; and a nut portion disposed in a second range closer to the second end side from the first range in the axial direction, the nut portion having an outer peripheral surface with a nut shape. An expression (Dmax&#x2212;Dmin)/2&#x3c;L is satisfied, where L is a length of the first range in the axial direction, and Dmax is a maximum value and Dmin is a minimum value of the outer diameter of the curved-surface shaped portion in the first range.

Compressor-impeller fixing nut, impeller assembly, and supercharger

A fuel nozzle for gas turbine combustor of the present invention includes a diffusion combustion burner including a diffusion fuel nozzle, a premixing combustion burner including a premixing fuel nozzle, an end flange to which the diffusion combustion burner and the premixing combustion burner are mechanically joined, and a diffusion combustion burner support which fixes the diffusion combustion burner to the end flange and is mounted around the premixing fuel nozzle in a manner to cover a root portion of the premixing fuel nozzle, the root portion being a junction between the premixing fuel nozzle and the end flange. An outside diameter of the premixing fuel nozzle longitudinally varies in a manner to progressively increase toward the junction. A maximum diameter of the root portion of the premixing fuel nozzle is greater than an inside diameter of a hole formed in the diffusion combustion burner support.

Full nozzle for gas turbine combustor

A noise reduction structure includes a compressor discharge-side pipe portion, a first porous plate having a plurality of through holes and extending circumferentially along an inner circumferential surface of the compressor discharge-side pipe portion so that an air layer is formed between the first porous plate and the inner circumferential surface, a partition dividing an interior of the compressor discharge-side pipe portion in a radial direction in a circumferential direction of the compressor discharge-side pipe portion so as to form a plurality of flow paths in the compressor discharge-side pipe portion, and a second porous plate having a plurality of through holes. The second porous plate is provided in each of the plurality of flow paths and extends along the partition so that an air layer is formed between the second porous plate and the partition.

Noise reduction structure and supercharging device

A gas turbine combustor includes a plurality of fuel nozzles, a premixing plate, and a plurality of annular flow sleeves. The plurality of annular flow sleeves includes an inner annular flow sleeve and an outer annular flow sleeve. The plurality of annular flow sleeves is formed to divide an airflow passage into a plurality of flow passages including an inner and an outer circumferential flow passages. The airflow passage is formed around the plurality of fuel nozzles. The airflow passage extends from an upstream side of the plurality of fuel nozzles to fuel injecting ports of the fuel nozzles. The plurality of annular flow sleeves rectifies a flow of air in each of the flow passages and guiding the flow of air to the fuel injecting ports of the fuel nozzles.

Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages

While a compression part (B) in a bottom wall part of a cup-shaped workpiece (B) is compressed by an inner punch () and an inner die () and moved in a direction to get away from an intermediate die (), the inner die () is pushed toward the inner punch (); and a compression part (B) being an outer end portion in a radial direction of the workpiece (B) is compressed by an outer punch () and an outer die () and moved in an direction to approach the intermediate die (), to thereby suppress the workpiece (B) in the compression part (B) from material-flowing in a direction to get away from a central axis (), whereby thickness reduction processing of the compression part (B) and thickness increase processing of a vertical wall part (B) of the workpiece (B) sandwiched by an intermediate punch () and the inner die () and a vertical wall part (B) of the workpiece (B) sandwiched by the intermediate punch () and an outer die () are performed.

Press-forming method

Growing community of inventors

Tokyo, Japan

Yasuhiro Wada