Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Japan Tobacco Inc.

Koichi Akagi

Taku Ichiryu

Hideki Haruta

Jun Kubota

Sunao Umemura

Yasuoki Tomita

Hiroki Shibata

Shigemi Mandai

Shinji Akamatsu

Koichi Nishida

Yoichi Iwasaki

Kotaro Miyauchi

Rintaro Chikami

Masataka Ota

Yoshichika Sato

Yasuhiro Ojiro

Kazuya Kobayashi

Yoji Kochi

Katsunori Tanaka

Satoshi Hada

Masaki Ono

Sosuke Nakamura

Tetsu Konishi

Hitoshi Morimoto

Sunao Aoki

Yukihiro Hashimoto

Katsunori Akiyama

Tadao Yashiki

Shigenobu Kushihashi

Tomoka Tanaka

Masahito Kataoka

Tetsuo Ueno

Hiroshi Kanki

Masayuki Takahama

Tadakazu Sakaguchi

Yoshiyuki Kita

Naoki Hagi

Yasuhiro Hashimoto

Jun Yasuraoka

Hiroji Tada

Shuichi Kajiwara

Hidetoshi Iida

Miki Nishida

Junya Michinishi

There is provided a through-hole manufacturing method for a cylindrical body wall that enables the operation of forming a through-hole without leaving a machining burr on the wall of a cylindrical member to be easily and reliably carried out without depending on experts. A through-hole manufacturing method for a cylindrical body wall in which a machining burr is not formed on inner walls of through holes formed by a tool piercing the wall of a cylindrical body, the method including a hole forming step of forming one pair or a plurality of pairs of the through-holes in the cylindrical body wall by the tool piercing the cylindrical body from the outside orthogonally or substantially orthogonally to a cylindrical body axis of the cylindrical body; and a welding step of sealing the through-hole formed by the tool piercing the cylindrical body from the outer wall to the inner wall by welding using a welding jig made of a material having better heat conductivity than the cylindrical body, wherein the through-hole formed by the tool piercing the cylindrical body from the inner wall to the outer wall is left as a nozzle hole.

Through-hole manufacturing method for cylindrical body wall and cylindrical body structure

A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Transition piece of combustor, gas turbine having the same, and producing method for transition piece

A cigarette bundle feeder has a discharge duct which forms a lower part of a hopper and delivers filter cigarettes towards a bottom plate located under the hopper to produce a cigarette bundle, the discharge duct having a plurality of discharge passages arranged adjacent to each other in a width direction of the hopper to make the filter cigarettes flow downwards separately, the discharge passages opening in one direction; a front plate disposed at one side of and adjacent to the discharge duct, and extending in the width direction to cover the discharged passages of the discharge duct; and a plurality of suction holes formed in the front plate and having open ends that open towards the discharge duct, for sucking, through the open ends, tobacco shreds that spill from the cigarette ends of the filter cigarettes and drop into a gap between the front plate and the discharge duct.

Cigarette bundle feeder

An exhaust-side bearing rotatably supports a rotor of a turbine. A seal air-pipe and a first air-supply pipe supply compressed air extracted from a compressor of the turbine to the exhaust-side bearing. A second air-supply pipe supplies compressed air from a supplementary air-source to the exhaust-side bearing. A control apparatus switches between the first air-supply pipe and the second air-supply pipe based on the operation state of the gas turbine.

Control apparatus for gas turbine

In a central portion of inner tube,of combustor,pilot fuel nozzle,and pilot cone,are arranged and main fuel nozzles,and main swirlers,therearound. Air intake portion (X-,) is provided with rectifier tube,for making air intake uniform. In air intake portion (X-,), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube,In main swirler portion (X-,) and pilot cone portion (X-,), bolt joint of the main swirlers,is employed and optimized welded structure having less influence of thermal stress of the pilot swirler,is employed, respectively. Tail tube cooling portion (X-,) is provided with cooling structure having less influence of thermal stress to cool flange,portion of tail tube,uniformly. By the improvements in the portions (X-,) to (X-,), obstacles in attaining higher temperature in the combustor,is dissolved and combustor performance is enhanced.

Gas turbine combustor

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

A gas turbine steam cooled system has a high temperature portion,outlet steam temperature maintained to a predetermined value without a cooling steam pressure becoming lower than the pressure in the gas turbine cylinder. Steam coming from an intermediate pressure superheater,of a waste heat recovery boiler,is led into the high temperature portion,of the gas turbine for cooling thereof. The temperature of the cooling steam at the outlet of the high temperature portion,is detected by a high temperature portion outlet steam temperature detector,, and a signal thereof is sent a lower value selector,via a temperature controller,. Pressure in the gas turbine cylinder is detected by a gas turbine cylinder pressure detector,, and pressure of the cooling steam at the high temperature portion,outlet is detected by a high temperature portion outlet steam pressure detector,. A differential signal thereof is sent to a pressure controller,. Signals from the temperature controller,and the pressure controller,are inputted into the lower selector,, and temperature control valve,is controlled by the lower value thereof to be opened and closed.

Steam cooled system in combined cycle power plant

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

In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

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.

Sealing structure for first stage stator blade of gas turbine

Rotor for gas turbines

A gas turbine stationary blade unit in which two stationary blades are formed in a single segment by divided shrouds functions to lessen the occurrence of cracks. Two stationary blades 1a, 1b are fixed to an outer shroud and an inner shroud, respectively. Each shroud is divided into two sections 2a, 2b and 3a, 3b. Flanges 4a, 4b are provided to connect the section together by bolts via boltholes 7. Likewise, flanges 5a, 5b are provided to form a similar connection or joint. If the two stationary blades 1a, 1b are fixed in a single segment by the shrouds which are not divided, a restraining force becomes larger, local stress occurs due to thermal stress and the frequency of crack occurrence increases. However, since the shrouds are divided respectively into two parts and jointed together by bolts, the crack occurrence is lessened. Also, pinholes are provided in opposing faces at the divided portion of the shrouds. Also, pins are inserted into the pinholes for connection of the divided shrouds, thereby relative movement between the divided shrouds is prevented and a strong jointed blade unit is provided.

Gas turbine stationary blade unit

In order to realize a seal device of a gas turbine interstage portion which is excellent in a sealing ability during regular operation of the gas turbine, a gas turbine interstage portion seal device is constructed comprising a honeycomb seal (2) of a ring shape provided to an inner side of a turbine stationary blade inner ring (1) and a plurality of seal fins (5) of a ring shape provided to an outer side of a turbine disc seal arm portion (4). Also, an inner side surface of the honeycomb seal and outer peripheries of the plurality of seal fins, comprise large diameters and small diameters, and convex and concave portions formed thereby respectively are mated with each other.

Gas turbine interstage portion seal device

A vibration reducer for a diaphragm coupling is capable of suppressing axial vibrations as well as torsional vibrations. A diaphragm pack 3 is mounted between a diaphragm mount flange 2 provided on an intermediate shaft 1 serving as a drive shaft and a shaft flange 4 of another shaft serving as a driven shaft. An elastic arm 5 extends through the diaphragm pack 3 and is mounted to the diaphragm mount flange 2. The elastic arm 5 is a cylindrical member, whose circumferential portion is severed by slits formed by wire-cutting. Free ends 5a of the elastic arm 5 are expanded in the radial directions by centrifugal forces caused by rotation of a shafts and come into pressure-contact with the liner member 8 formed integrally within a cylindrical portion 7 of the shaft flange 4. A part of a torque is thereby transmitted via the pressure-contact portion, and rigidity in the axial direction of the elastic arm 5 is added to that of the diaphragm pack 3 to suppress vibrations. An alternative construction has a large pressure-contact force caused by centrifugal forces realized by making use of centrifugal weights 22, a centrifugal weight holder 23, and an elongated bolt 24.

Centrifugally operated axial and torsional vibration reducer for a

Growing community of inventors

Takasago, Japan

Koichi Akagi