Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Other

Mitsubishi Yukogyo

Mitsubishi Hitachi Power Systems, Ltd.

Taku Ichiryu

Yasuoki Tomita

Tadao Yashiki

Tsuneyoshi Mitsuhashi

Masanori Kobayashi

Kiyoshi Suenaga

Koichi Akagi

Kazuzo Katayama

Yasushi Mori

Yasushi Mouri

Satoshi Hada

Hiroki Shibata

Ryotaro Magoshi

Kouichi Akagi

Hideaki Nishida

Shoki Yamashita

Hideyuki Toda

Hiroshi Kanki

Takeshi Yoshimi

Tadakazu Sakaguchi

Naoki Hagi

Takaaki Matsuo

Kazuso Katayama

Jack Samuel Lavender

Naoyuki Seki

Kazuhiro Matsui

Masahito Kataoka

Yasushi Fukuizumi

Miki Nishida

Hiroyasu Ochiai

Naoyuki Mitsubishi Heavy Ind Ltd Seki

Taku Mitsubishi Heavy Ind Ltd Ichiryu

The present invention aims at providing a technique for providing a stepped structure separately to a rotating shaft in a later step of assembly for preventing oil leakage from a bearing box. To this end, the rotating machine of the present invention includes a rotating shaft having a rotating member, a bearing device including a rotating shaft insertion hole larger in diameter than the rotating shaft, an oil thrower provided between an outer circumferential portion of the rotating shaft insertion hole and the rotating shaft, and an additional ring attached to the rotating shaft between the oil thrower and the rotating shaft such as to protrude in a radial direction of the rotating shaft.

Rotating machine and additional ring

A hydraulic detachable coupling, which can transmit rated torque in a manner stable to vibrations, and can fully withstand abnormal torque. For this purpose, in a hydraulic detachable coupling () mounted detachably on a rotor () of a steam or gas turbine or other machine, a coupling sleeve (), which is fitted on a shaft end portion of a casing penetrating shaft () in the rotor (), includes a taper hole portion (-) which is interference-fitted on a taper shaft portion () of the shaft end portion by a hydraulic pressure, and a straight hole portion (-) having teeth () engaging a plurality of teeth () formed in a straight shaft portion () of the shaft end portion, the taper hole portion (-) and the straight hole portion (-) being located adjacent to each other.

Hydraulic detachable coupling

An inner shroud portion and an outer shroud portion dividedly formed per stationary blade are formed integrally with each stationary blade. A plurality of the stationary blades adjacent to each other in a circumferential direction are coupled together by a band member at the outer shroud portions. The inner shroud portions are held between seal holders which are formed as two divided members in the flowing direction of a working fluid, which are fastened by a bolt, and which have a length corresponding to the plurality of the stationary blades. The plurality of stationary blades, the inner and outer shroud portions, the band member, and the seal holders assembled in this manner constitute a unit. A plurality of the units are connected in the circumferential direction to constitute a stationary blade ring of an axial compressor.

Stationary blade ring of axial compressor

A turbine blade and a gas turbine are provided in which the velocity of cooling fluid at the inlet of a pin fin region is improved so that the cooling performance at the trailing edge of the turbine blade can be improved. It includes an airfoil; a supply channel extending through the interior of the airfoil in the span direction, through which cooling fluid flows; a pin fin channel extending from the supply channel along the center line of the airfoil toward the trailing edge of the airfoil and opening at the trailing edge to the exterior of the airfoil; a plurality of gap pin fins projecting from a pair of opposing inner walls that constitute the pin fin channel at a region at the supply channel side of the pin fin channel and forming a gap therebetween extending in the span direction; pin fins connecting the pair of opposing inner walls at a region at the trailing edge side of the pin fin channel; and an insertion portion disposed in the gap to decrease the area of the channel of the cooling fluid at the region at the supply channel side of the pin fin channel.

Turbine blade and gas turbine

A casing includes an upper casing and a lower casing jointed in a dividable manner, and a sealing structure that suppresses outward leakage of gas from a joint area between the upper casing and the lower casing. The casing 1 also includes: an upper protruding element that protrudes from an outer circumference of the upper casing; a lower protruding element that protrudes from an outer circumference of the lower casing; and an intermediary member that is arranged on outer circumferences of the upper protruding element and the lower protruding element. The joint area between the upper casing and the lower casing is extended by the upper protruding element and the lower protruding element, and the intermediary member is welded to the upper protruding element and the lower protruding element, at a position offset from the joint area.

Casing and fluid machine

A turbine rotor is provided with a torque transfer mechanism equipped between a pair of adjacent rotor discs among a plurality of rotor discs so as to transfer a torque from one rotor disc to another rotor disc. The torque transfer mechanism is provided with a first groove having a semi-circle in cross section formed on a first contact face of one rotor disc, and a second groove having a semi-circle cross section formed on a second contact face of another rotor disc, and a torque pin inserted into cylindrical holes formed by combining the first grooves and the second grooves. The flange of the torque pin has long sides and short sides, and the length of the short sides is shorter than the width of an binary flange receiving plane formed by a pair of outer circumference planes of adjacent two rotor disc along the circumferential direction, and the long side of the flange has a longer length than the width of the binary flange receiving plane. A pair of flange receiving recessed portions is provided for receiving the end portions of the long sides of the flange on both side walls of the binary flange receiving plane.

Turbine rotor and turbine having the same

There is provided a fastening device in which the tightening load at the engaged portion between the thread of a nut and the thread of a bolt can be made uniform along the length of the threads, the circumferential load distribution at the end of the engagement of the bolt can also be made uniform, and concentration of a stress in the vicinity of the beginning of the engagement can be reduced. The fastening device includes an object to be fastened, having a nut hole; a nut having, at one end, a female screw portion to be fitted in the nut hole and configured such that the center of gravity is located in the nut hole; and a bolt having, at one end, a male screw portion to be screwed into the female screw portion.

Fastening device

Adjustment of the distance between the tip of a pickup section and the outer surface of a shaft of a rotor can be carried out easily and with high precision. In a vibrometer mounting mechanism securing a measuring section of a vibrometer for measuring vibration of a shaft of a rotary machine to a casing of the rotary machine, the vibrometer mounting mechanism includes a case secured to the casing with fixing means; an inner cylinder that accommodate the measuring section at one end, that is disposed in the inside of the case, and that slides relative to the case; and an adjustment bolt disposed at one end of the case and capable of moving forward and backward with respect to the case and the inner cylinder, wherein the inner cylinder is made to move in a direction away from the shaft by the adjustment bolt being inserted into the case and the inner cylinder, and wherein the inner cylinder is made to move in a direction toward the shaft by the adjustment bolt being retracted from the case and the inner cylinder.

Vibrometer mounting mechanism

The present invention provides a centering mechanism capable of improving the efficiency of centering work and reducing the work time and the cost. The centering mechanism centers an inner member located inside in a radial direction, with respect to an outer member arranged to surround the inner member in a circumferential direction, and includes a vertical-direction positioning unit which positions the inner member in a vertical direction in a non-stepwise manner.

Centering mechanism

There is provided a gas turbine capable of improving the durability of a main shaft by absorbing the deformation of a casing due to heat and pressure and suppressing stresses acting on the main shaft. A link plateof a movable supporting legthat supports a casingof a gas turbineon the turbineside is installed beforehand in an inclined manner at an angle &#x3b8;, whereby the displacement X of a lower casingL in the height direction; which occurs between a pinin a top end portion of the link plateand a top surface of a lower casingL when the operation status of the gas turbineshifts from a stop condition to an operating condition is compensated for. This prevents a main shaftfrom changing in the height direction in the part of the movable supporting legand suppresses bending stresses acting on the main shaft

Gas turbine

A casing of a hydraulic machine such as a gas turbine is formed as a horizontally split type flangeless casing. The flangeless casing consists of an upper casing and a lower casing joined together at joint faces and fastened by fastening bolts. The fastening bolt has a screw thread which engages the threaded hole on the joint face of the lower casing. A bolt hole having an internal screw thread and through which the fastening bolt passes is provided in the upper casing. A sleeve having an external screw thread is fitted into the bolt hole of the upper casing by engaging the external screw of the sleeve with the internal sleeve of the bolt hole. An enlarged diameter portion is formed on a shaft of the fastening bolt at the portion where the enlarged diameter portion abuts an upper end face of the sleeve when the fastening bolt is screwed into the threaded hole in the lower casing. When the fastening bolt is tightened, the shaft tensile force of the bolt is received by the abutment of the enlarged diameter portion and the upper end face of the sleeve and, then, transferred from the sleeve to the upper casing through the engagement of the external screw thread of the sleeve and the internal screw thread of the bolt hole of the upper casing and generates the fastening force which presses the upper casing to the lower casing.

Fastening arrangement for a split casing

This pilot nozzle has a fuel oil supply pipe disposed at the center of a heat-shielding air layer that is provided along an axial core, and a plurality of atomized-fluid supply paths are disposed in the circumferential direction of a cylinder unit that surrounds the outside of the heat-shielding air layer. The atomized-fluid supply paths and the fuel gas supply paths are disposed alternately and uniformly. Based on this structure, it is possible to take a large thickness for the heat-shielding air layer to a maximum extent in a radial direction. Therefore, it is possible to protect the fuel oil supply pipe disposed at the center, from high temperature at the outside of the pilot nozzle.

Pilot nozzle for a gas turbine combustor and supply path converter

Gas turbine rotor blade tip loss is reduced and loss caused by leakage of working fluid through gap between members constituting an annular flow passage is reduced. Turbine (AT) of a gas turbine (GT) constituting a combined cycle plant (CC) is supported to a turbine casing ( ) to be expandable or contractible in turbine shaft ( ) radial direction. First blade ring ( ) corresponds to first stage turbine stator blades (TS ) and rotor blades (TR ) and comprises a first heating medium flow passage ( P) for steam circulation therein. Second blade ring ( ) corresponds to second stage turbine stator blades (TS ) and rotor blades (TR ) and comprises a second heating medium flow passage ( P) for steam circulation therein. Further provided is a communication member ( ) for connecting the first blade ring ( ) and second blade ring ( ) to each other and for communicating the first heating medium flow passage ( P) and second heating medium flow passage ( P) with each other.

Combined cycle plant with gas turbine rotor clearance control

The gas-turbine rotor is composed of a plurality of rotor disks which are placed one next to another in the axial direction thereof and fastened by spindle bolts piercing through all the rotor disks in the axial direction. Each of the rotor disks has annular protrusions on both sides and are joined to the adjoining rotor disks by abutting the top faces of the annular protrusions against the annular protrusions of the adjoining rotor disks. Grooves having semicircular cross sections are formed on the top face of each of the annular protrusions. When the rotor is assembled, the grooves of the adjoining rotor disks join and form circular holes. Cylindrical torque pins having flanges at both ends are fitted into the circular holes formed by the grooves. The surfaces of the inner side walls of the annular protrusions are formed as spherical surfaces. The faces of the flanges of the torque pins which contact the inner side walls are formed as spherical shapes matching the curvature of the spherical surfaces of the inner side walls.

Gas-turbine rotor

In a cooling air supply system for a rotor, cooling air is supplied from cooling air nozzles to an annular cooling air passage formed around the rotor shaft. The cooling air nozzles are formed as straight air passages having circular cross sections. The straight air passages disposed on a stationary annular nozzle member surrounding the rotor shaft. Since the nozzles are formed as straight air passages having circular cross sections, the nozzles can be manufactured accurately at low cost by machining the annular nozzle member. Further, since the freedom for the arrangement of the nozzles increases by using the straight air passages, the nozzles can be arranged in such a manner that cooling air leaving the nozzle flows into the cooling air passage around the rotor shaft without changing its flow direction. Thus, the pressure drop in the cooling air caused by changing flow direction can be largely reduced.

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Takasago, Japan

Taku Ichiryu