Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

International Business Machines Corporation

Kokusai Denshin Denwa Co., Ltd.

Satoshi Hada

Saki Matsuo

Susumu Wakazono

Masamitsu Kuwabara

Keita Takamura

Hidemichi Koyabu

Keizo Tsukagoshi

Tomoko Morikawa

Junichiro Masada

Hiroyuki Otomo

Yasuo Miyahisa

Yasuoki Tomita

Masanori Yuri

Shunsuke Torii

Satoshi Mizukami

Hidekatsu Atsumi

Katsunori Tanaka

Michiharu Kudo

Yoshifumi Okajima

Akihiko Tozawa

Kunihiko Waki

Friedrich Soechting

Tomofumi Shintani

Norifumi Hirata

Yasumasa Kunisada

Tomoko Hashimoto

Takuya Okamoto

Sosuke Nakamura

Hiroshi Asano

Yoshitaka Uemura

Naishin Seki

Mitsuru Kondo

Yoshifumi Tsuji

Yusuke Izumi

Ryozo Tamura

Takahiko Imada

Katsutoshi Ooe

Hiroyuki Yamamoto

Takashi Fujii

Kiyoshi Suenaga

Hideaki Sugishita

Hiroki Shibata

Shigemi Mandai

Shinichi Yoshioka

Eisaku Ito

Kazunari Ide

Kenichi Arase

Taku Ichiryu

Tetsu Konishi

Tsuyoshi Kitamura

Masaaki Matsuura

Hideyuki Uechi

Takaharu Hiroe

Ryotaro Magoshi

Koki Tateishi

Yasuro Sakamoto

Mitsuru Yamada

Koichi Akagi

Robbert C Van Der Linden

Ryuji Takenaka

Kouichi Akagi

Toshiaki Tanaka

Takashi Hiyama

Robbert Van Der Linden

Daigo Fujimura

Ryuta Ito

Tetsuya Shimmyo

Vincent Laurello

Yuya Fukunaga

Koshiro Fukumoto

Hitoshi Kitagawa

Mitsuo Hasegawa

David Allen Flodman

Yoshimasa Takaoka

Hiroki Kitada

Kazuki Morimoto

Makato Murata

Takehiko Shimizu

Rosic Budmir

Sumiu Uchida

Yuko Suenaga

A turbine stator vane comprising: a vane body; a shroud formed at an end of the vane body in a vane height direction; a fillet portion joining the vane body and the shroud; and a plurality of cooling holes in a bottom plate contacting a combustion gas flow path. The plurality of cooling holes connect to entry openings and downstream exit openings formed in the bottom plate. The entry openings and the exit openings are connected by cooling hole center lines having the same inclination with respect to an axial direction. The plurality of cooling holes constitute a set of cooling hole rows in which a linear first opening center line connecting the centers of the exit openings and a linear second opening center line connecting the centers of the entry openings are formed parallel to each other.

Turbine stator vane and gas turbine

A turbine stationary blade is a turbine stationary blade that includes: a blade body; and a shroud formed in an end portion of the blade body in a blade height direction. The shroud includes: a bottom plate in contact with a combustion gas flow passage; a peripheral wall formed in the blade height direction and along a peripheral edge of the bottom plate; a recess forming a space surrounded by the peripheral wall and the bottom plate; a plurality of partition ribs connecting the blade body and the peripheral wall, dividing the recess into a plurality of spaces, and forming a plurality of cavities; and an impingement plate dividing the space into an outer cavity formed on an outer side in the blade height direction and an inner cavity formed on an inner side of the outer cavity, and having a plurality of through holes via which the outer cavity and the inner cavity communicate with each other. The peripheral wall includes: a leading edge end portion extending to a leading edge side of the blade body; a suction side end portion extending from a leading edge to a trailing edge on a suction side of the blade body, and internally including a suction side passage; a pressure side end portion extending from a leading edge to a trailing edge on a pressure side of the blade body, and internally including a pressure side passage; and a trailing edge end portion extending to a trailing edge side of the blade body. The plurality of cavities are formed from the inner cavity, and include: a first cavity disposed on a leading edge pressure side so as to surround a circumference of the blade body between the blade body and the peripheral wall, connected to the cooling hole formed in the bottom plate, and connected to the pressure side passage; and a second cavity disposed adjacent to an axially downstream side of the first cavity, disposed on a most axially upstream side of the pressure side among the partition ribs, disposed via a first partition rib connecting the pressure side end portion and the pressure surface of the blade body, and having a plurality of cooling holes in the bottom plate. An opening density of the through holes of the impingement plate in the second cavity is lower than the opening density of the through holes of the impingement plate in the first cavity.

Gas turbine stationary blade and gas turbine

A rotor blade including: a blade body extending in a blade height direction that is a direction perpendicular to an airfoil cross-section; and a platform provided to an end at a hub side, from between a tip side and the hub side which are of the blade height direction. The blade body includes: an anterior edge and a posterior edge; a ventral surface and a dorsal surface linking the anterior edge and the posterior edge together; and a cooling passage extending in the blade height direction between the ventral surface and the dorsal surface. The ventral/dorsal wall thickness ratio at any position between the hub-side position and the middle position in the cooling passage is smaller than the ventral/dorsal wall thickness ratio at any position between the middle position and the tip-side position.

Rotor blade and gas turbine provided therewith

A stator blade including a blade body, a first insert, a second insert, and an end cover. The blade body has a first blade air passage and a second blade air passage extending in the blade height direction within the blade body. Each passage has an open end on a blade-height second side. The first insert and the second insert have tubular outer peripheral plate portions. A plurality of impinge holes are formed in the outer peripheral plate portion. The tube height opening side of the outer peripheral plate portion in the tube height direction is open. The outer peripheral plate portion of the first insert is disposed in the first blade air passage such that cooling air flows into the outer peripheral plate portion from the opening of the first insert. The outer peripheral plate portion of the second insert is disposed in the second wing air passage.

Stator blade and gas turbine comprising same

A stator vane assembly of a gas turbine includes: a stationary member formed to have an annular shape; and a plurality of stator vane segments each including a shroud and a vane body, the plurality of stator vane segments disposed along a circumferential direction of the stationary member at a radially inner side of the stationary member such that a cavity is disposed between the shrouds and the stationary member and the shrouds are disposed adjacent to one another in the circumferential direction of the stationary member. The stationary member has a hole which penetrates through the stationary member from a radially outer side toward the radially inner side, and a center axis of the hole is oriented toward a circumferential-direction end portion of the shroud.

Stator vane assembly of gas turbine, stationary member segment, and method of producing stator vane assembly of gas turbine

This gas turbine blade comprises a platform part having a cooling passage formed inside, and a wing body part protruding from the upper surface of the platform part. A plurality of first ejection ports that eject a gas supplied from the cooling passage are formed in an inner chordal region of the upper surface, which is positioned further toward the wing-body side than a wing chord connecting the leading edge and the trailing edge of the wing body part. A plurality of second ejection ports that eject the gas supplied from the cooling passage are formed in an outer chordal region of the upper surface, which is positioned on the side opposite the inner chordal region with respect to the wing chord. The outer chordal region has an outer chordal leading edge region positioned on the leading-edge side and an outer chordal trailing edge region positioned on the trailing-edge side, more second ejection ports being formed in the outer chordal leading edge region than in the outer chordal trailing edge region.

Gas turbine blade

This stator vane is at least provided with a blade body disposed in a combustion gas flow channel through which a combustion gas flows, a shroud that defines a part of the combustion gas flow channel, and an impingement plate attached to the shroud. A partition rib extends from a blade body end to an inner wall surface of a peripheral wall, and a shelf is provided at a rib-less part of the inner wall surface of the peripheral wall excluding at least a part in which the partition rib extends to the inner wall surface of the peripheral wall.

Stator vane and gas turbine

In a clearance control system for a gas turbine, a control device operates an adjustment device such that a first flow rate is greater than a second flow rate when a load stable state is entered in which a fluctuation range of a load shifts within a preset range, and operates the adjustment device such that the second flow rate is greater than the first flow rate when a load fluctuation state is entered in which the load falls outside the range.

Clearance control system for gas turbine

A turbine stator vane includes: a vane body which includes: an airfoil portion which has a serpentine flow passage inside thereof, the serpentine flow passage including a plurality of cooling flow passages and a plurality of turn-back flow passages; a shroud disposed on at least one of a tip end side or a root end side, in the vane height direction, of the airfoil portion; and a lid portion fixed to the airfoil portion. The lid portion forming the turn-back flow passage and being provided as a separate member from the airfoil portion. The lid portion has an inner wall surface width formed to be greater than the flow-passage width of the cooling passage formed in the airfoil portion, and a minimum value of a thickness of the lid portion is smaller than a thickness of a part of the shroud to which the lid portion is mounted.

A turbine blade is provided with an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage. The cooling passage includes: a first cooling passage located closer to the pressure surface than the suction surface; and a second cooling passage located closer to the suction surface than the pressure surface. The first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion. At least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member.

Turbine blade

A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud. The circumferential-direction passage includes, in a cross-sectional view as seen in the circumferential direction, an oblique passage having a third end portion to protrude closer to the gas path surface toward the side of a leading edge, and a fourth end portion formed at the side of the trailing edge with respect to the third end portion, the oblique passage having an opening portion disposed on a trailing-edge side end surface of the protruding portion and closed by a lid portion, and a position, in an axial direction, of the first end portion where each trailing edge end portion passage connects to the circumferential-direction passage is positioned at the side of the leading edge with respect to a position of the trailing-edge side end surface of the protruding portion at a position where the protruding portion connects to the shroud.

Turbine stator vane, gas turbine, and method of producing turbine stator vane

A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.

Turbine vane and gas turbine comprising same

A turbine blade and a gas turbine are provided with: an airfoil portion () internally including a cooling air passage (); a platform () provided in a blade base end portion () in a blade height direction (Dh) of the airfoil portion (); and a fillet portion () provided around the entire perimeter of a connecting portion of the airfoil portion () and the platform (). The fillet portion () includes a first fillet portion () which is provided on a rear side blade surface () side of the airfoil portion (), on the trailing edge () side of a position at which the distance between the rear side blade surface () of the airfoil portion () and a rear side edge portion () of the platform () is shortest, and which has a fillet width (W) that is greater than the fillet width W of other regions of the fillet portion ().

Turbine blade and gas turbine

A turbine blade including an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface extending between the leading edge and the trailing edge. The airfoil portion internally forming a cooling passage, which includes first and second cooling passages, and a plurality of outflow passages each having one end which opens to a merging portion formed by connecting an end portion of the first cooling passage on a side of the trailing edge and an end portion of the second cooling passage on the side of the trailing edge, and another end which opens to the trailing edge. The first cooling passage and the second cooling passage are divided by a partition member disposed in the airfoil portion. The cooling passage includes pressure side pin fins in the first cooling passage, and suction side pin fins in the second cooling passage.

Turbine blade and method for manufacturing the turbine blade

A turbine blade includes an airfoil body, and a plurality of cooling passages extending along a blade height direction inside the airfoil body and being in communication with each other to define a serpentine flow passage. The plurality of cooling passages include first turbulators on an inner wall surface of an upstream cooling passage of the plurality of cooling passages, and second turbulators on an inner wall surface of a downstream cooling passage of the plurality of cooling passages. A second angle formed by the second turbulators with respect to a flow direction of a cooling fluid in the downstream cooling passage is smaller than a first angle formed by the first turbulators with respect to the flow direction of the cooling fluid in the upstream cooling passage.

Growing community of inventors

Yokohama, Japan

Satoshi Hada