Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Tomoko Morikawa

Satoshi Hada

Saki Matsuo

Hiroyuki Otomo

Takuya Okamoto

Kenichi Arase

Hideyuki Uechi

Kunihiko Waki

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 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 blade has a flow passage forming plate that defines a part of a combustion gas flow passage. The flow passage forming plate has a plurality of back channels that open in a back end surface. A density of openings of the plurality of back channels in a middle region of the back end surface is higher than the density of openings of the plurality of back channels in at least one side region of a suction-side region and a pressure-side region of the back end surface. The density of openings is a ratio of a length of wetted perimeter of the plurality of back channels to an interval of openings of the plurality of back channels.

Blade and gas turbine including the same

Provided is a flow path forming plate having a gas path surface that comes in contact with combustion gas, end surfaces formed at peripheral edges of the gas path surface, a first side passage, and a plurality of end surface blow-out passages. The first side passage extends in a direction along a first end surface that is one of the end surfaces, and cooling air flows through the first side passage. A plurality of passage forming surfaces forming the first side passage includes a first forming surface that faces an opposite-flow-path side and extends gradually farther away from the gas path surface while extending toward the first end surface. The end surface blow-out passages open in the first forming surface of the first side passage and in the first end surface.

Flow path forming plate, vane including this flow path forming plate, gas turbine including this vane, and manufacturing method of flow path forming plate

In a turbine vane and a gas turbine, an outer shroud is fixed to one end of a vane body formed in a hollow shape, an inner shroud is fixed to the other end thereof, and a partition plate is fixed to the inner portions of the vane body, the outer shroud, and the inner shroud, so that a cavity is formed so as to be continuous between the partition plate and the group of the vane body, the outer shroud, and the inner shroud. Then, the vane body, the outer shroud, and the inner shroud are provided with a plurality of cooling holes, and the partition plate is provided with a plurality of penetration holes. Accordingly, since the vane structure or the end wall structure is evenly cooled, a deformation or damage may be suppressed.

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Yokohama, Japan

Tomoko Morikawa