Mitsubishi Heavy Industries Limited

Shigehiro Shiozaki

Yasuoki Tomita

Masamitsu Kuwabara

Kotaro Ohshima

Shunsuke Torii

Ryotaro Magoshi

Hideaki Kaneko

Kengo Yamaguchi

Friedrich Soechting

Tatsuaki Fujikawa

Yoshiyuki Morii

Shinichi Inoue

The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A flow passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.

Gas turbine stationary blade

The gas turbine stationary blade comprises a stationary blade section provided therein with a passage for cooling air, an inner shroud for supporting the stationary blade section on the side of a discharge port of the cooling air, and a plurality of segments each of which includes at least one stationary blade section and at least one inner shroud. A low passage is pulled out from the discharge port of the cooling air, and the flow passage is introduced to a front edge corner section of the inner shroud and is extended rearward along a side edge of the inner shroud.

The division wall is made up of a plurality of division wall sections forming a passage wall of high temperature gas which are connected in the direction of arrangement of blades to form a wall surface having a roughly circular cross section as a whole, a gas flow restricting structure for preventing high temperature gas from passing through a gap formed at a connecting portion between the division wall sections in the flow direction of the high temperature gas from the opening on the upstream side of the high temperature gas in the gap, or a gas flow restricting structure for preventing the high temperature gas from being embraced in the gap, for example, a sealing member formed into a prism having a T-shape cross section as a whole composed of a plane portion as a sealing portion and a projected portion for filling the gap is provided.

Division wall and shroud of gas turbine

The present invention provides a turbine moving blade, a turbine stationary blade, and a turbine split ring which are capable of restraining the deterioration and peeling-off of a thermal barrier coating easily and surely, and a gas turbine capable of enhancing the energy efficiency by increasing the temperature of combustion gas. The turbine moving blade provided in a turbine constituting the gas turbine includes a platform having a gas path surface extending in the combustion gas flow direction, and a blade portion erecting on the platform. The thermal barrier coating covering the gas path surface is formed so as to go around from the gas path surface to an upstream-side end face and a downstream-side end face of the outer peripheral faces of the platform.

Turbine moving blade, turbine stationary blade, turbine split ring, and gas turbine

A gas turbine wherein cooling failure attributable to the occurrence of a horseshoe vortex produced in the vicinity of the stationary blades of the turbine is preventable, the gas turbine including moving blades provided on a rotor side which rotate together with the rotor, and stationary blades provided on a stationary side which cover the periphery of the moving blades and form a combustion gas flow path in the interior, and which are arranged alternately with the moving blades in the rotation axis direction of the rotor.

Gas turbine

A gas turbine segmental ring has an increased rigidity to suppress a thermal deformation and enables less cooling air leakage by less number of connecting portions of segment structures. Cooling air ( ) from a compressor flows through cooling holes ( ) of an impingement plate ( ) to enter a cavity ( ) and to impinge on a segmental ring ( ) for cooling thereof. The cooling air ( ) further flows into cooling passages ( ) from openings ( ) of the cavity ( ) for cooling an interior of the segmental ring ( ) and is discharged into a gas path from openings of a rear end of the segmental ring ( ). Waffle pattern ( ) of ribs arranged in a lattice shape is formed on an upper surface of the segmental ring ( ) to thereby increase the rigidity. A plurality of slits ( ) are formed in flanges ( ) extending in the turbine circumferential direction to thereby absorb the deformation and thermal deformation of the segmental ring ( ) is suppressed.

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Hyogo, Japan

Shigehiro Shiozaki