Kabushiki Kaisha Toshiba

Toshiba Energy Systems & Solutions Corporation

Daizo Saito

Kunihiko Wada

Hideyuki Maeda

Shoko Ito

Iwataro Sato

Yomei Yoshioka

Junji Ishii

Nobuhiro Okizono

Satoru Kuboya

Yoshiaki Sakai

Takeo Takahashi

Masataka Tamura

Kazutaka Tsuruta

Reki Takaku

Yoshihiro Aburatani

Naoyuki Okamura

Toshiaki Fuse

Masahiro Hiragishi

Kazuhiro Kitayama

Kazutoshi Ishibashi

A thermal insulation coating member includes: a substrate having a surface; a binding layer on the surface, and a thermal insulation layer on the binding layer. The thermal insulation layer includes: a first ceramic layer including a plurality of first flat pores, the plurality of first flat pores being inclined at a first angle with respect to the surface and extending in a first direction; and a second ceramic layer including a plurality of second flat pores, the plurality of second flat pores being inclined at a second angle with respect to the surface and extending in a second direction. The second angle differs from the first angle, the second direction differing from the first direction, or the second angle and the second direction respectively differing from the first angle and the first direction.

Thermal insulation coating member, axial flow turbine, and method for producing thermal insulation coating member

A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other.

Turbine, manufacturing method thereof, and power generating system

A transition piecein an embodiment is provided with an inner ductthrough which a combustion gas is led to a turbine partand an outer ductthat is provided so as to cover an outer periphery of the inner ductand has a plurality of ejection holesto eject air onto an outer peripheral surface of the inner ductformed therein. It is structured such that a channel cross-sectional area of a cooling air channelthat is formed between the inner ductand the outer ductand through which the air ejected from the ejection holesflows gradually decreases at an air flow downstream side rather than the portion where the ejection holesare formed, and gradually increases from a throat portionhaving the minimized channel cross-sectional area to an air flow downstream side.

Transition piece between combustor liner and gas turbine

A damage-repairing method of a transition piece in an embodiment includes; an oxide removing step of removing an oxide on an outer surfaceof an inner ductof a transition piecehaving damage; a repair material placing step of placing a brazing repair materialon the outer surfaceof the inner ductso as to cover the damage; and a diffusion brazing step of diffusion heat treating the inner ductto repair the damage formed in the outer surface. The damage-repairing method of the transition piece includes: a pressurized heat treating step of, under high pressure, heat treating the inner duct; a surface finishing step of scraping off the brazing repair materialprojecting from the outer surface; and a non-pressurized heat treating step of solution heat treating and aging heat treating the inner ductunder non-pressure.

Damage-repairing method of transition piece and transition piece

A method for refurbishing service-degraded gas turbine component can recover the microstructure of the alloy of the gas turbine component, whose material is deteriorated or damaged after its operation, to the extent that is equivalent or more than the characteristic at the time of its manufacture. The method comprises performing a recovery heat treatment, performing a solution heat treatment, and performing an aging heat treatment. The recovery heat treatment heat-treats the component under a predetermined pressure, which is higher than normal pressure, wherein the temperature of the component is increased to a predetermined temperature under the predetermined pressure. The solution heat treatment is processed under reduced pressure or inert gas atmosphere after the recovery heat treatment. The aging heat treatment is processed under reduced pressure or inert gas atmosphere after the recovery heat treatment.

Method for refurbishing a service-degraded component of a gas turbine

An apparatus for correcting deformation of a gas turbine blade includes a stationary die fixed to a backside of a tip shroud of a gas turbine blade to hold a back surface thereof and a pressing die pressing a front surface of the tip shroud so as to press the tip shroud of the blade between the pressing die and the stationary. A hydraulic drive mechanism including pressure generator is arranged for pressing the pressing die against the tip shroud held by the stationary die and a control device is operatively connected to the hydraulic drive mechanism so as to set and indicate a driving condition on a basis of deformation correction data preliminarily stored in the control device.

Apparatus and method of correcting deformation of gas turbine blade

Growing community of inventors

Yokohama, Japan

Daizo Saito