Hitachi, Ltd.

Other

The Tokyo Electric Power Company, Incorporated

Tohoku Electric Power Company, Inc.

Katsuo Wada

Nobuyuki Iizuka

Katsukuni Hisano

Fumiyuki Hirose

Isao Sato

Yoji Ishibashi

Hiromi Koizumi

Kazumi Iwai

Hiroshi Inose

Michio Kuroda

Yoshitaka Kojima

Yoshiaki Matsushita

Osamu Arai

Yoshihiro Uchiyama

Akira Arai

Hideyuki Arikawa

Hideki Tamaki

Mitsuo Haginoya

Mitsuo Teranishi

Ryuta Watanabe

Shin Yoshino

Mitsuru Kobayashi

Isao Takehara

Kazuhiko Kawaike

Yuichi Sawai

Akira Yoshinari

Hidetaro Murata

Shinichi Hoizumi

Yoshiyuki Yasutomi

Seiichi Kirikami

Motoyuki Miyata

Katsumi Iijima

Ryoichiro Oshima

Mitsutaka Shizuya

Soichi Kurosawa

Sadao Umezawa

Kimio Kano

Tosiaki Saito

Tomo Sato

Masashi Kunihiro

Hiroyuki Matsuzaki

Osamu Sakuda

A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al O layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co&mdash;32%Ni&mdash;21%Cr&mdash;8%Al&mdash;0.5%Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO &mdash;8wt. %Y O ceramic and insulative ceramic (e.g. Al O ), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.

Method for producing a ceramic-coated blade of gas turbine

A gas turbine includes a compressor and a combustor having a first fuel supply system for supplying a first fuel and a second fuel supply system for supplying a second fuel lower in calorific value than the first fuel and burning compressed air and fuel supplied through switching the first fuel system and the second fuel system. A turbine is driven by combustion gas supplied from the combustor. An extraction system is provided for extracting part of the compressed air supplied from the compressor to the combustor. Control means are provided for controlling, so as to suppress a pressure change of the compressed air supplied to the combustor, by adjusting an opening of the control valve according to a calorific value of the second fuel when fuel supplied to the combustor is switched from the first fuel to the second fuel lower in calorific value than the first fuel.

Gas turbine

A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al.sub.2 O.sub.3 layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co-32% Ni-21% Cr-8% Al-0.5% Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO.sub.2 -8 wt. % Y.sub.2 O.sub.3 ceramic and insulative ceramic (e.g. Al.sub.2 O.sub.3), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.

Ceramic-coated blade of gas turbine and method of producing same

A method of estimating non-destructively the life expectancy of ceramic members, at least a surface layer of which is made of ceramics, is disclosed. The method comprises measuring a variation in at least one of physical characteristics of said ceramic members including color, grain size, electroconductivity and Young's modulus and estimating the life expectancy of the ceramic members on the basis of the predetermined relationship between the life of said ceramics and the physical characteristics. The method is excellent in estimation of the life expectancy of ceramic members of gas turbines or nuclear fusion reactor since the life expectancy of the members to be inspected can easily be estimated in a short time without fracturing the members.

Method of non-destructively estimating life of ceramic member

A gas-turbine moving blade made of a Ni-base superalloy containing less grain boundary strengthening elements, in which a blade portion is formed of a single crystal and the rest is formed of columnar crystals, and a gas turbine including the moving blade. A thermal efficiency of the gas turbine can be improved to 35% or more, and a thermal efficiency of complex power generation with a steam turbine can be improved to 45% or more.

Blade for gas turbine

A method and an apparatus for burning gaseous fuel, the composition of the fuel varying at times, wherein; main injection ports and sub-injection ports are arranged in such positions that the fuel injected through the sub-injection ports may be ignited by a flame formed from the fuel injected through the main injection ports; fuel passes are provided or conducting the gaseous fuel separately to the two groups of injection ports; and control valve is provided for adjusting the ratio of the fuel flow to the main injection ports to the fuel flow to the sub-injection ports; whereby the proportion of the fuel to be injected through the main injection ports is increased as the rate of burning the gaseous fuel increases.

Method for burning gaseous fuel, wherein fuel composition varies

A catalytic combustor for a gas turbine comprises catalyst layers arranged in two stages in a direction of gas flow. Fuel supply nozzles are disposed close to and upstream of the downstream catalyst layer. A substantially constant amount of fuel is supplied from the fuel supply nozzles to form pilot flames by the downstream catalyst layer, which are above 1000 degrees C. and below 1500 degrees C. Combustible component having passed through the upstream catalyst layer is burned by the pilot flames.

Combustor for gas turbine

A method and an apparatus for burning gaseous fuel, the composition of the fuel varying at times, wherein; main injection ports and sub-injection ports are arranged in such positions that the fuel injected through the sub-injection ports may be ignited by a flame formed from the fuel injected through the main injection ports; fuel passes are provided for conducting the gaseous fuel separately to the two groups of injection ports; and a control valve is provided for adjusting the ratio of the fuel flow to the main injection ports to the fuel flow to the sub-injection ports; whereby the proportion of the fuel to be injected through the main injection ports is increased as the rate of burning the gaseous fuel increases.

Method and apparatus for burning gaseous fuel, wherein fuel composition

In a combustion air flow rate adjusting device in which a cylindrical regulating ring fitted about an outer peripheral surface of an inner cylinder of a gas turbine combustor is translated along the outer peripheral surface of the inner cylinder in order to vary an opening area of air intake ports formed in the peripheral wall of the inner cylinder, an arcuately moving part at a forward end of a lever fixedly connected to a forward end of a shaft extending inwardly through a peripheral wall of an outer cylinder of the gas turbine combustor is connected to a part reciprocating together with the regulating ring, by leaf springs.

Combustion air flow rate adjusting device for gas turbine combustor

The penetrating members (21, 35, 37, 38, 39) are disposed inside the cooling passage (8) at positions so as to penetrate through the cooling passage (8), and have both of ends thereof fixed to the rear side wall (17) and the body side wall (18). The projecting members (33) (34A, 34B) are disposed inside the cooling passage (8) so as to project from the rear side wall (17) or the body side wall (18). The rectification ribs (36) are disposed at intermediate positions between the penetrating members (21, 35, 37, 38, 39) or the projecting members (33, 34A, 34B). The penetrating members (21, 35, 37, 38, 39) or the projecting members (33, 34A, 34B) disturbs the main stream (3a) of the cooling fluid (3) near the internal partition (19) in both directions of the leading edge wall (16) and the first internal partition (19) and make the main stream (3a ) non-uniformly or causes its channelling.

Gas turbine cooled blade

A combustor of two-stage combustion type in which fuel is supplied only from primary fuel nozzles for combustion only in primary combustion chamber under the operating condition where gas turbine load is low, and premixed mixture is supplied into a secondary combustion chamber provided on the downstream side of the primary combustion chamber for combustion in both the primary and secondary combustion chambers under the operating condition where the load is high. An air-bleed passageway opens on a downstream side of air holes for intaking secondary combustion air to be mixed with secondary fuel and communicates with the outside of the combustor. The air-bleed passageway is provided with a regulating valve and the secondary combustion air is bled at the minimum point of the load where the secondary fuel is supplied so that the fuel to air ratio of secondary premixed mixture may not be excessively lean, thereby reducing the production of non-burned components.

A method of starting a gas turbine plant, which plant has at least one combustor including a primary combustion chamber into which primary fuel nozzles open and a secondary combustion chamber into which secondary fuel nozzles open, a compressor for supplying the combustor with compressed combustion air, and a gas turbine driven by the combustion gas generated in the combustor and adapted to drive a load such as an electric power generator. When the gas turbine is being accelerated to a rated speed or while the load is still below a normal load range, a fuel is supplied only to the primary fuel nozzle, whereas, in other loaded operation range, the fuel is supplied to both the primary and secondary fuel nozzles. Before the fuel supply to the secondary fuel nozzles is commenced, a part of the compressed air is bled through at least one air bleed pipe leading from the compressor and having an air bleed valve. The air bleed valve is controlled in such a manner that the opening degree thereof is maximized when the fuel supply to the secondary fuel nozzles is commenced and is progressively decreased in accordance with the increase of the load such as to become substantially zero when the load has been increased to the normal load range.

Method of starting gas turbine plant

A gas turbine combustor having a head combustion chamber and a rear combustion chamber, with a plurality of air supply ports arranged in a circumferential wall of the rear combustion chamber, and a fuel nozzle. An outer cylinder forms a cylindrical air flow passage between the inner cylinder and the outer cylinder. A cylindrical control member is provided which is adapted to be movable in an axial direction for regulating an opening of the air supply ports. The control member is supported by a supporting means which is adapted to maintain a gap between the control member and the wall of the rear combustion chamber. The supporting member includes a flexible member for absorbing a deformation of the control member during the axial movement of the control member so that it is possible to prevent, if not avoid, mechanical wear on the control member and to reduce the No.sub.x concentration as well as obtain a highly reliable operation of the gas turbine combustor.

Gas turbine combustor

A turbine rotor provided with a sealing member for preventing air leaks through a gap between the under side surface of a projection extending from one of discs of the rotor and the upper side surface of a outward end portion of the spacer interposed between the discs. The spacer is formed with an annular groove on the upper side surface of the outward end portion for receiving a sealing wire in its entirety. The sealing wire has its outer portion forced against the underside surface of the projection by centrifugal forces while its inner portion remains inside the groove during turbine operation, to thereby seal the gap to prevent leaks of air therethrough.

Turbine rotor with means for preventing air leaks through outward end of

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Hitachi, Japan

Katsuo Wada