Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Mitsubishi Heavy Industries, Co., Ltd.

Sunao Aoki

Kiyoshi Suenaga

Yasuoki Tomita

Kazuo Uematsu

Hiroki Fukuno

Kouji Takahashi

Taiji Torigoe

Hideaki Sugishita

Eisaku Ito

Kazutaka Mori

Ikuo Okada

Kazuharu Hirokawa

Yukihiro Hashimoto

Minoru Ohara

Tatsuo Ishiguro

Keizo Tsukagoshi

Rintaro Chikami

Yoshinori Shirakata

Wataru Seki

Akihiro Kawada

Toshishige Ai

Yoichiro Iritani

Koji Hirokawa

Katsunori Tanaka

Makoto Kobayashi

Yoichi Iwasaki

Masanori Yuri

Shunsuke Torii

Koichi Akagi

Hidetaka Mori

Kengo Yamaguchi

Katsunori Akiyama

Masaaki Matsuura

Jun Kubota

Yoshiaki Tsukuda

Hisato Arimura

Nobuyuki Yamaguchi

Toshiaki Sano

Akihiko Shirota

Takehiko Hirata

Shouichi Kikkawa

Youichi Iwasaki

Junya Michinishi

Shuichi Kajiwara

There is provided a through-hole manufacturing method for a cylindrical body wall that enables the operation of forming a through-hole without leaving a machining burr on the wall of a cylindrical member to be easily and reliably carried out without depending on experts. A through-hole manufacturing method for a cylindrical body wall in which a machining burr is not formed on inner walls of through holes formed by a tool piercing the wall of a cylindrical body, the method including a hole forming step of forming one pair or a plurality of pairs of the through-holes in the cylindrical body wall by the tool piercing the cylindrical body from the outside orthogonally or substantially orthogonally to a cylindrical body axis of the cylindrical body; and a welding step of sealing the through-hole formed by the tool piercing the cylindrical body from the outer wall to the inner wall by welding using a welding jig made of a material having better heat conductivity than the cylindrical body, wherein the through-hole formed by the tool piercing the cylindrical body from the inner wall to the outer wall is left as a nozzle hole.

Through-hole manufacturing method for cylindrical body wall and cylindrical body structure

A thermal barrier coating material, containing a metal binding layer laminated on a base material and a ceramic layer laminated on the metal binding layer, the ceramic layer comprising partially stabilized ZrOwhich is partially stabilized by additives of DyOand YbO.

Thermal barrier coating material and method for production thereof, gas turbine member using the thermal barrier coating material, and gas turbine

A thermal barrier coating enabling to prevent peeling of layer in a high temperature use and still having a high thermal barrier effect, a turbine part coated by this thermal barrier coating and a gas turbine comprising this turbine part are provided. The thermal barrier coating comprises a base materialof high temperature heat resistant alloy and a ceramics layerformed on the base material. The ceramics layercomprises ZrOadded with YbOas stabilizer and is laminated on the base material via a bond coat layerlaminated as a metallic bond layer. A plurality of cracksA are preferably introduced in the ceramics layer. The turbine part is constructed having its surface coated with the above thermal barrier coating.

Thermal barrier coating, manufacturing method thereof, turbine part and gas turbine

The present invention relates to a method of repairing a Ni-based alloy part having an undercoat layer and a topcoat layer stacked on a Ni-based alloy base when the topcoat layer is damaged, comprising the steps of removing a peeled-off portion of the damaged topcoat layer and a denatured portion of the undercoat layer corresponding to the peeled-off portion, forming another undercoat layer by applying spraying to an opening portion of the undercoat layer in the atmosphere at a spray particle speed of 300 m/s or more and a base-material temperature of 300&#xb0; C. or less, and forming another topcoat layer in the peeled-off portion of the topcoat layer

Method of repairing a Ni-base alloy part

An evaporator is constructed such that bundles of heat exchanger tubes for flowing cold water are disposed inside a container for admitting the cooling medium. When a total cross sectional area of the heat exchanger tubes at various locations in a flow passage of the cold water is compared, the total area in a downstream location is less than a total area in an upstream location of the flow passage. Therefore, even though the temperature differential between the cold water and the cooling medium is small, the flow speeds of the cold water in the downstream tubes become faster than that in the upstream tubes, so that the heat flux is increased and heat transfer rate is improved.

Evaporator and refrigerator

A thermal barrier coating material can prevent spall-off from occurring during operation at high temperatures and has a high heat insulating effect. A turbine parts and a gas turbine that are protected with the thermal barrier coating material are also provided. The thermal barrier coating material of the present invention comprises a ceramic layer, which is formed on a high temperature heat-resistant alloy baseto protect the basefrom high temperatures, the ceramic layerbeing applied via a bonding coat layerprovided as a metal bonding layer and is made of ZrOwith ErOadded thereto as a stabilizing agent. The turbine parts and the gas turbine of the present invention are coated with the thermal barrier coating material on the surfaces thereof.

Thermal barrier coating material, gas turbine parts and gas turbine

A combined cycle system includes a gas turbine ( ) having a generator ( ), a compressor ( ), a combustor ( ), a blade cooling air cooler ( ), a fan ( ), and a turbine ( ); a steam turbine ( ) having a high pressure turbine ( ), an intermediate pressure turbine ( ), and a low pressure turbine ( ); and a waste heat recovery boiler ( ). Saturated water from a high pressure pump ( ) is partially led into a heat exchanger ( ) for cooling steam to be supplied into a moving blade ( ) and a stationary blade ( ). Also, outlet steam from the high pressure turbine ( ) is led into the moving blade ( ), the stationary blade ( ), and the combustor transition piece ( ) for cooling thereof, and the steam is then supplied to an inlet of the intermediate pressure turbine ( ). Further, the outlet steam from the high pressure turbine ( ) is led into the turbine ( ) for cooling blades thereof. The steam used for cooling the stationary blade is supplied to the inlet of the intermediate pressure turbine ( ), and the steam used for cooling the moving blade is supplied to a reheater ( ). Thus, the efficiency is enhanced.

Steam cooled gas turbine system with regenerative heat exchange

In an evaporator composed by providing plural heat-transfer pipes for flowing cold water in a container into which a refrigerant is introduced, the heat-transfer pipes are divided into plural pipe groups and the pipe groups are arranged in a zigzag pattern with intervals between each adjacent pipe groups. Bubbles which are generated around the heat-transfer pipes provided lower position, easily come to the surface of the refrigerant, and further, there are few bubbles which degrade the performance of the heat-transfer pipes positioned around the center of the pipe groups, preventing a fall in the heat transfer coefficient.

A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, cooling air enters cooling passages to flow through other cooling passages for cooling the blade, and then to flow out of the blade. A recessed portion having a smooth curved surface is provided in the platform near a blade fitting portion on the blade trailing edge side. A fillet of the blade fitting portion on the blade trailing edge side has a curved surface with curvature larger than that of a conventional blade fitting portion. A hub slot below the fillet, for blowing air, has a cross sectional area larger than other slots of the blade trailing edge. A thermal barrier coating is applied to the blade surface. By the above construction, thermal stresses due to temperature differences between the blade and the platform during gas turbine stoppage are made smaller and occurrence of cracks is prevented.

Gas turbine moving blade

In a steam cooling system proposed heretofore, high-pressure steam is supplied into an internal space of a blade for effecting cooling thereof with the high-pressure steam to thereby recover heat energy. This system however suffers from problems concerning the strength of the blade and the like. The present invention solves these problems and provides a gas-turbine blade which does not suffer from problems concerning the strength thereof nor problems concerning the flow of high-pressure steam. To this end, a coolant flow passage is formed within the blade extending in the longitudinal direction of the blade, and reinforcing ribs which interconnects a dorsal wall and a ventral wall of the blade is disposed within the coolant flow passage so as to extend in the flow direction of the coolant. Hence, the strength of the blade can be ensured without any obstacle to the flow of the coolant.

Gas turbine blade

A steam-cooling gas turbine in which cooling steam is fed from a center portion of a rotating shaft and recovered through passages disposed at the outer side of the center portion with steam leaking through a seal portion from a feeding steam being effectively recovered. Feed steam (,) serving as coolant is supplied to a cavity (,) from a inner cylinder (,) and hence fed to moving blades (,) through recesses (,) formed in a coupling portion (,) interposed between a final-stage disk (,) and a turbine shaft (,), steam feeding pipes (,) and steam feeding passages (,). After cooling of the moving blades, steam (,) is recovered through steam recovering passages (,), steam recovering pipes (,), radial steam-recovering passages (,), axial steam-recovering passages (,) and outlet openings (,). The coupling portion (,) is forced to hermetically close under thermal stress, whereby leakage of the feed steam (,) is prevented. Steam leaking through a seal portion constituted by stationary and rotatable seal fin assemblies (,) can be effectively recovered. The inner cylinder (,) can move in the axial direction through cooperation of piston rings (,) and a centering piece (,) adapted for absorbing thermal stress induced in the inner cylinder (,). Upstream tip end portions of steam feeding pipes (,) and steam recovering pipes (,) are secured onto a side surface of the first-stage disk (,) through sleeves removably fitted thereto.

Steam-cooling type gas turbine

A sealing device for a gas turbine stator blade, in which an outer shroud (,) is mounted by heat insulating rings (,) on a blade ring (,). The blade ring (,) has a first air hole (,), which communicates with a space (,), and a second air hole (,), which communicates with a seal tube (,). The seal tube (,) is inserted into the second air hole (,), and a spring (,) is arranged between a projection (,) of the tube (,) and a retaining portion (,) of the air hole (,) to removably secure the seal tube (,). Cooling air (,) flows through the first air hole (,) to cool the shrouds and the inside of a stator blade (,) until it is released from the trailing edge of the blade. The cooling air also flows into a cavity (,) so that a high pressure can be maintained without a pressure loss because the tube (,) is independent of the space (,) in the blade ring.

Device for sealing gas turbine stator blades

A blade for a gas turbine includes an internally formed passage (a) for cooling the blade with steam. The ratio (t/c) of blade thickness (t) to chord length (c) should fall within the range of 0.10 to 0.15.

In gas turbine cooled moving blade, a cooling air passage is made shortest and temperature elevation and pressure drop of the cooling air are suppressed. The cooling air passage (,) is bored in a turbine cylinder wall (,) located below a first stage stationary blade (,). The cooling air passage (,) communicates at one end (,) with a turbine cylinder and at the other end (,) with a space (,) between the stationary blade and the moving blade. The passage (,) is directed to an air inflow hole (,) provided in a shank portion (,) of a lower portion of a platform (,) of the moving blade (,). Cooling air is jetted from the cooling air passage (,) toward the air inflow hole (,) so as to flow into the shank portion (,) and then into the moving blade (,) for cooling thereof. An axis (,) of the cooling air passage (,) is directed so as to deviate in a rotational circumferential direction by an angle determined by the velocity of the cooling air jetted from the cooling air passage (,) and the rotational velocity of the moving blade (,) from position of the air inflow hole when the moving blade (,) stands still in row with the stationary blade (,) in rotor axial direction. Thus, the cooling air can be jetted in an optimal direction with the shortest distance, and the temperature elevation and pressure drop of the cooling air can be suppressed to minimum.

Gas turbine cooling moving blades

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Takasago, Japan

Sunao Aoki