Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.

Abstract: This method is a method for manufacturing a gas turbine blade, including: producing a gas turbine blade having a cooling pass inside thereof; and partially coating an inner surface of the cooling pass with Al. The step of partially coating an inner surface of the cooling pass with Al further including: a first step of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength and the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis; a second step of setting an Al-coating-applying portion of the inner surface of the cooling pass as the temperature range specified at the first step; and a third step of applying Al coating only into the set Al-coating-applying portion.

Abstract: A method of production of a welded joint which enables improvement of the fatigue strength in the case where measures for improvement of the fatigue strength cannot be applied due to the presence of structurally sealed regions is provided. The method is provided with a first weld step which performs welding by forming an inside weld toe or root part by using a weld metal with a transformation start temperature of 175° C. to 400° C. in range, at least parts of the weld metal forming the inside weld toe or root part which was formed at the first weld step becoming unmelted parts, and a second weld step which performs welding for building up the weld metal by a single pass by a weld heat input by which all of the unmelted parts are retransformed to austenite so as to introduce compressive residual stress to the inside weld toe or root part.

Abstract: This method is a method for manufacturing a gas turbine blade, including: producing a gas turbine blade having a cooling pass inside thereof; and partially coating an inner surface of the cooling pass with Al. The step of partially coating an inner surface of the cooling pass with Al further including: a first step of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength and the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis; a second step of setting an Al-coating-applying portion of the inner surface of the cooling pass as the temperature range specified at the first step; and a third step of applying Al coating only into the set Al-coating-applying portion.

Abstract: Provided is a gas turbine that can solve a problem in which a seal fin of a turbine blade is abraded by a brazed place of a honeycomb seal. A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30. The turbine 30 includes: a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5A-5C rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5A-5C facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4. The honeycomb seal 7 is formed by a plurality of corrugated thin sheet metals 71 overlapped with each other at walls of node 71a thereof and the walls of node 71 blazed with each other, each of the corrugated thin sheet metals 71 having trapezoids alternately continued.

Abstract: The most principal feature of the present invention is as follows: Namely, in the gas-turbine-use high-temperature component including the thermal barrier coating and a cooling structure, micro passages are provided inside an alloy bond-coat layer and a thermal-barrier ceramic top-coat layer of the thermal barrier coating, the micro passages being in communication from the substrate side to the surface side. Moreover, a partial amount of coolant of a coolant for cooling the high-temperature component is caused to flow out to the outside of the high-temperature component via these micro passages. The employment of the structure like this makes it possible to expect the implementation of a high-temperature component's heat-resistant-temperature enhancement effect based on the transpiration cooling effect.

Abstract: An electric component structure is provided with at least two electrical conductive parts, an insulator and a magnetic flux generating structure. The electrical conductive parts are arranged with an electric line of force existing between adjacent ones of the conductive parts. The insulator holds the conductive parts. The magnetic flux generating structure generates a magnetic flux with magnetic flux lines oriented in a direction different from a direction of the electric line of force existing between the adjacent ones of the conductive parts.

Abstract: Disclosed is a turbine blade for an industrial gas turbine including a blade substrate; a multilayer alloy coating containing a diffusion barrier layer; a bond coat; and a top coat. The blade substrate being formed of a single crystal alloy which consists essentially of 0.06 to 0.08% of C, 0.016 to 0.035% of B, 0.2 to 0.3% of Hf, 6.9 to 7.3% of Cr, 0.7 to 1.0% of Mo, 7.0 to 9.0% of W, 1.2 to 1.6% of Re, 8.5 to 9.5% of Ta, 0.6 to 1.0% of Nb, 4.9 to 5.2% of Al, 0.8 to 1.2% of Co, and the balance being Ni and incidental impurities by weight. The multilayer alloy coating, the bond coat and the top coat being directly and sequentially laminated on a surface of the blade substrate, in which the diffusion barrier layer is a multilayer and a discontinuous layer.

Abstract: A turbine blade for industrial gas turbine is used which includes a blade substrate formed of a single-crystal heat-resistant alloy containing C: 0.06 to 0.08%, B: 0.016 to 0.035%, Hf: 0.2 to 0.3%, Cr: 6.9 to 7.3%, Mo: 0.7 to 1.0%, W: 7.0 to 9.0%, Re: 1.2 to 1.6%, Ta: 8.5 to 9.5%, Nb: 0.6 to 1.0%, Al: 4.9 to 5.2%, Co: 0.8 to 1.2%, and the remainder substantially consisting of Ni with reference to mass, and includes a diffusion barrier layer, a metal layer, a bond coat, and a top coat, these layers and coats being stacked in this order on a surface of the blade substrate, the metal layer having a thickness of 5 to 30 ?m. Thus, the turbine blade can be provided which has a thermal barrier coating formed without loss of a function of the diffusion barrier layer.

Abstract: A method of production of a welded joint which enables improvement of the fatigue strength in the case where measures for improvement of the fatigue strength cannot be applied due to the presence of structurally sealed regions is provided. The method is provided with a first weld step which performs welding by forming an inside weld toe or root part by using a weld metal with a transformation start temperature of 175° C. to 400° C. in range, at least parts of the weld metal forming the inside weld toe or root part which was formed at the first weld step becoming unmelted parts, and a second weld step which performs welding for building up the weld metal by a single pass by a weld heat input by which all of the unmelted parts are retransformed to austenite so as to introduce compressive residual stress to the inside weld toe or root part.

Abstract: A resistant body 13 is provided in a periphery of at least one of the current-carrying members 11 on a surface of the insulator 12. The resistant body 13 distributes a voltage applied to the surface of the insulator 12 between a pair of the current-carrying members 11 adjacent to each other, so that a potential difference distributed on the surface of the insulator 12 is set to a discharge starting voltage or less.

Abstract: In a surface finishing method for a stainless steel material, excimer irradiation is made on a surface of the stainless steel material by emitting ultraviolet light to improve wetness. Then, a surface finishing is applied on the surface of the stainless steel material wherein the wetness is improved. In manufacturing a gasket, the stainless steel material or plate is cut in a predetermined shape, and holes and bead are formed in the metal formation plate. Then, the plate may be assembled with other plate.

Abstract: A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (hardness RC15Y: 80±3), the porous ceramic abradable layer is provided with slit grooves by machining work, and a slit groove width is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.

Abstract: An electric component structure is provided with at least two electrical conductive parts, an insulator and a magnetic flux generating structure. The electrical conductive parts are arranged with an electric line of force existing between adjacent ones of the conductive parts. The insulator holds the conductive parts. The magnetic flux generating structure generates a magnetic flux with magnetic flux lines oriented in a direction different from a direction of the electric line of force existing between the adjacent ones of the conductive parts.

Abstract: There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas turbine ceramic abradable coating includes a bond layer, a thermal barrier ceramic layer, and a porous ceramic abradable layer (hardness may be RC15Y: 80±3). A slit groove is provided in the porous ceramic abradable layer by machining. A width of a rectangular section of the ceramic abradable layer divided by the slit groove may be set to a range of 2 to 7 mm.

Abstract: The present invention provides a flux cored wire for gas shielded arc welding of high-strength steel having proof stress of 690 MPa or more, which is capable of all-position welding with a higher efficiency and exhibits an excellent cracking resistance. The flux cored wire comprising a steel sheath, and a flux filled therein, wherein the flux cored wire comprises, by mass % with respect to the total mass of the flux cored wire: C: 0.03 to 0.10%, Si: 0.25 to 0.7%, Mn: 1.0 to 3.0%, Ni: 1.0 to 3.5%, B: 0.001 to 0.015%, Cr: limited to 0.05% or less, and Al: limited to 0.05% or less, and in the flux, TiO2: 2.5 to 7.5%, SiO2: 0.1 to 0.5%, ZrO2: 0.2 to 0.9%, and Al2O3: 0.1 to 0.4%; and the remainder comprising: Fe, arc stabilizer, and unavoidable impurities; and wherein the total mount of hydrogen in the flux cored wire is in 15 ppm or less.

Abstract: A resistance bonding method comprises contacting a plurality of bonding members, which are electro-conductive, supplying current to the bonding members under a stress applied to a contact interface therebetween by means of plural electrodes in contact with the bonding members thereby to bond the members. The current supply is conducted by switching energizing paths. Part of the members is thermally expanded by current supply before one of the bonding members is contacted with other member, and the members in contact with each other are bonded by the second current supply.

Abstract: A metal laminate gasket is formed of at least three metal plates, i.e. first to third metal plates assembled together. A connecting portion is formed for partially connecting the first and second metal plates. The third metal plate has an opening located at a position facing the connecting portion for receiving the connecting portion therein. Thus, local pressure formed at the connection portion when the gasket is tightened is eliminated.

Abstract: A novel treatment method, for improving fatigue life, is provided that aims to resolve problems associated with conventional treatment methods for improving fatigue life of metal by reduction of stress concentration and conventional treatment methods for improving fatigue life of metal by introduction of compressive stress, that is, problems of poor efficiency in work execution, required level of skill of workers, and the impossibility of quality control due to lack of means for measuring the effect after treatment, characterized in that, for locations in metal for which fatigue is a problem, after pre-treatment is performed, ultrasonic impact treatment is performed, and thereafter, a quality assurance test is performed so as to improve the fatigue life of the metal.

Abstract: In a surface finishing method for a stainless steel material, excimer irradiation is made on a surface of the stainless steel material by emitting ultraviolet light to improve wetness. Then, a surface finishing is applied on the surface of the stainless steel material wherein the wetness is improved. In manufacturing a gasket, the stainless steel material or plate is cut in a predetermined shape, and holes and bead are formed in the metal formation plate. Then, the plate may be assembled with other plate.