Abstract: The present invention provides a gas turbine in which a proper clearance is kept between a rotor blade and a shroud for a long period of time from the operation start, so that damage to the rotor blade is less liable to occur. In a turbine portion of the gas turbine in accordance with the present invention, the rotor blade and the shroud face each other. At the tip end of the rotor blade is formed an abrasive layer, and on the inner peripheral surface of the shroud is formed a heat insulating layer. The abrasive layer is formed of a matrix and many abrasive particles dispersed in the matrix. The abrasive particles include protruding particles protruding from the matrix and embedded particles embedded in the matrix. In initial sliding of the rotor blade and the shroud at the early stage of operation, the inner peripheral surface of the shroud is ground by the protruding particles. After the protruding particles have disappeared, the inner peripheral surface of the shroud is ground by the embedded particles.

Abstract: A tip of rotor blade which rotates is an abradable surface. An inner wall of a shroud as a jacket for the rotor blade is an abrasive surface. A part of an abrasive particle protrudes from the abradable surface. When the tip of the rotor blade which rotates contacts the inner wall of the shroud, the protruding section of the abrasive particle slides with the abrasive surface so as to be ground. By doing this, a turbine which can maintain an appropriate clearance between the rotor blade and the shroud and can be used for a long period under high-temperature conditions with easy restoration and remaking thereof.

Abstract: The present invention is a thermal barrier coating method to form a thermal barrier coating by spray coating over the surface of a component where cooling holes are made. The thermal barrier coating is formed by spray coating after masking pins, which do not protrude above the surface of the component, are inserted into the cooling holes or masking pins protruding above the surface of the component are inserted and get shrunk due to heat while spray coating, obtaining the protruding amount equal to or less than the thickness of the thermal barrier coating after shrinkage, which characterizes the method. By way of this method, a thermal barrier coating can be formed all over the surface without clogging the cooling holes.

Abstract: The present invention provides an abrasion-resistant coating which has high oxidation resistance and durability and can be applied easily at a low cost. The abrasion-resistant coating in accordance with the present invention is formed at the tip end of a base material forming a gas turbine blade. The abrasion-resistant coating at the tip end has a thickness of 300 microns. On the tip end, hard particles H consisting of CBN are fixed in a bond coating formed by heating, melting, and solidification of a mixture of a brazing filler metal and M—Cr—Al—Y (M designates a metal element such as Co and Ni). The hard particles H are Ni and Co coated to improve wettability relative to the brazing filler metal, and are arranged so that some of them are partially protruded from the surface of bond coating to exhibit the grindability.

Abstract: The method of the present invention comprises a steps of performing nickel strike plating onto a base material, thereby forming a first plating layer, performing nickel plating, in which alloy particles containing at least Cr, Al and Y are dispersed, onto the first plating layer, thereby forming a second plating layer, performing nickel plating, in which alloy particles containing at least Cr, Al and Y and hard particles are dispersed, on the second plating layer, thereby forming a third plating layer, performing plating, in which alloy particles containing at least Cr, Al and Y are dispersed, onto the third plating layer, thereby forming a fourth plating layer such that the hard particles of the third plating layer are partly exposed, and performing intermediate heating process to the plating layers to diffuse the alloy particles throughout the plating layers, thereby forming an alloy layer.

Abstract: A storage device including a storage medium having a data area configured to write content data therein and an identifier area configured to write an identifier therein, and a storage medium support frame configured to hold the storage medium and provided with visible information that corresponds to the identifier, the visible information being visible from the outside and selected from the group consisting of a character, symbol, pattern, color, and combination of a character, symbol, pattern, and color.

Abstract: A tip plug is capped on a boss section so as to fit to a hole which is used for detaching a core which is formed in a blade tip section of the gas turbine blade. A butt-section T is melted so as to form a butt-welding section by using a YAG laser beamthere; thus, the hole is plugged by the tip plug. Also, parameters such as an interval between the butt-section T, a member for forming the tip plug, condition for a laser welding operation, and a defocus position of the laser beam are optimized. By doing this, it is possible to control the entering heat amount and prevent the solidification cracking and the liquation cracking reliably. Furthermore, it is possible to melt and weld the butt-welding section more strongly by using a laser having a narrow bead width; thus, it is possible to improve the manufacturing process efficiently and produce a product in uniform quality repeatedly.

Abstract: The invention relates to a thermal barrier coating material for coating a gas turbine member that provides a higher thermal barrier property and a higher peeling resistance. In a first aspect of the invention, a metal binding layer 22 and a porous ZrO2-based ceramic layer 23 are laminated successively on a base material 21, and microcracks that extend in the thickness direction are formed in the ceramic layer 23. After laminating the ceramic layer 23 on the metal binding layer 22 by thermal spraying, etc., microcracks 24 are formed by irradiating with a laser beam a surface of the ceramic layer 23 and thereby heating the surface of the ceramic layer 23 at 1000° C. to 1700° C., while cooling the rear surface of the base material 21. Thus, microcracks 24 are formed by a heating and cooling cycle.

Abstract: 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° C.

Abstract: There are provided for an improved card connector contacting structure featuring its compactness and simplicity in construction, higher reliability of contacting action and higher impact resistance. The contacting structure is designed as a card connector comprising a plurality of contact terminals which are arranged in parallel with one another; among the plurality of contact terminals, at least two are the terminals for connecting with the power source; at least two are the terminals for grounding; at least one is for detecting whether the IC card has been loaded securely into the card connector; among the plurality of contact terminals, one of the terminals for grounding comes into contact first with the corresponding external contact of the IC card, among the plurality of contact terminals, the terminal for detecting the card coming into contact last with the corresponding external contact of the IC card.

Abstract: The present invention provides a gas turbine in which a proper clearance is kept between a rotor blade and a shroud for a long period of time from the operation start, so that damage to the rotor blade is less liable to occur. In a turbine portion of the gas turbine in accordance with the present invention, the rotor blade and the shroud face each other. At the tip end of the rotor blade is formed an abrasive layer, and on the inner peripheral surface of the shroud is formed a heat insulating layer. The abrasive layer is formed of a matrix and many abrasive particles dispersed in the matrix. The abrasive particles include protruding particles protruding from the matrix and embedded particles embedded in the matrix. In initial sliding of the rotor blade and the shroud at the early stage of operation, the inner peripheral surface of the shroud is ground by the protruding particles. After the protruding particles have disappeared, the inner peripheral surface of the shroud is ground by the embedded particles.

Abstract: At first, a brazing filler metal sheet is prepared (step S1). The brazing filler metal sheet comprises a brazing filler metal layer, a sticking material layer, and a released paper. The brazing filler metal layer comprises a brazing filler metal. A coating material layer is laminated on the brazing filler metal layer (step S2). The coating material layer comprises a mixture of coating material particles and a binder. As the coating material particles, MCrAlY particles and abrasive particles (cubic boron nitride particles or the like) are used. The coating material layer is then dried (step S3), and the brazing filler metal sheet is cut (step S4), and adhered to a rotor blade (step S5). The rotor blade is heated (step S6), to melt the brazing filler metal. The brazing filler metal gets wet as a liquid phase around the MCrAlY particles, and diffuses due to the heat treatment holding process. A solidified layer is then formed by cooling (step S7).

Abstract: An IC card includes a base card and a semiconductor integrated circuit device package. The semiconductor integrated circuit device package has one surface and the other surface disposed opposite to the one surface. In one surface, a plurality of card terminals which can re-contact terminals of an electronic device are disposed. The base card includes a concave portion. The other surface is attached to a bottom of the concave portion of the base card.

Abstract: The present invention provides an abrasion-resistant coating which has high oxidation resistance and durability and can be applied easily at a low cost. The abrasion-resistant coating in accordance with the present invention is formed at the tip end of a base material forming a gas turbine blade. The abrasion-resistant coating at the tip end has a thickness of 300 microns. On the tip end, hard particles H consisting of CBN are fixed in a bond coating formed by heating, melting, and solidification of a mixture of a brazing filler metal and M-Cr—Al—Y (M designates a metal element such as Co and Ni). The hard particles H are Ni and Co coated to improve wettability relative to the brazing filler metal, and are arranged so that some of them are partially protruded from the surface of bond coating to exhibit the grindability.

Abstract: A tip of rotor blade which rotates is an abradable surface. An inner wall of a shroud as a jacket for the rotor blade is an abrasive surface. A part of an abrasive particle protrudes from the abradable surface. When the tip of the rotor blade which rotates contacts the inner wall of the shroud, the protruding section of the abrasive particle slides with the abrasive surface so as to be ground. By doing this, a turbine which can maintain an appropriate clearance between the rotor blade and the shroud and can be used for a long period under high-temperature conditions with easy restoration and remaking thereof.