Abstract: A gas turbine having a rotor driven by a shaft with a cooling medium passageway therein has a heat shield pipe portion mounted inside the passageway which forms an air layer with a wall of the passageway to protect a bearing member metal supporting the shaft from the heat of a cooling medium and a seal shaft portion for forming a labyrinth seal to prevent leakage of the cooling medium are formed as one piece and constitute a heat shied seal pipe.

Abstract: Spherical tetragonal barium titanate particles of the present invention have a perovskite crystal structure, an average particle diameter of 0.05 to 0.5 ?m, a particle size distribution ?g of not less than 0.70, and a ratio of Ba to Ti of 0.99:1 to 1.01:1. The spherical tetragonal barium titanate particles exhibit an excellent dispersibility as well as a high denseness, a high purity and excellent permittivity properties.

Abstract: An adjustment method for an image forming device, for adjusting image forming condition with respect to a sheet by using image forming means. The adjustment operation is performed in such a manner that: a first image, that is used for detecting scanning error of an image scanning device, is formed on an image carrying body and then transferred from the image carrying body to the sheet, the first image being formed over at least three corners of the sheet while extending outside the sheet. The sheet with the first image is scanned by the image scanning device to figure out a scanning error amount of the image scanning device, and a correction value of image forming condition of the image forming means is found in consideration of the scanning error amount. The image forming condition with respect to the sheet is modified based on the correction value.

Abstract: Spherical tetragonal barium titanate particles of the present invention have a perovskite crystal structure, an average particle diameter of 0.05 to 0.5 &mgr;m, a particle size distribution &sgr;g of not less than 0.70, and a ratio of Ba to Ti of 0.99:1 to 1.01:1. The spherical tetragonal barium titanate particles exhibit an excellent dispersibility as well as a high denseness, a high purity and excellent permittivity properties.

Abstract: In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades and to prevent the cooling air from leaking into the junction, the holes in the radial direction and the cooling air supply holes are interconnected and the supply members covering the junction are fit into them. The cooling air after cooling the second stage moving blades is introduced into the collection holes formed in the outer periphery of the spacer via the cooling air collection holes and to prevent the cooling air from leaking into the boundary, the cooling air collection holes and collection holes are interconnected and the collection members covering the boundary are fit into them.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A plurality of first base images are formed from a base color output in accordance with a predetermined adjustment value. A plurality of first correction images are formed on the first base images from a correction color to be a subject for correction output in accordance with a predetermined adjustment value. The first correction images are displaced within a predetermined range. The first adjustment value is determined from changed adjustment values. The second base images are formed from the base color output in accordance with the predetermined adjustment value, and the second correction images are formed from the correction color output in accordance with a plurality of adjustment values determined based on the first adjustment value. The second adjustment value having an extreme is determined from a plurality of adjustment value candidates. Finally, the adjustment value for the correction color is corrected to the determined second adjustment value.

Abstract: In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades. The holes in the radial direction and the cooling air supply holes are interconnected and supply members covering the connection are installed. The cooling air after cooling the second stage moving blades is introduced into collection holes formed in the outer periphery of the spacer via the cooling air collection holes. The cooling air collection holes and collection holes are interconnected and collection members covering the connection are installed. To make the sum of minimum sectional areas of the respective paths of the second stage moving blades smaller than the sum of minimum sectional areas of the respective paths of the first stage moving blades, a minimum sectional member is incorporated into the supply member.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A heat shield pipe portion 12a formed in an air layer 21 to protcet a bearing member metal 16 from the heat of a cooling medium 16 and a seal shaft portion 12c for forming a labyrinth seal 14 to prevent a leakage of the cooling medium arc formed with one piece and they form a heat shield seal pipe 12. A component number for installing the components to a rear portion shaft 105 can be arranged as one and also a bolt connection portion can be deleted. Namely, the bearing member metal 16 can be constituted to protect the bearing member metal from the heat of the cooling medium and the construction of the gas turbine can be simple and the manufacture thereof performs easily and further during the operation time the generation of the vibrations according to the centering displacement can be reduced.

Abstract: A gas turbine having a rotor driver by a shaft with a cooling medium passageway therein has a heat shield pipe portion mounted inside the passageway which forms an air layer with a wall of the passageway to protect a bearing member metal supporting the shaft from the heat of a cooling medium and a seal shaft portion for forming a labyrinth seal to prevent leakage of the cooling medium are formed as one piece and constitute a heat shied seal pipe.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: In a gas turbine having a structure of collecting a refrigerant after cooling the moving blades, a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members are alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant after cooling the moving blades flows are installed in the spacer members, and the first flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and the second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.

Abstract: A fixed station and an on-board apparatus are constructed to carry out a short range communication. The on-board apparatus specifies an application from a command included in reception data received from the fixed station and starts a corresponding processing, when an acquired command is a menu selection command. A menu including commodities and charges are displayed. When a selected item is determined, the determined content is displayed. When an IC card unit receives an IC card for settling the charge, the charge is settled by rewriting the IC card by data exchange via wireless communication. A short range wireless unit is used to ensure individuality of the communication. This short range communication may also be used at a vehicle repair shop, at a curved corner on a travel path or the like.

Abstract: A control center calculates boarding ratio based on operating state information (‘out-of-service,’ ‘empty,’ ‘pickup,’ and ‘serving’) that is received from taxis. It then determines whether the boarding ratio is less than a predetermined ratio. If the boarding ratio is less than the predetermined ratio, the control center notifies discount information for starting of discount operation where a taxi fare is reduced from a normal fare, to the taxis, a taxi stand, and a website on the internet. Notification of the discount information to general public enhances intension that the general public would like to take the taxis. The taxi company and taxi driver can thus expect increase of taxi customers.

Abstract: A turbine rotor includes a plurality of moving blades having cooling paths through which a refrigerant flows inside, a plurality of wheels having the moving blades mounted in the outer periphery thereof and at least one spacer member installed between the wheels. The spacer member has a plurality of flow paths through which a refrigerant flows after cooling the moving blades. The plurality of flow paths have flow paths interconnecting to the cooling paths in the moving blades on a first wheel adjacent the spacer member and interconnecting to a space formed on a side wall surface with which a second wheel adjacent the spacer member and the spacer member are in contact.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades and to prevent the cooling air from leaking into the junction, the holes in the radial direction and the cooling air supply holes are interconnected and the supply members covering the junction are fit into them. The cooling air after cooling the second stage moving blades is introduced into the collection holes formed in the outer periphery of the spacer via the cooling air collection holes and to prevent the cooling air from leaking into the boundary, the cooling air collection holes and collection holes are interconnected and the collection members covering the boundary are fit into them.

Abstract: A turbine rotor comprises first and second wheels each having turbine blades fixed to a peripheral portion thereof, and a spacer arranged so as to be sandwiched between the first and second wheels, and is characterized in that in a partitioning member is provided between the spacer and at least one of the first and second wheels, coolant paths in which coolant for cooling the turbine blades flows are provided inside the turbine blades, and a cavity formed by the partitioning member and the spacer is provided in a recovery course through which the coolant passed through the coolant paths is exhausted from the turbine blades. A gas turbine comprising the turbine rotor as mentioned above and a cooling method of the turbine rotor are disclosed.