Abstract: A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.

Abstract: A turbine blade according to the invention includes a first wall surface facing a cooling passage through which cooling air flows; a second wall surface facing a working fluid passage through which a working fluid flows; a communication hole establishing communication between the cooling passage and the working fluid passage; and a projection provided on the downstream side of the flowing direction of the cooling air in the opening of the communication hole formed in the first wall surface, the projection protruding from the first wall surface toward the cooling passage. The projection includes a slope section formed on the first wall surface that ascends in the direction opposite the flowing direction of the cooling air toward the cooling passage and a curved section formed as a convex section on the side of the cooling passage, the curved section extending along the opening in the form of an arc.

Abstract: A turbine blade according to the invention includes a first wall surface facing a cooling passage through which cooling air flows; a second wall surface facing a working fluid passage through which a working fluid flows; a communication hole establishing communication between the cooling passage and the working fluid passage; and a projection provided on the downstream side of the flowing direction of the cooling air in the opening of the communication hole formed in the first wall surface, the projection protruding from the first wall surface toward the cooling passage. The projection includes a slope section formed on the first wall surface that ascends in the direction opposite the flowing direction of the cooling air toward the cooling passage and a curved section formed as a convex section on the side of the cooling passage, the curved section extending along the opening in the form of an arc.

Abstract: The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade.

Abstract: A turbine rotor blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the blade and suppress degradation in performance even if cooling air mixes in toward the blade. The rotor blade is mounted to a rotor to form a turbine blade row rotating in a stationary member that includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is smaller on the downstream side than on the upstream side.

Abstract: A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.

Abstract: A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

Abstract: There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.

Abstract: The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade.

Abstract: A turbine rotor blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the blade and suppress degradation in performance even if cooling air mixes in toward the blade. The rotor blade is mounted to a rotor to form a turbine blade row rotating in a stationary member that includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is smaller on the downstream side than on the upstream side.

Abstract: A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.

Abstract: There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.

Abstract: Early detection of infectious agents of human prion diseases such as CJD by using an animal model, etc. is needed in order to rapidly determine prion infections in pharmaceuticals such as blood products, foods, or cosmetics. This invention provides a screening method for infectious agents of human or non-human prion diseases in samples, which employs, as an indication, the deposition of the aberrant prion protein in the follicular dendritic cell (FDC) of a non-human animal.

Abstract: Early detection of infectious agents of human prion diseases such as CJD by using an animal model, etc. is needed in order to rapidly determine prion infections in pharmaceuticals such as blood products, foods, or cosmetics. This invention provides a screening method for infectious agents of human or non-human prion diseases in samples, which employs, as an indication, the deposition of the aberrant prion protein in the follicular dendritic cell (FDC) of a non-human animal.

Abstract: Disclosed is a connector for detachably and rotatably connecting one article to another article, which comprises an insert member to be attached to said one article and a receiving member having a space for insertion of said insert member, which is to be attached to said another member, wherein said insert member has an engaging annular peripheral portion having a void or hollow at the center thereof, a pair of spherical projections capable of elastic and reversional deformation are arranged in the insertion space of the receiving member to confront each other, and such a dimensional relation is established between the engaging annular peripheral portion and the spherical projections that the distance between apexes of the spherical projections is smaller than the thickness of the engaging annular peripheral portion and when said insert member is inserted into the receiving member, the engaging annular peripheral portion is rotatably gripped and supported by the peripheral parts of the paired spherical projec

Abstract: Disclosed is a dust-controlling mat comprising tufted pile yarns containing fibers composed of a grafting product or polymer blend of polyvinyl alcohol and polyvinyl chloride and a dust adsorbing agent retained in the tufted pile yarns in an amount of 1 to 40% by weight based on the tufted piled yarns. This dust-controlling mat has an excellent dust-controlling property and a highly improved flame-proofing property in combination.

Abstract: An oil coater for mats which comprises a mat-supporting moving surface, a coating roller disposed above said mat-supporting moving surface and having on the periphery thereof a foam layer capable of being impregnated with an oiling composition, a press roller having a diameter smaller than the diameter of said coating roller and having on the periphery thereof a foam layer capable of being impregnated with an oiling composition, a first bearing mechanism which supports said press roller at a position upstream of said coating roller so that the top face of said press roller is substantially on the same horizontal plane with the top face of said coating roller and the degree of pressed contact between said coating roller and said press roller can be adjusted, a mat-feeding roller disposed below said mat-supporting moving surface, a second bearing mechanism which supports said feeding roller so that the axis of said feeding roller is substantially on the same vertical plane with the axis of said coating roller a