Abstract: Provided are a variable geometry turbine and a turbocharger with the same. The variable geometry turbine is provided with a turbine impeller, a housing, a plurality of nozzle vanes, and a link mechanism. Inside the housing, a link compartment in which the link mechanism is accommodated is formed, the link compartment being separated from a nozzle flow path by a hub-side member having a hub side surface defining the nozzle flow path. The link mechanism and each of the plurality of nozzle vanes are coupled together via a nozzle shaft penetrating through the hub-side member. The hub-side member has at least one communication hole providing communication between the nozzle flow path and the link compartment. When each of the plurality of nozzle vanes is fully opened, the opening of the at least one communication hole on the nozzle flow path side is formed on the inner side radially of the turbine impeller than the leading edge of each of the plurality of nozzle vanes.

Abstract: A variable geometry turbine includes a variable nozzle unit for adjusting a flow of exhaust gas in an exhaust gas passage for introducing exhaust gas to the turbine rotor. The variable nozzle unit includes a plurality of nozzle vanes disposed in the exhaust gas passage at intervals in the circumferential direction of the turbine rotor. When the exhaust gas passage is divided into a near-tongue region in the vicinity of a tongue portion of the scroll passage and a far-tongue region which is a region other than the near-tongue region, the plurality of nozzle vanes includes at least one near-tongue nozzle vane disposed in the near-tongue region and at least one far-tongue nozzle vane disposed in the far-tongue region. The at least one near-tongue nozzle vane has, in at least one of a leading edge or a trailing edge of the near-tongue nozzle vane, a notch that is cut out to a greater extent than a leading edge or a trailing edge of the far-tongue nozzle vane.

Abstract: An antigen protection method for enabling delayed sample processing may include: fixing a sample; embedding the sample; sectioning the sample and placing a section of the sample in contact with a microscope slide to produce a sectioned sample; de-embedding the sectioned sample; optionally rehydrating the sectioned sample; performing target retrieval on the sectioned sample; and optionally performing target visualization on the sectioned sample. The method may further include the steps of: applying a protecting reagent onto the sectioned sample; drying the protecting reagent; and waiting a period of time, such as greater than six hours, and these steps may be performed after the de-embedding step, rehydrating step, and/or target retrieval step.

Abstract: A variable geometry turbine includes: a turbine rotor; a scroll passage forming part which forms a scroll passage; an exhaust gas passage forming part which forms an exhaust gas passage for introducing an exhaust gas from the scroll passage to the turbine rotor; and a variable nozzle unit including a plurality of nozzle vanes disposed in the exhaust gas passage and configured to be rotatable about respective rotation centers. The exhaust gas passage forming part includes: a first plate member having an annular first plate part; and a second plate member having an annular second plate part which defines the exhaust gas passage between the first plate part and the second plate part and is disposed closer to a turbine outlet than the first plate part in an axial direction of the turbine rotor.

Abstract: A variable geometry turbine includes a variable nozzle unit for adjusting a flow of exhaust gas in an exhaust gas passage for introducing exhaust gas to the turbine rotor. The variable nozzle unit includes a plurality of nozzle vanes disposed in the exhaust gas passage at intervals in the circumferential direction of the turbine rotor. When the exhaust gas passage is divided into a near-tongue region in the vicinity of a tongue portion of the scroll passage and a far-tongue region which is a region other than the near-tongue region, the plurality of nozzle vanes includes at least one near-tongue nozzle vane disposed in the near-tongue region and at least one far-tongue nozzle vane disposed in the far-tongue region. The at least one near-tongue nozzle vane has, in at least one of a leading edge or a trailing edge of the near-tongue nozzle vane, a notch that is cut out to a greater extent than a leading edge or a trailing edge of the far-tongue nozzle vane.

Abstract: A central system coupled to a subsystem receives a fault indication associated with a fault in one or more circuits of the subsystem from a local fault collection and control (FCCS) of the subsystem when a software recovery of the fault fails. Based on the received fault indication, the local FCCS and a central FCCS of a central system is masked from additional fault indications from the one or more circuits. The central system then signals the reset of the one or more circuits of the subsystem after the masking of the additional fault indications, wherein the one or more circuits is reset based on the signaling and the additional faults are masked from one or more of the local FCCS and central FCCS during the reset.

Abstract: A variable nozzle device 20 for a variable geometry turbocharger includes: a nozzle mount 21; a nozzle plate 22 disposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passage 4 having an annular shape between the nozzle plate 22 and the nozzle mount 21; and a plurality of variable nozzle vanes 6 disposed at a predetermined interval in a circumferential direction of the nozzle flow passage 4 so as to be individually rotatable about a pivot axis O2. The nozzle plate 22 includes a first surface 33 facing the nozzle mount 21, a second surface 34 opposite to the first surface 33, and at least one through hole 36 formed through the first surface 33 and the second surface 35.

Abstract: Improved biotin blocking methods are provided which utilize a high-affinity monomeric biotin-binding protein of the avidin family that have only a single biotin binding site. Because the biotin-binding protein is monovalent, it can be applied as a single reagent. Since it does not introduce any additional biotin binding sites, as would be the case with native tetrameric streptavidin, no further blocking of biotin binding sites is necessary. Furthermore, because it is a single reagent, it can be combined with other steps such as the peroxidase blocking step, and both endogenous peroxidase and endogenous biotin can be blocked simultaneously. The biotin blocking methods may be used in the performance of immunoassays, such as tissue sample containing endogenous biotin is stained by IHC to detect a specific analyte. Prior to staining, the tissue is first blocked for endogenous biotin, according to the present invention, by the application of a high-affinity biotin-binding protein.

Abstract: A variable geometry turbine includes: a turbine rotor; a scroll passage forming part which forms a scroll passage; an exhaust gas passage forming part which forms an exhaust gas passage for introducing an exhaust gas from the scroll passage to the turbine rotor; and a variable nozzle unit including a plurality of nozzle vanes disposed in the exhaust gas passage and configured to be rotatable about respective rotation centers. The exhaust gas passage forming part includes: a first plate member having an annular first plate part; and a second plate member having an annular second plate part which defines the exhaust gas passage between the first plate part and the second plate part and is disposed closer to a turbine outlet than the first plate part in an axial direction of the turbine rotor.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a fin disposed on at least one of a pressure surface or a suction surface of the nozzle vane body and disposed within a range of 0.6L from a trailing edge of the nozzle vane body, where L refers to a chord length of the nozzle vane body. The fin satisfies a relationship of 0.3L?X, where X refers to a length of the fin along a chord direction of the nozzle vane body.

Abstract: A sample protection method is provided which may be used for protecting a biological sample on a microscope slide, such as during heat-induced target retrieval and/or after heat-induced target retrieval such that: 1) the sample remains adherent to the microscope slide; and 2) the microscopic morphology of the biological sample remains intact. In some embodiments, the sample protection method may include the steps of: creating a sectioned sample that is in contact with a microscope slide; applying a protecting reagent onto a sectioned sample that is in contact with a microscope slide and drying the protecting reagent in which the protecting reagent may be both applied and dried onto the sectioned sample before and/or after performing target retrieval on the sectioned sample. The protecting reagent may include a water-soluble polymer and/or a water-soluble wax, such as polyethylene glycol, polypropylene glycol, polyvinyl alcohol, polyvinylpyrrolidone, alginic acid, and carrageenan.

Abstract: A variable nozzle device 20 for a variable geometry turbocharger includes: a nozzle mount 21; a nozzle plate 22 disposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passage 4 having an annular shape between the nozzle plate 22 and the nozzle mount 21; and a plurality of variable nozzle vanes 6 disposed at a predetermined interval in a circumferential direction of the nozzle flow passage 4 so as to be individually rotatable about a pivot axis 02. The nozzle plate 22 includes a first surface 33 facing the nozzle mount 21, a second surface 34 opposite to the first surface 33, and at least one through hole 36 formed through the first surface 33 and the second surface 35.

Abstract: A nozzle vane for a variable geometry turbocharger satisfies 0.45<(Xp/L)?0.60, where L is a chord length of the nozzle vane, and Xp is a distance between a leading edge of the nozzle vane and a rotation center of the nozzle vane.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a flange portion provided on at least one of a shroud-side end surface or a hub-side end surface of the nozzle vane body, and formed around a center of rotation of the nozzle vane body.

Abstract: A method to produce a rapid immunohistochemical detection of an antigen from a biological sample is provided. Preferably, the method may be used for rapid immunohistochemical staining of a biological sample that allows completion of the staining process in less than ten minutes, such as during a cancer removal procedure. In some embodiments, the method may include the steps of: depositing a section of the biological sample on a slide; permeabilizing the section of the biological sample; incubating the section of the biological sample with a secondary antibody having a detectable label; removing unbound secondary antibody from the section of the biological sample; mounting the section of the biological sample; and detecting secondary antibody bound to the section of the biological sample.

Abstract: A radial inflow turbine includes a scroll flow passage, a turbine wheel disposed radially inward of the scroll flow passage, a plurality of variable nozzle vanes disposed on a flow passage extending from the scroll flow passage toward the turbine wheel, at a radial position between the scroll flow passage and the turbine wheel, a nozzle mount rotatably supporting each of the plurality of variable nozzle vanes, a nozzle plate arranged to face the nozzle mount and forming the flow passage with the nozzle mount, and a swirl generating member disposed, radially outward of the plurality of variable nozzle vanes, on the nozzle plate in a height range which is smaller than that of a vane height of each of the plurality of variable nozzle vanes. A position of an end part of the swirl generating member on a side of the nozzle mount is farther away from the nozzle mount than a position of an end part of each of the plurality of variable nozzle vanes on the side of the nozzle mount in an axial direction.

Abstract: A nozzle vane for a variable geometry turbocharger has an airfoil including a leading edge, a trailing edge, a pressure surface, and a suction surface at least in a center position in a blade height direction. The airfoil satisfies 0?Wmax/L<0.03, where Wmax is a maximum value of a distance from a line segment connecting the trailing edge and a fixed point on the pressure surface at a 40% chord position from the trailing edge toward the leading edge to a given point on the pressure surface between the trailing edge and the fixed point, and L is a length of the line segment.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a flange portion provided on at least one of a shroud-side end surface or a hub-side end surface of the nozzle vane body, and formed around a center of rotation of the nozzle vane body.

Abstract: A nozzle vane of a variable geometry turbocharger comprises: a nozzle vane body rotatably disposed in an exhaust gas passage defined between a shroud surface and a hub surface; and a fin disposed on at least one of a pressure surface or a suction surface of the nozzle vane body and disposed within a range of 0.6L from a trailing edge of the nozzle vane body, where L refers to a chord length of the nozzle vane body. The fin satisfies a relationship of 0.3L?X, where X refers to a length of the fin along a chord direction of the nozzle vane body.

Abstract: A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller, and including a scroll passage positioned on an outer circumferential side of the turbine impeller and an inner circumferential wall part defining an inner circumferential boundary of the scroll passage; a plurality of nozzle vanes disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; and a plate disposed on a side of the intermediate flow passage with respect to the inner circumferential wall part so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction. The plate has at least one through hole through which the intermediate flow passage and the gap are communicated with each other.