Abstract: Provided are a fibroin film having an electroconductive wiring pattern with high fixability, a sensor device, and a biological sensor device. Specifically, provided is an electroconductive film including: a base material containing fibroin; and electroconductive wiring containing a plurality of electroconductive particles, wherein the electroconductive wiring includes: a permeation portion formed of the electroconductive particles in a permeation layer in which the electroconductive particles have permeated the base material; and a non-permeation portion formed of the electroconductive particles prevented from permeating the base material.

Abstract: Provided are a fibroin aqueous solution excellent in storage stability and also excellent in foamability and a method of producing the same. The fibroin aqueous solution includes fibroin and a compound represented by the general formula (1) or (2).

Abstract: A gas turbine combustor according to at least one embodiment is a gas turbine combustor that includes: a tubular member; a plurality of premixing tubes circumferentially arranged on an inner side of the tubular member, each of the plurality of premixing tubes forming an outlet portion of a premixing passage; and a base plate for supporting the plurality of premixing tubes. The base plate has: a plurality of through holes disposed corresponding to the plurality of premixing tubes, respectively, and allowing the premixing passage to pass through the base plate; and a plurality of oblique holes extending obliquely with respect to an axial direction of the gas turbine combustor in a region different from a region where the through holes are disposed.

Abstract: An external additive for toner comprising: a fine particle A containing, as a binder component, an organosilicon compound having a siloxane bond; and a fine particle B that is present on a surface of the fine particle A in a state of being at least partially embedded in the surface of the fine particle A, wherein the external additive for toner (i) has a number-average particle diameter of a primary particle of 0.03 ?m or more and 0.30 ?m or less, and (ii) has a Young's modulus of 10 GPa or more and 30 GPa or less, wherein content ratios, on a number basis, of the following unit (a), unit (b), and unit (c) in the fine particle A based on all silicon atoms present in the fine particle A satisfy the following expressions (1) and (2). (a)+(b)+(c)?0.80??(1) (b)+(c)?0.

Abstract: The external additive for toner includes an external additive particle containing: a fine particle A; and a plurality of fine particles B that are each present so as to partially protrude from a surface of the fine particle A, wherein the fine particle A (i) is a particle of an organosilicon compound having a siloxane bond, (ii) has a number-average particle diameter of 0.03 ?m or more and 0.30 ?m or less, and (iii) has an average circularity of 0.90 or more, wherein, when the number-average particle diameter of the fine particle A is represented by DA, and a number-average particle diameter of the plurality of fine particles B is represented by DB, DB/DA is 0.10 or more and 0.63 or less.

Abstract: The external additive for toner includes an external additive particle containing: a base particle A; and a plurality of convex forming particles B each configured to form a convex portion on a surface of the base particle A. The base particle A and the convex forming particles B are particles each containing a silicon compound having a siloxane bond, and a chemical bond is formed between the base particle A and each of the convex forming particles B. The base particle A and the convex forming particles B each have a total content of the following unit (a), unit (b), and unit (c) of 80 mass % or more and 100 mass % or less: where R1 and R2 each represent an alkyl group having 1 or more and 6 or less carbon atoms.

Abstract: A gas turbine combustor according to at least one embodiment is a gas turbine combustor that includes: a tubular member; a plurality of premixing tubes circumferentially arranged on an inner side of the tubular member, each of the plurality of premixing tubes forming an outlet portion of a premixing passage; and a base plate for supporting the plurality of premixing tubes. The base plate has: a plurality of through holes disposed corresponding to the plurality of premixing tubes, respectively, and allowing the premixing passage to pass through the base plate; and a plurality of oblique holes extending obliquely with respect to an axial direction of the gas turbine combustor in a region different from a region where the through holes are disposed.

Abstract: A combustor includes: a fuel nozzle for injecting fuel; a combustion liner surrounding a combustion space for combusting the fuel and having an internal passage having an outlet communicating with the combustion space; and an air-fuel mixture line, connected to an inlet of the internal passage of the combustion liner, for introducing an air-fuel mixture containing the fuel and compressed air to the internal passage. The combustion liner is configured to be cooled by the air-fuel mixture flowing through the internal passage.

Abstract: A gas turbine combustor is equipped with a nozzle in which an air ejection passage extending along an axis and having an open distal end, and a fuel supply passage extending along the axis and having an open distal end are formed; swirling vanes provided around the nozzle so as to be twisted around the axis of the nozzle; an inner cylinder surrounding an outer periphery of the nozzle and the swirling vanes, and in which compressed air flows through an inside of the inner cylinder toward a downstream side; an outer cylinder which defines an inversion flow path, which inverts the compressed air on an outer periphery of the inner cylinder and introduces the compressed air to the inside of the inner cylinder, between the inner and outer cylinders; and an air introduction pipe having one end connected to a space on an upstream side of the compressed air from the inversion flow path, and the other end connected to the air ejection passage.

Abstract: A control device is a control device for a gas turbine including a plurality of combustors and is configured to select combustors to ignite in accordance with a target load on the basis of a predictor which defines a relationship between a load and the number and arrangement of combustors to ignite and a combustion temperature.

Abstract: External additive particles including a polymer containing a sulfur atom and a nitrogen atom, wherein the polymer includes a vinyl polymer moiety and a siloxane moiety, relative to a total number of carbon atoms, oxygen atoms, and silicon atoms constituting the external additive particles, a ratio of a number of the silicon atoms constituting the external additive particles is 4.0% or more and 25.0% or less, and in surfaces of the external additive particles analyzed by X-ray photoelectron spectroscopy, relative to a total number of carbon atoms, nitrogen atoms, oxygen atoms, silicon atoms, and sulfur atoms, a ratio of a number of the nitrogen atoms is 0.40% or more and 2.50% or less, and a ratio of a number of the sulfur atoms is 0.05% or more and 0.25% or less.

Abstract: A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which extends along the axis and through which first fuel is configured to flow, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and is configured to eject the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air is configured to flow, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and is configured eject the purge air from the center of the distal end.

Abstract: A combustor provided with: a nozzle having formed therein an air jet section that causes air to be jetted from a nozzle section; a cylindrical part covering the nozzle from the outer peripheral side thereof and forming an air flow path between the cylindrical part and the nozzle; and a pressure loss section provided to the air flow path. The pressure loss section causes a loss of pressure in the air that flows through the air flow path. The nozzle is provided with: at least one air inlet section that takes in air from an outer peripheral surface that is an upstream side from the pressure loss section; and a flow path-forming section forming a discharge air flow path that guides air that is taken in from the at least one air inlet section to the air jet section.

Abstract: A combustor includes: a fuel nozzle for injecting fuel; a combustion liner surrounding a combustion space for combusting the fuel and having an internal passage having an outlet communicating with the combustion space; and an air-fuel mixture line, connected to an inlet of the internal passage of the combustion liner, for introducing an air-fuel mixture containing the fuel and compressed air to the internal passage. The combustion liner is configured to be cooled by the air-fuel mixture flowing through the internal passage.

Abstract: A fuel injector including a fuel supply tube (8), a plurality of premix tubes (2), a support plate (3) which supports the fuel supply tube and the plurality of premix tubes, a substrate which supports downstream end portions of the plurality of premix tubes, an outer wall which is cylindrical, which forms a plenum (P) inside, a partition plate which partitions the plenum (P) into a fuel plenum (PF) and a cooling air plenum (PA), a baffle which partitions the cooling air plenum (PA) into an upstream cooling air plenum (PA1) and a downstream cooling air plenum (PA2) and has a plurality of cooling holes formed therein, and a cooling air supply tube configured to supply cooling air to the upstream cooling air plenum (PA1), in which the end portion on the downstream side of the fuel supply tube opens in the fuel plenum (PF), and a fuel introduction hole.

Abstract: A fuel injector including a fuel supply tube (8), a plurality of premix tubes (2), a support plate (3) which supports the fuel supply tube and the plurality of premix tubes, a substrate which supports downstream end portions of the plurality of premix tubes, an outer wall which is cylindrical, which forms a plenum (P) inside, a partition plate which partitions the plenum (P) into a fuel plenum (PF) and a cooling air plenum (PA), a baffle which partitions the cooling air plenum (PA) into an upstream cooling air plenum (PA1) and a downstream cooling air plenum (PA2) and has a plurality of cooling holes formed therein, and a cooling air supply tube configured to supply cooling air to the upstream cooling air plenum (PA1), in which the end portion on the downstream side of the fuel supply tube opens in the fuel plenum (PF), and a fuel introduction hole.

Abstract: A control device is a control device for a gas turbine including a plurality of combustors and is configured to select combustors to ignite in accordance with a target load on the basis of a predictor which defines a relationship between a load and the number and arrangement of combustors to ignite and a combustion temperature.

Abstract: A gas turbine combustor is equipped with a nozzle in which an air ejection passage extending along an axis and having an open distal end, and a fuel supply passage extending along the axis and having an open distal end are formed; swirling vanes provided around the nozzle so as to be twisted around the axis of the nozzle; an inner cylinder surrounding an outer periphery of the nozzle and the swirling vanes, and in which compressed air flows through an inside of the inner cylinder toward a downstream side; an outer cylinder which defines an inversion flow path, which inverts the compressed air on an outer periphery of the inner cylinder and introduces the compressed air to the inside of the inner cylinder, between the inner and outer cylinders; and an air introduction pipe having one end connected to a space on an upstream side of the compressed air from the inversion flow path, and the other end connected to the air ejection passage.

Abstract: A gas turbine provided with: a first nozzle including a first-nozzle radially inner fuel injection hole from which to inject a first-nozzle fuel and a first-nozzle radially outer fuel injection hole which is formed on a radially outer side of the first nozzle relative to the first-nozzle radially inner fuel injection hole and upstream of the first-nozzle radially inner fuel injection hole with respect to the flow of air inside a combustor and from which to inject the first-nozzle fuel, and in a case where the first-nozzle fuel is made of a moderate calorie fuel, the first-nozzle fuel is constantly injected from the first-nozzle radially inner fuel injection hole while the gas turbine is driven, and the first-nozzle fuel is constantly injected from the first-nozzle radially outer fuel injection hole while the gas turbine is driven at a rated rotation speed.

Abstract: A combustor nozzle includes a nozzle main body extending along an axis. The nozzle main body includes a first fuel passage which is formed along the axis and through which first fuel flows, a first fuel ejection passage which extends to an outer circumferential surface of the nozzle main body toward a distal end side thereof from the first fuel passage and ejects the first fuel from the outer circumferential surface, an air flow passage which extends in an axial direction on a radial outer side of the first fuel passage with respect to the axis and through which purge air flows, and an air ejection passage which extends from the air flow passage toward a center of a distal end of the nozzle main body and ejects the purge air from the center of the distal end.