Abstract: An image processor of a display device includes: an image sticking object detector which classifies a class of an input image data and outputs inference data including image sticking object information based on the classified class; a memory which stores previous inference data; a post-processor which calculates accumulative inference data, based on the inference data and the previous inference data received from the memory and generates corrected inference data, based on the accumulative inference data; and an image sticking prevention part which outputs an image data subjected to an image sticking prevention process, based on the corrected inference data.

Abstract: A combustor for a gas turbine, includes: a first fuel nozzle group and a second fuel nozzle group each of which includes a fuel nozzle capable of supplying a fuel and has an independently controllable fuel supply system; a cylinder inside which a combustion region allowing a combustion gas produced by combustion of the fuel to flow is formed; and a first contraction portion extending partially along a circumferential direction so as to correspond to one of the first fuel nozzle group or the second fuel nozzle group and protruding radially inward from an inner peripheral surface of the cylinder.

Abstract: A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: a fuel nozzle for injecting the fuel; a mixing passage supplied with the fuel and the air; and a support portion connecting a passage wall of the mixing passage and the fuel nozzle to support the fuel nozzle.

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 combustion tube for a gas turbine including an outlet section having a cross-section of an annular sector-shape. The outlet section includes an outer wall forming an outer peripheral boundary of the annular sector-shape, an inner wall forming an inner peripheral boundary of the annular sector-shape, and a pair of side walls forming boundaries on both sides of the annular sector-shape in a circumferential direction, respectively. The outer wall extends obliquely with respect to the inner wall such that a height of the annular sector-shape decreases toward an outlet opening of the combustion tube. A first side wall extends obliquely with respect to a second side such that a perimeter of the annular sector-shape increases toward the outlet opening of the combustion tube. An inclination angle ?1 of the first side wall with respect to the second side wall satisfies 0<?1?56.

Abstract: The upstream-side wall portion 54 includes, in the circumferential direction thereof, a first region 31 where air inlets 30 are formed at a lower density, and a second region 32 which is disposed at a position offset from the first region 31 in the circumferential direction, and in which the air inlets 30 are formed at a higher density than in the first region 31.

Abstract: A fuel injector has a body extending in an axial direction. The body includes: an axial passage formed so as to extend in the axial direction; a radial passage formed so as to communicate at one end with the axial passage and to open at another end to an outer surface of the body; and an internal passage including a first opening and a second opening open to the outer surface, and formed so as to extend inside the body from the first opening to the second opening. The first opening and the second opening are located opposite to each other across a third opening, through which the radial passage opens to the outer surface, in a circumferential direction centered on an axis of the body.

Abstract: A combustion tube for a gas turbine including an outlet section having a cross-section of an annular sector-shape. The outlet section includes an outer wall forming an outer peripheral boundary of the annular sector-shape, an inner wall forming an inner peripheral boundary of the annular sector-shape, and a pair of side walls forming boundaries on both sides of the annular sector-shape in a circumferential direction, respectively. The outer wall extends obliquely with respect to the inner wall such that a height of the annular sector-shape decreases toward an outlet opening of the combustion tube. A first side wall extends obliquely with respect to a second side such that a perimeter of the annular sector-shape increases toward the outlet opening of the combustion tube. An inclination angle ?1 of the first side wall with respect to the second side wall satisfies 0<?1?56.

Abstract: A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: a fuel nozzle for injecting the fuel; a mixing passage supplied with the fuel and the air; and a support portion connecting a passage wall of the mixing passage and the fuel nozzle to support the fuel nozzle.

Abstract: A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each of the at least one fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each of the at least one fuel nozzle includes at least one fuel injection hole formed on a side surface of the protruding portion. A top surface of the protruding portion includes a convex curved surface.

Abstract: A combustor includes a fuel supply unit defining on a radially inner side of an axis an inner peripheral side space into which inert gas is introduced and which is configured to supply the inert gas to a combustion cylinder, and defining on a radially outer side an outer peripheral side space into which the inert gas is introduced and which is configured to supply the inert gas to the combustion cylinder; an inner peripheral side oxygen supply unit that is configured to supply oxygen to the inner peripheral side space; an outer peripheral side oxygen supply unit that is configured to supply oxygen to the outer peripheral side space; and an adjustment unit that is configured to adjust the relative amounts of the oxygen supplied by the inner peripheral side oxygen supply unit and the oxygen supplied by the outer peripheral side oxygen supply unit.

Abstract: A resonant sound absorbing device of a gas turbine combustor includes a plurality of resonance chambers independently disposed side by side in an axial direction of the gas turbine combustor so as to communicate with a gas passage of the gas turbine combustor via acoustic holes. The plurality of resonance chambers include n related resonance chambers each satisfying: 0.9 × ? i = 1 n ? F i n ? F i ? 1.1 × ? i = 1 n ? F i n ( A ) where n is an integer of 2 or more, and Fi is a peak frequency corresponding to a maximum sound absorbing ratio of the ith related resonance chamber of the n related resonance chambers.

Abstract: A gas turbine combustor provided with: a plurality of swirler tubes that are disposed inside a combustor basket and impart a swirl to a premixed gas, the premixed gas being obtained by premixing a fuel and air for combustion; and an outer ring that is disposed between the plurality of swirler tubes and the combustor basket with a gap provided between the outer ring and the combustor basket, and generates film-shaped air inside a combustor transition piece connected to the combustor basket via injection through the gap into the combustor transition piece, and at a downstream end of the outer ring, the outer ring includes a tapered surface formed such that the outer ring gradually decreases in thickness from an upstream side toward a downstream side.

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 first cylindrical body which is configured to hold a fuel nozzle extending in an axial line direction and through which air flows toward a downstream side thereof; a second cylindrical body that is connected to a downstream side of the first cylindrical body; and an outer shell that has an inner peripheral surface configured to define an air introduction channel through which air is introduced such that the air reverses course at an upstream end of the first cylindrical body and flows toward the downstream side together with an outer peripheral surface of the first cylindrical body. The inner peripheral surface has an outside narrowing surface that is formed to extend inward in a radial direction toward the upstream end of the first cylindrical body.

Abstract: A burner assembly for a combustor includes: a plurality of first nozzles arranged in a circumferential direction of the combustor; a plurality of first burner cylinders accommodating the respective first nozzles; and a middle-flow-passage forming portion which is connected to a downstream end of the plurality of first burner cylinders and which forms a middle flow passage through which a combustion chamber of the combustor is in communication with an interior space of each of the plurality of first burner cylinders. The middle-flow-passage forming portion includes an inner peripheral wall disposed on a radially inner side of the combustor and formed such that a distance from a center axis of the combustor to the inner peripheral wall is uneven with respect to the circumferential direction.

Abstract: A combustor includes a nozzle, a burner cylinder surrounding the outer circumference of the nozzle, and an outside flow path cylinder surrounding the outer circumference of a downstream end portion of the burner cylinder. A purge air flow path through which air flows is formed between the inner circumferential side of the outside flow path cylinder and the outer circumferential side of the burner cylinder. A tapered surface is formed in the downstream end portion of the burner cylinder such that the plate thickness of a burner cylinder-forming plate that forms the burner cylinder gradually thins toward the downstream side.

Abstract: There is provided a gas turbine (1) including a compressor (2) that generates compressed air, a casing (5) into which the compressed air is introduced, a combustor (3) that generates a combustion gas, a turbine (4) that is driven by the combustion gas, a combustor cooling system (6) that has a sub-compressor (62), which is able to be operated independently of the compressor (2), and a heat exchanger (61), which extracts air in the casing (5) and causes the air to exchange heat after the sub-compressor (62) has increased a pressure of the air, and that introduces the air, which has exchanged heat, into a cooling passage (31) of a cylindrical body (30) of the combustor (3), and a combustor air introducing system that extracts air flowing in the combustor cooling system (6) and introduces the air into the combustor (3).

Abstract: A fuel nozzle for a gas turbine is a diffusion combustion type fuel nozzle for a gas turbine, including a nozzle body, a plurality of nozzle holes arranged along a circumferential direction of the nozzle body, each of the nozzle holes extending along an axial direction of the nozzle body and having a center axis inclined toward a center axis of the nozzle body downstream in the axial direction of the nozzle body, and a plurality of fuel supply holes extending along the axial direction of the nozzle body and connected to the plurality of nozzle holes to serve as fuel supply paths for supplying fuel, respectively. Each of the nozzle holes has an injection opening for injecting the fuel to a downstream end portion in the axial direction of the nozzle body.

Abstract: A combustor (3) includes a plurality of first burners extending along an axis (P) and arranged at intervals in the circumferential direction, a base plate (31) having support openings configured to support the plurality of first burners and a plurality of through-holes (34) through which base plate air flows toward a downstream side, a plurality of extension pipes supported by the base plate (31) to correspond to the first burners and configured to guide a pre-mixed gas ejected from the first burners toward the downstream side, and a base plate air guide section (35) configured to change a direction of at least some of the base plate air ejected from the through-holes (34) at a downstream side of the base plate (31).