Abstract: This gas turbine equipment comprises a gas turbine and a control device. A combustor of the gas turbine uses ammonia as fuel, and uses the RQL method. A compressor of the gas turbine includes an intake adjustor that adjusts an intake rate which is the flow rate of air that flows into a compressor casing. When the concentration of NOx in exhaust gas reaches or exceeds a predetermined value, the control device controls the operation of the intake adjustor so that the intake rate decreases.

Abstract: Provided is a fuel supply system including a main ammonia line through which liquid ammonia flows; a vaporizer connected to an end of the main ammonia line and configured to heat and vaporize the liquid ammonia via heat exchange between a heating medium and the liquid ammonia; a gaseous ammonia line connected to the vaporizer, the gaseous ammonia line configured to guide a gaseous ammonia, which is ammonia vaporized by the vaporizer, as fuel to a combustor of a gas turbine; a liquid ammonia line configured to guide liquid ammonia which has not undergone heat exchange with the heating medium at the vaporizer as fuel to the combustor; and a switching device configured to switch an ammonia supply state between a first state in which the gaseous ammonia is guided from the gaseous ammonia line to the combustor and a second state in which the liquid ammonia is guided from the liquid ammonia line to the combustor.

Abstract: A combustor of the present disclosure includes: a mixing portion which is provided with a plurality of mixing passages passing through the mixing portion so as to be extended from an upstream end surface to a downstream end surface of the mixing portion intersecting an axis of the combustor, air being introduced to the plurality of the mixing passages from the upstream end surface of the mixing portion; and a fuel supply portion which is configured to supply the air introduced to the mixing passages with fuel to generate mixed fluid, wherein flow paths of the mixing passages have different pressure loss coefficients so that the differences in the flow velocity of the mixed fluid flowing through the mixing passages at the downstream end surface of the mixing portion are greater than those of a case where the mixing passages have the same flow path shape.

Abstract: A gas turbine including a fuel gas supply system to supply fuel gas via a fuel piping to a gas turbine combustor, a pressure control valve installed halfway along the fuel piping, a flow control valve installed in the fuel piping at downstream of the pressure control valve, and a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P1 at upstream of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P1.

Abstract: A gas turbine facility includes: a fuel pipe connected to a fuel supply facility; a fuel supply pipe connected to a combustor of a gas turbine; a fuel treating pipe connected to a fuel treating apparatus that treats a fuel; and a three-way valve having an inlet port connected to the fuel pipe, a first outlet port connected to the fuel supply pipe, and a second outlet port connected to the fuel treating pipe.

Abstract: A gas turbine combustor is equipped with a transition piece assembly of the combustor, the transition piece assembly includes a transition piece, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the movement suppression mechanism and the aforementioned projection members fit together and thereby the aforementioned seal member is fixed to the frame.

Abstract: A gas turbine including a fuel gas supply system to supply fuel gas via a fuel piping to a gas turbine combustor, a pressure control valve installed halfway along the fuel piping, a flow control valve installed in the fuel piping at downstream of the pressure control valve, and a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P1 at upstream of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P1.

Abstract: A gas turbine combustor that mixes fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supplies the generated combustion gas to a turbine is provided with: an inner cylinder forming a combustion chamber thereinside; an outer cylinder that covers the inner cylinder and forms, between the outer cylinder and the inner cylinder, a cylindrical outer peripheral flow path through which the compressed air flows; an end cover closing the end of the outer cylinder on an opposite side from a side the turbine is located; and a turn guide provided at the end on the end cover side of the inner cylinder, protruding from the outer peripheral surface of the inner cylinder toward the outer cylinder and smoothly connected to the inner peripheral surface of the inner cylinder.

Abstract: A gas turbine combustor that mixes fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supplies the generated combustion gas to a turbine is provided with: an inner cylinder forming a combustion chamber thereinside; an outer cylinder that covers the inner cylinder and forms, between the outer cylinder and the inner cylinder, a cylindrical outer peripheral flow path through which the compressed air flows; an end cover closing the end of the outer cylinder on an opposite side from a side the turbine is located; and a turn guide provided at the end on the end cover side of the inner cylinder, protruding from the outer peripheral surface of the inner cylinder toward the outer cylinder and smoothly connected to the inner peripheral surface of the inner cylinder.

Abstract: The present invention provides a gas turbine combustor which reduces NOx emissions for a hydrogen-containing fuel, is improved in reliability and realizes stable operation. The gas turbine combustor of the present invention includes a combustion chamber which burns a fuel and air, an air hole plate which is located on an upstream side of the combustion chamber and has air holes which are concentrically arranged plurally in line and plurally in number, and fuel nozzles which are arranged plurally in line and plurally in number, and a fuel nozzle inner wall has a fuel nozzle tapered shape which extends in an outer circumferential direction on a leading end part of the fuel nozzle.

Abstract: A gas turbine combustor is equipped with a transition piece assembly of the combustor, the transition piece assembly includes a transition piece, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the movement suppression mechanism and the aforementioned projection members fit together and thereby the aforementioned seal member is fixed to the frame.