Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: A gas turbine combustion device comprises a plurality of combustion devices. Each combustion device has an inner cylinder and a tail cylinder in a vehicle chamber. An acoustic sleeve is provided between each inner cylinder and a corresponding outer cylinder in the vehicle chamber. An acoustic coupling effect with a vehicle chamber can be reduced.

Abstract: The objective is to provide a gas turbine and the combustor thereof in which super high frequency combustion oscillation and the generation of NOx are reduced.

Abstract: A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

Abstract: A gas turbine combustor in which a part or all of the wall of the combustor disposed within an intake chamber is formed as an acoustic energy absorbing member that can absorb the acoustic energy of a combustion variation generated within the combustor. The acoustic energy absorbing member is constructed of a thin corrugated plate in a circumferential direction, a high-temperature-proof perforated material, or a back plate disposed at the outside of a perforated plate in a radial direction with a distance from the perforated plate. It is also possible to provide a covering member at the outside of the acoustic energy absorbing member in a radial direction, for covering the acoustic energy absorbing member with a distance from the acoustic energy absorbing member. It is preferable that the acoustic energy-absorbing member and/or the covering member are reinforced with a frame that extends in a circumferential direction and/or a longitudinal direction.

Abstract: A gas turbine combustion device comprises a plurality of combustion devices. Each combustion device has an inner cylinder and a tail cylinder in a vehicle chamber. An acoustic sleeve is provided between each inner cylinder and a corresponding outer cylinder in the vehicle chamber. An acoustic coupling effect with a vehicle chamber can be reduced.

Abstract: In a noise measuring system comprising a microphone array and a directivity forming section for controlling the direction of directivity of the microphone array, the directivity forming section includes delay section and adding section, and the optimal value of a delay time of the delay section is set in such a manner that a noise isolation characteristic for causing any mobile noise generator not targeted for noise measurement to come off a directional plane or a directional line formed in the direction of directivity of the microphone array and a deterioration characteristic of the directivity of the microphone array balance with each other.

Abstract: In a full-automated washer, a cloth amount sensor detects a quantity of an object being washed which is thrown into a washing drum as a value inclusive of information regarding a degree of bulkiness of the object to be washed. A processing circuit included in the full-automated washer is responsive to a detection output signal from the cloth amount sensor to determine a water supply amount, a cleanser feed amount, a stirring time and a rinsing time. The cloth amount sensor is mounted to a stirring motor. Upon an OFF-state of the motor, the detection output signal is generated by measuring a voltage waveform induced by inertial motion which varies in accordance the degree of bulkiness of the object to be washed.