Abstract:
A regulator for compressed gas, comprising a body with a gas inlet, a gas outlet and a gas passage fluidly interconnecting the gas inlet and gas outlet; a pressure reducer with, in the gas passage, a shut-off device and a movable assembly operatively connected to the shut-off device and delimiting with the body a regulating chamber downstream of the shut-off device; a pressure relief device in the gas passage downstream of the regulating chamber; and a flow restriction in the gas passage upstream of the shut-off device, dimensioned for reducing the gas pressure at the gas outlet under a maximum pressure value when the pressure relief device is opened and the shut-off device is opened.
Abstract:
An integrated combustion device power saving system includes: a hydrogen generation device, for generating a hydrogen-rich gas; a combustion device, for receiving the hydrogen-rich gas for combustion and generating heat energy and flue gas; a smoke distributing device, for distributing flue gas to the hydrogen generation device or atmosphere; a hydrogen-generation feed preheating device, for capturing waste heat of the flue gas from the smoke distributing device to preheat a hydrogen-generation feed to be used in the hydrogen generation device; and a power generating device, for receiving the flue gas from the hydrogen-generation feed preheating device while recycling waste heat of the flue gas to generate power to at least one of the hydrogen generation device or the combustion device.
Abstract:
A consumption amount of high-calorific gas such as coke oven gas (COG) during operation of a gas turbine is reduced, halt of the gas turbine due to clogging of a pilot system, a malfunction of a compressor which compresses high-calorific gas is prevented, and reliability of the gas turbine is improved. When operation of the gas turbine (11) starts, with use of both a first fuel supply system (31) which supplies a high-calorific fuel for a first nozzle constituting a combustor (17), and a second fuel supply system (32) which supplies a low-calorific fuel for a second nozzle constituting the combustor (17), the high-calorific fuel and the low-calorific fuel are supplied to the combustor (17), and at a time when the gas turbine (11) reaches output power which enables continuous operation with only the low-calorific fuel, supply of the high-calorific fuel to the combustor (17) is shut off, and only the low-calorific fuel is supplied to the combustor (17).
Abstract:
The object of this invention is to provide a fuel supply system capable of reducing the quantity of a fuel to be discharged from a plurality of fuel tanks connected in parallel is provided. The fuel supply system includes a plurality of the fuel tanks for storing a fuel, on-off valves provided individually for the fuel tanks, and a control unit which controls the opening and closing of the on-off valves. The control unit changes the number of the on-off valves to be simultaneously opened according to a situation. The control unit may reduce the number of the on-off valves to be simultaneously opened after a failure is detected or at the time of maintenance of the fuel supply system.
Abstract:
A turbomachine combustor assembly includes a combustor body, a combustion chamber defined within the combustor body, one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber, and a fuel start-up system fluidly connected to the combustion chamber. The fuel start-up system is configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel. A pilot nozzle is fluidly connected to the fuel start-up system. The pilot nozzle is configured and disposed to deliver an atomized cloud of the ignition fuel toward the combustion chamber.
Abstract:
A gas instrument determiner section (12) included in a flow meter device (10A) determines a kind of a gas instrument (20) in use by utilizing a flow pattern in which a range of increase/decrease in a gas flow is within a flow zone set in a fuel cell (21) as a flow pattern which is a pattern of a gas flow which changes over time when the fuel cell (21) is included in the gas instrument (20) in use. This makes it possible to accurately determine whether or not the gas instrument in use is the fuel cell while effectively suppressing unnecessary gas consumption.
Abstract:
A heating system can include certain pressure sensitive features. These features can be configured to change from a first position to a second position based on a pressure of a fuel flowing into the feature. These features can include, fuel selector valves, pressure regulators, burner nozzles, and oxygen depletion sensor nozzles, among other features.
Abstract:
A burner assembly comprising a burner element (8) at which gas is combusted. A valve (2) allows selective release of gas from a source into an expandable space (4) when the valve is opened. The space is expanadable up to a fixed volume (3) against the action of a restoring means. The space is arranged to contract under the action of the restoring means to force gas out of the space and to the burner element.
Abstract:
A fuel delivery system for a combustion turbine engine, comprising: a fuel line having a fuel compressor and parallel branches downstream of the fuel compressor: a cold branch that includes an after-cooler; and a hot branch that bypasses the after-cooler; a rapid heating value meter configured to measure the heating value of the fuel from the fuel source and transmit heating value data relating to the measurements; means for controlling the amount of fuel being directed through the cold branch and the amount of fuel being directed through the hot branch; and a fuel-mixing junction at which the cold branch and the hot branch converge; wherein the fuel-mixing junction resides in close proximity to a combustor gas control valve.