Abstract: A vehicle control device that controls a vehicle is configured to execute rotation speed control when the vehicle is in series traveling, in which a rotation speed of the internal combustion engine is increased to a first rotation speed in accordance with an increase in a speed of the vehicle, and when the rotation speed of the internal combustion engine reaches the first rotation speed, the rotation speed of the internal combustion engine is decreased to a second rotation speed lower than the first rotation speed; and restrict execution of the rotation speed control when receiving a predetermined operation.

Abstract: A Raman scattered light acquisition device includes an emitting optical system configured to guide excitation light into a fluid, a scattered light window configured to define a part of a flow path of the fluid and through which Raman scattered light from the fluid irradiated with the excitation light passes, and a scattered light receiving device having a light receiving surface receiving Raman scattered light passed through the scattered light window. The scattered light window and the light receiving surface of the scattered light receiving device are disposed at a position in which they are separated from an optical axis in the fluid in a radial direction within a range in which an optical path of the excitation light in the fluid is present in an optical axis direction in which the optical axis in the fluid which is an optical axis of the excitation light in the fluid extends.

Abstract: A Raman scattered light acquisition device includes an emitting optical system configured to guide excitation light into a fluid, a scattered light window configured to define a part of a flow path of the fluid and through which Raman scattered light from the fluid irradiated with the excitation light passes, and a scattered light receiving device having a light receiving surface receiving Raman scattered light passed through the scattered light window. The scattered light window and the light receiving surface of the scattered light receiving device are disposed at a position in which they are separated from an optical axis in the fluid in a radial direction within a range in which an optical path of the excitation light in the fluid is present in an optical axis direction in which the optical axis in the fluid which is an optical axis of the excitation light in the fluid extends.

Abstract: The gas turbine system has: a gas turbine having a compressor, a combustor, and a turbine; a fuel supply mechanism for supplying fuel to the combustor; a composition detection unit for detecting the composition of the fuel; and a controller for controlling the flow rate of the fuel supplied from the fuel supply mechanism to the combustor, on the basis of a function of the exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or an expansion ratio of the turbine. The controller calculates the specific heat ratio of the combustion gas from the composition of the fuel detected by the composition detection unit, corrects the function on the basis of the calculated specific heat ratio, and controls the flow rate of the fuel on the basis of the corrected function.

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 gas turbine system has: a gas turbine having a compressor, a combustor, and a turbine; a fuel supply mechanism for supplying fuel to the combustor; a composition detection unit for detecting the composition of the fuel; and a controller for controlling the flow rate of the fuel supplied from the fuel supply mechanism to the combustor, on the basis of a function of the exhaust temperature of exhaust gas passing through the turbine and either air pressure of air expelled from the compressor to the combustor or an expansion ratio of the turbine. The controller calculates the specific heat ratio of the combustion gas from the composition of the fuel detected by the composition detection unit, corrects the function on the basis of the calculated specific heat ratio, and controls the flow rate of the fuel on the basis of the corrected function.

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).