The invention relates to a method for determining a fluid conveying parameter, a fluid conveying device, particularly for determining a volumetric flow, comprising the steps of Determining excitation information for mechanical excitation of at least one fluid conveying element of the fluid conveying device in at least one spatial direction by at least one first sensor means, Providing operating information, comprising at least a value of an operating variable of the fluid conveying device by means of a providing means, Analyzing the information provided and determined, Determining a fluid conveying parameter, particularly a volumetric flow, of the fluid conveying device based on the analyzed information.

A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

An aspect of the present disclosure provides a diagnosis device for an internal combustion engine. The internal combustion engine 1 includes a variable geometry type turbocharger 14, and the turbocharger includes a variable vane 28, a link mechanism configured to operate the variable vane, and an actuator 29 configured to drive the link mechanism. The diagnosis device includes a control unit 100 configured to control an opening degree of the variable vane by controlling the actuator. The control unit determines that an abnormality has occurred in the link mechanism of the turbocharger when an operating time of the internal combustion engine in a predetermined operating region exceeds a predetermined upper limit value and a differential pressure between a target boost pressure determined according to an operating state of the internal combustion engine and an actual boost pressure exceeds a predetermined upper limit value.

A system and method for increasing power output of a gas turbine. A method of increasing a power output of a gas turbine comprises providing an auxiliary system configured to be coupled to the gas turbine. The auxiliary system includes a natural gas engine, a compressor, and a heat exchanger fluidly coupled to the compressor. The method includes fluidly coupling the auxiliary system to a combustor case of the gas turbine. The method comprises operating the natural gas engine to drive the compressor to compress air to form compressed air and directing exhaust of the natural gas engine to the heat exchanger. The method includes heating the compressed air in the heat exchanger using the exhaust of the natural gas engine to form heated compressed air and injecting the heated compressed air into the combustor case of the gas turbine.

A system includes a compressor having a compressor inlet, a turbine having a plurality of stages disposed within a turbine casing, and a turbine extraction gas (TEG) heating system. The turbine is configured to drive the compressor via expansion of combustion products through the plurality of stages. The TEG heating system includes a turbine gas extraction system coupled to the turbine casing and to the compressor inlet. The turbine gas extraction system is configured to receive a portion of the combustion products as a turbine extraction gas (TEG) from the turbine. The TEG is received through the turbine casing, the TEG heating system is configured to supply a heated flow to the compressor inlet, and the heated flow includes the TEG.

An improved system, apparatus and method for estimating thrust from an engine, and more specifically, a system for estimating thrust from strain gauge and accelerometer measurements. At least one strain gauge is mounted on an engine mount to measure strain to estimate a constant velocity or steady-state portion of thrust. At least one accelerometer is mounted on the vehicle to measure acceleration to estimate a transient portion of thrust. Steady-state thrust estimation and transient thrust estimation are combined to estimate thrust from the engine. An algorithm provides steps for estimating thrust from strain gauge and accelerometer measurements.

A method for combusting a fuel includes, providing an oxidizer mass flow, providing a first oxidizer partial mass flow, combusting a fuel in the first oxidizer partial mass flow thus providing a mass flow of combustion products, providing the mass flow of combustion products to a duct, and ducting the mass flow of combustion products through the duct in a flow direction. A flow of a first supplementary fluid which is essentially aligned with the flow of combustion products is selectively provided as one of an oxidizer and a premixed fuel/oxidizer mixture. A further mass flow is discharged laterally offset with respect to a discharged mass flow of first supplementary fluid and across the flow cross section of the duct, to provide mass flows of supplementary fluids as laterally stratified layers of the respective supplementary fluids.

A 2-shaft gas turbine has a controller which controls the opening degree of an air inlet guide vane to adjust the inlet mass flow rate to a compressor. The air inlet guide vane control unit includes a first control unit that adjusts the opening degree of the inlet guide vane to keep the speed of a high pressure turbine shaft constant; a control status confirmation unit that confirms the actual speed and the opening degree of the inlet guide vane; and a low ambient temperature correction unit that reduces the actual speed in a case where the actual speed is equal to or greater than a predetermined threshold value, the opening degree of the inlet guide vane is equal to or greater than a predetermined threshold value, and the ambient temperature is equal to or less than a predetermined threshold value.

A system and medium for controlling a fuel gas compressor of a gas turbine system that compresses a gaseous fuel for consumption in a high-pressure combustor. Moreover, the compressor is configured to generate a discharge pressure for the combustor based at least in part on a load demand for the gas turbine system.

Embodiments of the disclosure provide a method for controlling steam pressure within a turbine component. The method includes calculating a predicted stress on a rotor of the turbine component based on a predicted steam flow with the inlet valve in a minimum load position, a rotor surface temperature, and an inlet steam temperature, and determining whether the predicted stress exceeds a threshold. If the predicted stress exceeds the threshold, the inlet valve adjusts to a warming position. When steam in the discharge passage reaches a target pressure, the exhaust valve partially closes while maintaining the warming position of the inlet valve. If a safety parameter of the turbine component violates a boundary, the exhaust valve partially opens while maintaining the warming position of the inlet valve. When the predicted stress does not exceed the threshold, the inlet valve opens to at least the minimum load position.