Patent application number | Description | Published |
20100257867 | MONITORING OF A HIGH-PRESSURE PUMP IN A TURBINE ENGINE FUEL SUPPLY CIRCUIT - A device and method for monitoring a high-pressure pump in a turbomachine fuel supply circuit by detecting opening of a pressurizing and shut-off valve mounted on an outlet side of a fuel flow regulating valve, by measuring rotational speed of the turbomachine corresponding to the opening of the pressurizing and cut-off valve, and by monitoring change in a value of the rotational speed to propose replacement of the high-pressure pump when the measure value rotational speed reaches a predetermined threshold. | 10-14-2010 |
20110296846 | AERONAUTICAL ENGINE WITH COOLING OF AN ELECTRIC STARTING DEVICE - An aeronautical engine including a fuel pumping device including a high pressure fuel pump including an inlet connected to a low pressure fuel conduit and an outlet connected to a main circuit for feeding high pressure fuel, an electric device starting the engine, and a device cooling the electric starting device connected to the pumping device to ensure cooling by circulation of fuel. The cooling device is supplied with fuel by a pump that includes an inlet connected to the pumping device, upstream from the high pressure pump, and that is driven by an electric motor independently of the high pressure pump. | 12-08-2011 |
20110301822 | METHOD AND SYSTEM FOR CONTROLLING A GAS TURBINE AND A GAS TURBINE INCLUDING SUCH A SYSTEM - A method for controlling a gas turbine including a compressor assembly including at least one variable geometry portion, a combustion chamber, and a turbine assembly. The method generates a flow rate setpoint value for fuel to be fed to the combustion chamber as a function of a desired speed of the gas turbine, computes threshold values for maintaining the fuel flow setpoint value in a given range, the threshold values depending on a thermodynamic state of the gas turbine, and controls the position of the variable geometry portion by controlling an actuator as a function of the difference between position information representative of the instantaneous position and setpoint position information. The threshold values are automatically adjusted by computation in real time as a function of the instantaneous position information of the variable geometry portion or of the difference between this position information and the setpoint position information. | 12-08-2011 |
20120101706 | METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET - A method for monitoring a servo-control loop ( | 04-26-2012 |
20130338898 | METHOD AND A DEVICE FOR MONITORING A SERVO-CONTROL LOOP OF AN ACTUATOR SYSTEM FOR ACTUATING VARIABLE-GEOMETRY COMPONENTS OF A TURBOJET - A method monitoring a servo-control loop, including: estimating monitoring parameters from operating data of the servo-control loop; obtaining indicators from the monitoring parameters; determining at least one signature from values of at least some of the indicators; and detecting and locating a degradation affecting the servo-control loop as a function of the at least one determined signature. | 12-19-2013 |