An electronic control unit diagnoses leakage abnormality in an intake system downstream from a supercharger provided in the intake system of the engine. The electronic control unit sets, as a supercharging region monitoring value, a ratio between a first air amount obtained from a detection value of an air flowmeter and a second air amount obtained from a detection value of an intake pressure sensor, the ratio being the ratio obtained when the engine is operated in a supercharging region. The electronic control unit also sets, as a non-supercharging region monitoring value, a ratio obtained when the engine is driven in a non-supercharging region. The electronic control unit determines the presence of the leakage abnormality in the intake system when the ratio of the supercharging region monitoring value to the non-supercharging region monitoring value is larger than a predetermined specified value.

A control device for an engine includes an electronic control unit configured to estimate a water content mixed in engine oil based on a history of a fuel injection amount during an operation of the engine and restrain freezing of water such that, when the water content thus estimated is a predetermined amount or more, the electronic control unit increases a mixing amount of the fuel into the engine oil as compared with a case where the water content thus estimated is less than the predetermined amount. The control device estimates the water content mixed in the engine oil as a function of an integrated value of water content while an oil temperature of the engine is less than a predetermined temperature.

A system of non-regression tests of a designing tool including modules used to build a monitoring device of an aircraft engine is provided. The system includes a processor configured to automatically create an experience base by instrumenting behavior tests upon executing the modules, the experience base including reference input signals, sets of reference parameters, reference output signals, and collections of results of reference executions relating to the modules; start again the behavior tests on the modules depending on the corresponding reference input signals and the corresponding sets of reference parameters thus generating test output signals and collections of results of test executions; and compare the test output signals with the corresponding reference output signals and the collections of results of test execution with the corresponding collections of results of reference executions in order to test the non-regression of the designing tool.

A system of non-regression tests of a designing tool including modules used to build a monitoring device of an aircraft engine is provided. The system includes a processor configured to automatically create an experience base by instrumenting behavior tests upon executing the modules, the experience base including reference input signals, sets of reference parameters, reference output signals, and collections of results of reference executions relating to the modules; start again the behavior tests on the modules depending on the corresponding reference input signals and the corresponding sets of reference parameters thus generating test output signals and collections of results of test executions; and compare the test output signals with the corresponding reference output signals and the collections of results of test execution with the corresponding collections of results of reference executions in order to test the non-regression of the designing tool.

A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.

A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.

A gas turbine system has a gas turbine engine, control unit, a data acquisition system including a thermodynamic model unit and a test sequence unit, sensor device coupled to the engine for measuring performance parameter of the engine, and comparative unit. The thermodynamic model unit generates computed performance parameter based on mechanical and thermodynamic models of the engine. The test sequence unit generates test sequence data including set point operating data and time schedule data with which a test cycle of the engine is runnable. The data acquisition system generates test control data based on the test sequence data, and is coupled to the control unit for providing test control data thereto to control the engine. The comparative unit is coupled to the data acquisition system such that the measured performance parameter measured by the sensor device is comparable with the computed performance parameter.

For continuous measurement of the dynamic fuel consumption of an internal combustion engine with a venting tank (10) which is disposed in a return line (11) from the outflow side (12) of the fuel system (7) and is also connected to the intake line (13) to the fuel system, a filling level regulator (15) is provided at a connection of the venting tank (10) and has a circulation pump (22) as well as a control valve (9) connected thereto, through which the flow passes continuously, and which is opened more or less as a function of the filling level to be regulated. Thus apparent consumptions occurring in specific operating states of the internal combustion engine can be avoided but can also be taken into account as corrections.

An example method of inspecting a part includes applying a penetrant dye to the part, the penetrant dye exhibiting a fluorescent color when subjected to light from a lighting device. A portion of the part is illuminated with light from the lighting device. An image of the portion of the part is automatically recorded with a camera while the portion is illuminated. An uncertainty metric for the image is automatically determined that is indicative of a likelihood that pixels in the image having the fluorescent color represent damage to the part. At least one of the part, lighting device, and camera are automatically adjusted based on the uncertainty metric being within a predefined range. The automatic recording, determining, and adjusting steps are iteratively repeated until the uncertainty metric is greater than the predefined range, or a predefined number of iterations have been performed for the portion of the part.

A marine propulsor comprises: a stationary part and a movable part which is movable relative to the stationary part; and a wireless communication system, comprising at least one transmitter which is disposed in the movable part and is configured to transmit an electromagnetic data signal and at least one receiver which is disposed in the stationary part and is configured to receive the electromagnetic data signal. The wireless communication system includes a diversity scheme for mitigating multipath distortion of the electromagnetic data signal between the at least one transmitter and the at least one receiver.