A system for monitoring the state of health of a monitored aircraft engine comprises an anomaly detection unit which analyses engine operating parameters and raises an alarm if a result of the analysis of one of the engine operating parameters crosses a threshold, the alarm being associated with a probability of a given type of engine damage occurring. The system further comprises an engine operating conditions monitoring unit which determines a state of wear of the engine, and an alarm corroboration unit which weights the said probability of occurrence by the determined state of wear. The invention is applicable to the preventive maintenance of turbomachines.

The present application provides a method of evaluating fatigue damage in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors and based upon the operating parameters, determining: a run time from start-up until the turbine reaches X percent load and a start-up temperature transient from start-up until the turbine reaches X percent load, and calculating: a run time ratio of the determined run time until the turbine reaches X percent load to a predetermined run time, a start-up temperature ratio of the determined start-up temperature transient to a predetermined start-up temperature transient, and a fatigue severity factor by averaging the run time ratio and the start-up temperature ratio. Based upon the determined fatigue severity factor, altering one or more of the operating parameters and/or initiating repair procedures.

A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

A method of monitoring a component includes providing the component which includes a body having an exterior surface and a plurality of passive strain indicators configured on the exterior surface. The method includes directly measuring the component with at least one three-dimensional data acquisition device. The direct measurement generates a first point cloud and a plurality of second point clouds. The first point cloud corresponds to the exterior surface and includes a plurality of first data points, each data point having an X-axis coordinate, a Y-axis coordinate, and a Z-axis coordinate. Each second point cloud corresponds to one of the plurality of passive strain indicators and includes a plurality of second data points, each data point having an X-axis coordinate, a Y-axis coordinate, and a Z-axis coordinate. A second data point density of each second point cloud is greater than a first data point density of each first point cloud.

A measurement processing system suitable for supporting condition monitoring of a wind turbine based upon measurements performed on electrical and mechanical parts of the wind turbine, and, while determining whether the wind turbine is connected to the electrical grid or not, determining information representative for shaft torque of the wind turbine and suited for condition monitoring of the wind turbine, based on said measurements.

A lubrication system is disclosed. The lubrication system may be used in conjunction with a gas turbine engine for generating power or lift. The lubrication system utilized a flow scheduling valve which reduces lubricant flow to at least one component based on an engine load. The lubrication system may further include a main pump which may be regulated by an engine speed. Thus, a lubrication system which provides a lubricant to engine components based on the load and speed of the engine is possible. The system may improve efficiency of the engine by reducing the power previously spent in churning excess lubricant by at least one engine component as well as reducing the energy used by a lubricant cooler in cooling the excess lubricant. The lubricant cooler size may also be minimized to reduce weight and air drag due to the reduced lubricant flow.

Distress models can be generated to model current or future deterioration of components. By correlating distress models with maintenance costs and material consumption, cumulative cost models and cumulative material models can be developed to optimize engine removal timing in order to maximize asset and portfolio value.

A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold.

A turbine blade maximum vibration response prediction method for predicting a maximum vibration response acting on a plurality of turbine moving blades provided along the circumferential direction of a turbine rotor includes the steps of: gaining, before turbine operation start, prior response data that is distribution data on vibration response of all the turbine moving blades for each turbine operating condition; gaining, by using the prior response data, operation response data that is distribution data on the vibration response of all the turbine moving blades during the operation of the turbine; and predicting, from the operation response data, the turbine moving blade of all the turbine moving blades on which the maximum vibration response is acting, and the magnitude of the maximum vibration response.

A lubrication system is provided. The lubrication system may be used in conjunction with a gas turbine engine for generating power or lift. The lubrication system utilized a flow scheduling valve which reduces lubricant flow to at least one component based on an engine load. The lubrication system may further include a main pump which may be regulated by an engine speed. Thus, a lubrication system which provides a lubricant to engine components based on the load and speed of the engine is possible. The system may improve efficiency of the engine by reducing the power previously spent in churning excess lubricant by at least one engine component as well as reducing the energy used by a lubricant cooler in cooling the excess lubricant. The lubricant cooler size may also be minimized to reduce weight and air drag due to the reduced lubricant flow.