A computer-implemented method comprising: controlling input of data quantifying damage received by a compressor of a gas turbine engine into a first machine learning algorithm; receiving data quantifying a first operating parameter of the compressor as an output of the first machine learning algorithm; and determining operability of the compressor by comparing the received data quantifying the first operating parameter of the compressor with a threshold.

A method of identifying a fuel contained in a fuel tank of an aircraft and arranged to power a gas turbine engine of the aircraft is performed by processing circuitry of the aircraft and includes: obtaining at least one fuel characteristic of any fuel already present in the fuel tank prior to refuelling; determining at least one fuel characteristic of a fuel added to the fuel tank on refuelling; and calculating at least one fuel characteristic of the resultant fuel in the fuel tank after refuelling. The method may further controlling the propulsion system of the aircraft based on the calculated at least one fuel characteristic of the resultant fuel in the fuel tank after refuelling.

A fuel flow measuring system includes an ultrasonic fuel flow sensor. The fuel flow sensor includes a first transducer and a second transducer. The first transducer is excited at multiple different excitation frequencies and a voltage, an electric current, and a phase difference between the voltage and the electric current is sensed at the first transducer during excitation. Data points are generated based on the sensed readings and a model is fit to the data points to determine a complex impedance spectrum. The complex impedance spectrum indicates a range of excitation frequencies within a range of a peak resonance frequency of the first transducer. One or more characteristics of excitation signals directed to the second transducer are set based on the determined complex impedance spectrum. In this manner, the signal to noise ratio of ultrasonic signals emitted by the second transducer and received by the first transducer can be maximized.

A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

An engine control system includes an engine controller configured to execute an open-loop model of the engine control system. The open-loop model receives a measured effector and boundary condition parameter vector and generates a synthesized engine operating parameter based on the measured effector and boundary condition parameter vector. The engine controller calculates a corrector error value between the synthesized engine operating parameter and a measured engine operating parameter, and determines an open loop corrector error calculated as a difference between the corrector error and a vector-matrix product of corrector state vector and a gain map/function. The engine controller applies the gain map/function to the open loop corrector error to determine an effector and boundary condition error vector of the measured effector and boundary condition parameter vector.

A control device is a device for controlling a gas turbine. The control device is provided with: a prediction unit configured to predict a future state quantity of the gas turbine corresponding to a control input to the gas turbine in a prediction horizon, using a prediction model; an optimization unit configured to optimize the control input in at least a part of the prediction horizon, using a prediction result of the prediction unit; a storage unit for storing sensitivity information indicating sensitivity of the control input to a change speed of the state quantity for each operating condition of the gas turbine; and an update unit configured to read the sensitivity information corresponding to the operating condition assumed in the prediction horizon from the storage unit, and update one or more coefficients of a prediction equation of the state quantity used in the prediction model.

A method for is provided. The method can include receiving data characterizing a first measurement image having a first state and a first set of three-dimensional coordinate data corresponding to the first measurement image. The first measurement image can include two-dimensional image data. The method can also include receiving data characterizing at least one geometric dimension determined for the first measurement image. The method can further include receiving data characterizing a second measurement image having a second state and a second set of three-dimensional coordinate data corresponding to the second measurement image. The method can also include applying the first state of the first measurement image to the second measurement image. The method can further include displaying at least one second geometric dimension determined using the second set of three-dimensional coordinate data. Related systems performing the method are also provided.

A system for automatically measuring an exhaust area of a turbine guide vane, including a data acquisition module configured to measure a three-dimensional point cloud coordinate of a contour of a throat; a positioning module configured to automatically adjust a relative spatial position between the data acquisition module and the turbine guide vane; and a data processing module configured to fit a three-dimensional contour of the throat according to the three-dimensional point cloud coordinate measured by the data acquisition module. A method for automatically measuring an exhaust area of a turbine guide vane using the system is also provided.

A method of evaluating compliance of a component of an aircraft engine with flow requirements has: obtaining experimental data from experimental testing on a prototype of the component; obtaining a digitized model of a production model of the component, the digitized model including digitized apertures having geometrical data corresponding to that of apertures defined in the production model; computing a nominal mass flow rate through the digitized apertures using the geometrical data and flow parameters from the experimental data; correcting the nominal mass flow rate of the digitized model to obtain a computed mass flow rate of the production model; and assigning at least one parameter to the production model, the at least one parameter indicative of installation approval of the production model of the component for installation on the aircraft engine when the computed mass flow rate is determined to be within a prescribed range of the flow requirements.