A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

The method can include determining a mass flow rate W of working fluid circulating through the compressor stage, determining a control parameter value associated to the geometrical configuration of the variable geometry element based on the determined value of mass flow rate W; and changing the geometrical configuration of the variable geometry element in accordance with the determined control parameter value.

Embodiments of the invention are shown in the figures, where a method is presented for designing a component, including designing or receiving a model of the component; determining at least one mode shape of at least a portion of the model; redesigning the model based on the determined at least one mode shape to obtain a redesigned model of the component; and manufacturing the component in accordance with the redesigned model.

A method for testing platforms (e.g., live, virtual, and/or constructive platforms associated with autonomous aircraft systems and their component subsystems) in a live/virtual/constructive (LVC) environment. In embodiments, the method includes determining, via a testbed engine, the development state of a platform component under test. The method includes retrieving a test to be executed, the test including test conditions to be applied to the component. The method includes determining whether the component is enabled to respond to the test conditions. The method includes, if the component is enabled to respond to the test conditions, executing the test while monitoring the component to detect a first output response and a second output response. The method includes identifying, via the testbed engine, at least one change in the development state of the component by comparing the first and second output responses.

In a turbine designing and manufacturing method attendant on a material change of a rotor disk of a turbine rotor, a temperature rise time ratio is determined which is a desired ratio of a temperature rise time of the temperature of the rotor disk from a first temperature to a second temperature after the material change to the temperature rise time before the material change. An inter-surface distance between surfaces on upstream and downstream sides of the rotor disk after the material change is determined, and a shape of the rotor disk after the material change is determined based on the inter-surface distance. The turbine is designed based on the determined shape of the rotor disk. After the material change in the shape determined in the designing process, the rotor disk and the turbine are manufactured based on the result of the designing process.

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.

A measuring system is provided that includes a turbine engine thrust estimator that computes “virtual measurements” of dynamic engine thrust and other parameters of interest from test cell data in a very short amount of time. The measuring system ‘tunes’ a user's engine model, in a numerical propulsion system simulation, by optimizing system biases and health parameters to match the sensor outputs of a set of steady state data points across the operating range. The tuned model is then utilized by the measuring system to create a constant gain extended Kalman filter that is added directly within a code of the numerical propulsion system simulation. Results, including thrust, from the numerical propulsion system simulation with Kalman filter are then presented as ‘actual’ corrected data.

Systems and methods for predicting a surge event in a compressor of a turbomachine are provided. According to one embodiment of the disclosure, a system may include one or more computer processors associated with the turbomachine. The one or more computer processors may be operable to receive a plurality of performance parameters of the compressor and analyze the plurality of performance parameters to determine corrected performance values of the performance parameters. Based at least partially on the corrected performance values, a compressor efficiency may be determined. The processor may be further operable to standardize the compressor efficiency for a standard mode of operation, ascertain historical performance data associated with the standard mode of operation, and analyze the compressor efficiency based at least partially on the historical performance data. Based on the analysis of the compressor efficiency, a surge event may be selectively predicted.

A method of developing a suggested blend repair to an airfoil includes the steps of: (a) storing history with regard to a particular airfoil in a particular engine; (b) taking information with regard to new damage to the particular airfoil; (c) reaching an initial blend recommendation based upon step (b); (d) assessing whether the initial blend recommendation of step (c) would be appropriate to repair the new damage based upon a consideration of steps (a)-(c); and (e) reporting a final blend recommendation. An airfoil repair recommendation system is also disclosed.

A torque required to achieve the modulated reference speed or adjustment of a modulated torque and the actual speed of the centrifugal pump is determined. Then a model speed is calculated with the aid of a mathematical pump-motor model simulating the behavior of the centrifugal pump within a hydraulic system as well as a disturbance signal from a deviation of the model speed from the actual speed of the centrifugal pump. Then a correction signal is determined by integrating the product of the disturbance signal and a sine or cosine signal with a multiple of the excitation frequency over at least one period of the excitation signal. Finally, at least one model parameter of the pump-motor model is determined as a function of the correction signal and the flow rate and/or the head is calculated using the adapted pump-motor model.