Systems and methods that include and/or leverage a neural network to approximate the steady-state performance of a turbine engine are provided. In one exemplary aspect, the neural network is trained to model a physics-based, steady-state cycle deck. When properly trained, novel input data can be input into the neural network, and as an output of the network, one or more performance indicators indicative of the steady-state performance of the turbine engine can be received. In another aspect, systems and methods for approximating the steady-state performance of a virtual or target turbine engine based at least in part on a reference neural network configured to approximate the steady-state performance of a fielded or reference turbine engine are provided.

A control system for a gas turbine includes a controller. The controller includes a processor configured to access an operational parameter associated with the gas turbine. The processor is configured to receive a plurality of signals from sensors disposed in a turbine system, wherein the turbine system comprises a compressor system. The processor is further configured to derive a compressor efficiency and a turbine heat rate based on the plurality of signals. The processor is additionally configured to determine if an online water wash, an offline water wash, or a combination thereof, should be executed. If the processor determines that the online water wash, the offline water wash, or the combination thereof, should be executed, then the processor is configured to execute the online water wash, the offline water wash, or the combination thereof.

An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.

A system and method for monitoring the operating conditions of a steam turbine and developing an adaptive inspection interval includes access to a digital data storage archive containing information relating to use and operation of comparable steam turbines and plant/service events, one or more turbine operational condition sensors for monitoring steam quality in real time during operation of the steam turbine. A processor calculates a steam quality value based upon cation conductivity of the steam used to operate the steam turbine as measured by the sensors. The processor uses the calculated steam quality information either alone or together with other acquired operational and parametric data to determine an adapted inspection interval for the steam turbine. The processor produces an output which includes the determined adapted inspection interval and may additionally include updated maintenance and repair schedules. A method for adapting an inspection interval for a particular steam turbine at a particular plant involves considering a calculated steam quality of the steam provided to the turbine, considering any available corrosion diagnostics data obtained during any turbine stand-still lay-off times, considering any relevant turbine fleet information and historical plant/service event information, and evaluating these parameters and informations to determine an adapted maintenance interval for the steam turbine. The method includes calculating a steam quality value in accordance with a predetermined formula based on a real-time measured conductivity of the steam provided to the turbine during operation and generating a output specifying an inspection interval adapted to the particular steam turbine and plant of operation.

A starter air valve (SAV) system includes a pressure actuated SAV actuator configured to be operatively connected to a SAV, a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator, and a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator. A manual override (MOR) valve selector is disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position.

A starter air valve (SAV) system includes a pressure actuated SAV actuator configured to be operatively connected to a SAV, a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator, and a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator. A manual override (MOR) valve selector is disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position.

A computer-implemented method. The method comprising: (a) obtaining a candidate characterising code, the candidate characterising code being indicative of character of an example of a physical system; (b) accessing a database of extant characterising codes, the extant characterising codes being indicative of character of other examples of the physical system; (c) determining a degree of similarity between the candidate characterising code, and at least one of the extant characterising code; and (e) providing, as an output, the results of the comparison.

In accordance with at least one aspect of this disclosure, there is provided a fuel control system for gaseous fuel in an aircraft. The system includes a control module operatively connected to a metering device in a fuel flow conduit, the control module operable to control the flow of fuel through the fuel flow conduit. The control module includes an input line operable to receive a command input indicative of a requested engine state. In embodiments, the control module includes a compressibility logic and machine readable instructions. The machine readable instruction can be configured to cause the control module to control the metering device to achieve the requested engine state based on a compressibility factor input from the compressibility logic.

A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.

A method of controlling a rotor tip clearance in a gas turbine engine (10). The method comprises determining an engine or component remaining useful life T.sub.r, and controlling a tip clearance control arrangement (38) to maintain a rotor tip clearance (36) at a target tip clearance D.sub.target. The target tip clearance D.sub.target is determined in accordance with a function of remaining engine life T.sub.r.