A compressor controller for operating a compressor within an industrial automation environment is provided. The compressor controller includes a control module, configured to control the compressor via control settings, and a machine learning module, coupled with the control module. The machine learning module is configured to receive a set of supervised data related to the compressor, and to train with the supervised data to produce a Newtonian physics model representing the inputs and outputs of the compressor within the industrial automation environment. The machine learning module is also configured to receive performance data related to the compressor, receive environment data related to the compressor, and to process the performance data and environment data to produce predicted future performance data for the compressor, and to produce control settings for the compressor.

A turbine analysis device includes a state quantity acquiring unit configured to acquire a state quantity of a turbine, the state quantity including at least a temperature of the turbine. A load specifying unit is configured to calculate a history of a load of the turbine, based on the state quantity. A load and time calculating unit is configured to derive a relationship between the load of the turbine and an operable time when the turbine is operated at the load, based on a designed service life of the turbine and the history of the load that has been calculated by the load specifying unit.

A health monitoring system including an array of microphones, a data collection system, and analytic software used to detect health status, pending malfunctions, or faults of several disparate, engine subsystems. The system can be used to monitor health of the main engines, the engine nacelles, and auxiliary power units (APU) on the aircraft.

A communication adapter of a gas turbine engine of an aircraft includes a housing configured to be coupled to the gas turbine engine, a plurality of antennas integrated in the housing, a memory system and processing circuitry. The processing circuitry is configured to establish communication with an engine control mounted on the gas turbine engine, establish wireless communication between the communication adapter and an offboard system external to the aircraft through at least one of the antennas integrated in the housing of the communication adapter, and authenticate communication requests at the communication adapter for data sent between the offboard system and the engine control.

A system and method for determining performance of a turbine engine, and operation thereof. The system and method includes a plurality of sensors and one or more computing devices executing operations including acquiring a plurality of parameter sets each corresponding to a plurality of engine conditions in which each parameter set corresponding to each engine condition indicates a health condition at a plurality of locations at the engine; comparing the plurality of parameter sets to determine a health condition corresponding to a location at the engine; and generating a health condition prediction at the engine based on the compared parameters.

In a first embodiment, a system includes a turbine system including turbomachinery, one or more processors, and a memory storing instructions. When executed by the one or more processors, the instructions are configured to cause the one or more processors to receive an operating parameter of the turbomachinery, and calculate a risk of failure for the turbomachinery based at least in part on an asset failure mode model. The instructions are also configured to cause the one or more processors to categorize the risk of failure as a selected failure indicator category of a plurality of failure indicator categories, and output the selected failure indicator category.

A gas turbine engine propulsion system includes a gas turbine engine, a fuel storage tank and a pump unit. The gas turbine engine provides propulsive forces to move a vehicle. The fuel storage tank stores a fuel that can be used to power the gas turbine engine. The pump unit displaces a fuel flow from the fuel storage tank and delivers the fuel flow to the gas turbine engine.

Systems and methods for predicting engine performance are provided herein. A fluid sample having particles suspended therein is received from a first engine. A plurality of particles are extracted from the fluid sample. Features of the plurality of particles extracted from the fluid sample and features of particles of reference fluid samples from a plurality of reference engines are obtained. A plurality of correlation indices indicative of a level of correlation between the first engine and each one of the plurality of reference engines is determined. The correlation indices are compared to a threshold to determine a subset of the plurality of reference engines. Performance history for the engines in the subset is obtained. From the performance history, the first engine is determined as having a similarity in performance with the engines in the subset. An output is generated indicating a predicted performance for the first engine.

A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

A corrosion maintenance scheduling and implementation system and method measure one or more characteristics of corrosion in equipment before and after implementation of a corrosion remediation action, determine one or more of a change in the one or more characteristics of the corrosion between before and after implementation of the corrosion remediation action, one or more historical operational characteristics of the equipment, or one or more forthcoming operational characteristics of the equipment, and modify a schedule of the corrosion remediation action for the equipment based on one or more of the one or more characteristics of corrosion that are measured, the change in the one or more characteristics of the corrosion, the one or more historical operational characteristics of the equipment, and/or the one or more forthcoming operational characteristics of the equipment.