The abrupt cessation or run-away of a combustion engine may damage the combustion engine and pose a safety hazard to the surrounding environment. The combustion engine operational mode may be controlled, regulated or maintained by regulating the combustion mixture of the combustion engine. The oxidizer flow, a material or both of the combustion mixture may be regulate to create or form a combustion material that is outside a combustible range such that the combustion engine is placed or maintained in a spin-down operational mode. The material added to the combustion mixture may include a combustible, non-combustible, oxidizer, or exhaust material. A brake may also provide a secondary mechanism to maintain or place the combustion engine in a spin-down mode.

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

Sensor values indicative of operating parameters of a combustion system are received. An emission is determined, by at least a predictive model, based on at least the sensor values. The predictive model has been trained using at least a first set of data acquired from a measured emission and a second set of data determined using at least a physics model. Combustion system operating parameters are adjusted based on at least the determined emission.

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

A system for operating a gas turbine includes a controller configured to execute logic stored in a memory that causes the controller to determine two or more of a frequency, a coherence, a phase, and an amplitude, of a combustion instability; to compare two of more of the frequency, the coherence, the phase, and the amplitude of the combustion instability to a respective predetermined limit; and to adjust at least one parameter of the gas turbine if two or more of the frequency, the coherence, the phase, and the amplitude of the combustion instability are actionable relative to their respective predetermined limits. A related method of operating the gas turbine is also disclosed.

Provided are more efficient techniques for operating gas turbine systems. In one embodiment a gas turbine system comprises an oxidant system, a fuel system, a control system, and a number of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. The gas turbine system also includes a number of oxidant-flow adjustment devices, each of which are operatively associated with one of the combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into the associated combustor. An exhaust sensor is in communication with the control system. The exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and the control system is configured to independently adjust each of the oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor.

A control method is provided for an engine. During this control method, a lambda target parameter indicative of a ratio between a stoichiometric air-to-fuel ratio and an actual air-to-fuel ratio is determined. A control signal is determined using the lambda target parameter. A component of the engine is operated based on the control signal to regulate airflow within a compressor section of the engine.

In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change in combustion products produced by the first turbine combustor; identifying a first sensor response of a first subset of a plurality of sensors disposed within or downstream from a turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors; correlating the first subset of sensors with the first turbine combustor; and diagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response.

A method for detecting a rotating stall includes: determining a level of variation of a static pressure in a combustion chamber of the turbojet engine around an average value of this static pressure; comparing the level of variation of the static pressure relative to a first threshold; comparing a temperature measured at the outlet of a turbine of the turbojet engine relative to a second threshold; and if the level of variation of the static pressure is greater than the first threshold and the temperature at the outlet of the turbine is greater than the second threshold, detecting a presence of a rotating stall.

In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change in combustion products produced by the first turbine combustor; identifying a first sensor response of a first subset of a plurality of sensors disposed within or downstream from a turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors; correlating the first subset of sensors with the first turbine combustor; and diagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response.