A method for use in a turbine control system includes controlling fuel supply to a gas turbine engine at least in part using a fuel supply limit determined as a first function of a rotational speed of a shaft of the gas turbine engine. The method also includes obtaining a first value representative of a rotational speed of the shaft, and differentiating the first value within a processing unit. The processing unit determines an adjusted fuel supply limit as an adjusted function of the first value. The adjusted function is based on the first function and the differentiated first value. The method further includes controlling the fuel supply to the gas turbine engine at least in part using the adjusted fuel supply limit.

A method of starting a gas turbine engine includes determining an abnormal shutdown condition during operation of the gas turbine engine and determining a first set of lightoff parameters for the gas turbine engine. The method also includes restarting the gas turbine engine using the first set of lightoff parameters. The method further includes iteratively determining subsequent first sets of lightoff parameters and restarting the gas turbine engine using a respective subsequent first set of the determined subsequent first sets of lightoff parameters until the gas turbine maintains a first set of operational parameters, where the first set of operational parameters is representative of a robust lightoff of the gas turbine engine.

A method of starting a gas turbine engine includes determining an abnormal shutdown condition during operation of the gas turbine engine and determining a first set of lightoff parameters for the gas turbine engine. The method also includes restarting the gas turbine engine using the first set of lightoff parameters. The method further includes iteratively determining subsequent first sets of lightoff parameters and restarting the gas turbine engine using a respective subsequent first set of the determined subsequent first sets of lightoff parameters until the gas turbine maintains a first set of operational parameters, where the first set of operational parameters is representative of a robust lightoff of the gas turbine engine.

An electrical power system architecture and method for allocating power includes a power distribution bus configured to receive power generated by a first engine having a first generator and a second generator, a first set of electrical buses connected with the power distribution bus and associated with the first engine, and a second set of electrical buses configured to selectively connect with the power distribution bus.

An electrical power system architecture and method for allocating power includes a power distribution bus configured to receive power generated by a first engine having a first generator and a second generator, a first set of electrical buses connected with the power distribution bus and associated with the first engine, and a second set of electrical buses configured to selectively connect with the power distribution bus.

A gas turbine engine includes a propulsor, a compressor and a turbine section having a first turbine rotor connected to the compressor through a first shaft. A second turbine rotor is connected to at least the propulsor through a second shaft. The first turbine rotor drives the compressor at a first speed, and the second turbine rotor drives the propulsor at a second speed. There is a control for the gas turbine engine. The control is programmed to compare one of the first speed and the second speed to a commanded speed to determine a difference. The control also is programmed to identify a flame out condition, and identify a locked in stall condition when the difference between the two speeds exceeds a threshold for at least a threshold period of time at least in part concurrently with the flame out condition. The control is programmed to take a corrective action should the locked in stall condition be identified. A method is also disclosed.

A gas turbine engine includes a propulsor, a compressor and a turbine section having a first turbine rotor connected to the compressor through a first shaft. A second turbine rotor is connected to at least the propulsor through a second shaft. The first turbine rotor drives the compressor at a first speed, and the second turbine rotor drives the propulsor at a second speed. There is a control for the gas turbine engine. The control is programmed to compare one of the first speed and the second speed to a commanded speed to determine a difference. The control also is programmed to identify a flame out condition, and identify a locked in stall condition when the difference between the two speeds exceeds a threshold for at least a threshold period of time at least in part concurrently with the flame out condition. The control is programmed to take a corrective action should the locked in stall condition be identified. A method is also disclosed.

Several embodiments include a system and method for providing thrust recovery in an aircraft engine. The system and method enables a wider range of safe operation for aircraft where the aircraft engine is rapidly reactivated from a substantially deactivated state. The method thereby reduces noise output and fuel usage during descent and shortens runway lengths and occupancy time required for landing. Thrust recovery is provided via the use of stored bleed air being re-injected back into the aircraft engine. An onboard air storage tank and a system of valves facilitating this method are disclosed.

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

A system and method for preventing a flame out condition in at least one engine, includes detecting a moisture content exceeding a threshold moisture content in an operating environment of the at least one engine, and engaging at least one igniter associated with the at least one engine in response to the moisture content.