Abstract: Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.

Abstract: Herein provided are methods and systems for reducing an acoustic signature of a gas turbine engine. An acceleration command for the engine is received. In response to receiving the acceleration command: a fuel flow to the engine is increased for a first predetermined time period; subsequent to the first predetermined time period, the fuel flow to the engine is reduced for a second predetermined time period; and subsequent to the second predetermined time period, the fuel flow to the engine is increased for a third time period.

Abstract: Herein provided are systems and methods for operating an engine of an aircraft. The engine is operated at a first fuel flow rate. An indication of a measured humidity level within the engine is obtained from a humidity sensor coupled to the engine. A determination is made regarding whether the measured humidity level within the engine is indicative that a flameout risk for the engine is below a predetermined risk level. Responsive to determining that the flameout risk is below the predetermined risk level, the engine is operated at a second fuel flow rate lower than the first fuel flow rate.

Abstract: Systems and methods for mitigating flameout risk in an engine of an aircraft are provided. A humidity value is obtained from a humidity sensor associated with the engine. A flameout risk for the engine is determined based on the humidity value. The flameout risk is compared to a predetermined risk threshold. When the flameout risk is above the predetermined risk threshold, a rate of fuel flow to the engine is increased.

Abstract: Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.

Abstract: Herein provided are methods and systems for reducing an acoustic signature of a gas turbine engine. An acceleration command for the engine is received. In response to receiving the acceleration command: a fuel flow to the engine is increased for a first predetermined time period; subsequent to the first predetermined time period, the fuel flow to the engine is reduced for a second predetermined time period; and subsequent to the second predetermined time period, the fuel flow to the engine is increased for a third time period.

Abstract: Method and system are disclosed for starting a high voltage engine using a starter permanent magnet motor. The starter motor is powered using a DC power source remote from the starter motor. A bidirectional DC-to-DC converter local to the DC power source is used to produce a variable high voltage variable frequency power for driving the starter motor, and is remotely controlled to produce a controlled output current level. During generate mode the DC-DC converter may be used to charge the battery.