Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.

Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.

Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.

Abstract: Systems and methods for detecting inclement weather in the vicinity of an aircraft engine are described herein. At least a first engine parameter and a second engine parameter are obtained, each engine parameter varies with changing weather conditions. An arithmetic value is determined as a function of at least the first engine parameter and the second engine parameter. The arithmetic value varies with changing weather conditions. A rate of change of the arithmetic value is determined. Inclement weather is detected when the rate of change exceeds a threshold.

Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.

Abstract: Systems and methods for detecting inclement weather in the vicinity of an aircraft engine are described herein. At least a first engine parameter and a second engine parameter are obtained, each engine parameter varies with changing weather conditions. An arithmetic value is determined as a function of at least the first engine parameter and the second engine parameter. The arithmetic value varies with changing weather conditions. A rate of change of the arithmetic value is determined. Inclement weather is detected when the rate of change exceeds a threshold.