The invention relates to a method for regulating an acceleration of a turbomachine, the turbomachine comprising a combustion chamber, a high-pressure turbine located downstream of the combustion chamber and which drives a high-pressure shaft in rotation, and a low-pressure turbine located downstream of the high-pressure turbine and which drives a low-pressure shaft in rotation, characterized in that the method comprises the following steps: Injecting (100) mechanical power onto the high-pressure shaft until a speed of the high-pressure shaft attains a target value, then Extracting (200) mechanical power from the high-pressure shaft so as to maintain the speed at the target value.

There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.

There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.

A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: determining when a flame in a combustion chamber of a gas turbine engine is extinguished, during a start-up process or re-light process or during operation; purging the combustion chamber by controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; and controlling rotation of the low pressure compressor using the first electrical machine, and controlling rotation of the high pressure compressor using the second electrical machine to restart the start-up process or perform the re-light process.

Methods and systems are provided for operating an engine with a series gap igniter. In one example, a system may include a series gap igniter coupled to a cylinder head of a cylinder, the series gap igniter including a first spark gap in an internal volume of the series gap igniter and a second spark gap of the series gap igniter external to the internal volume of the series gap igniter and within a clearance volume of the cylinder. In this way, a cylinder with a series gap igniter may be operated to efficiently and reliably initiate combustion over a range of engine operating conditions.

Methods and systems are provided for operating an engine with a series gap igniter. In one example, a system may include a series gap igniter coupled to a cylinder head of a cylinder, the series gap igniter including a first spark gap in an internal volume of the series gap igniter and a second spark gap of the series gap igniter external to the internal volume of the series gap igniter and within a clearance volume of the cylinder. In this way, a cylinder with a series gap igniter may be operated to efficiently and reliably initiate combustion over a range of engine operating conditions.

An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.

A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.

There are described methods and systems for operating a glow plug. The method comprises monitoring a glow plug current; applying a nominal voltage V.sub.N to the glow plug when the glow plug current is between an upper threshold I.sub.1 and a lower threshold I.sub.2<I.sub.1; applying a voltage V.sub.H>V.sub.N to the glow plug when the glow plug current exceeds the upper threshold I.sub.1; and applying substantially no voltage to the glow plug when the glow plug current falls below the lower threshold I.sub.2.

There are described methods and systems for operating a glow plug. The method comprises monitoring a glow plug current; applying a nominal voltage V.sub.N to the glow plug when the glow plug current is between an upper threshold I.sub.1 and a lower threshold I.sub.2<I.sub.1; applying a voltage V.sub.H>V.sub.N to the glow plug when the glow plug current exceeds the upper threshold I.sub.1; and applying substantially no voltage to the glow plug when the glow plug current falls below the lower threshold I.sub.2.