A gas turbine engine combustor includes a dome plate, an inner liner, and an outer liner. The inner liner and the outer liner are separately coupled to a rear side of the dome plate and both extend rearward therefrom. The outer and inner liners define an annular combustion chamber therebetween that extends rearward from the dome plate. At least one of the outer liner or the dome plate includes an igniter cavity formed therein that is separated from the combustion chamber by a partition wall. The partition wall defines one or more transfer holes therethrough that fluidly connect the igniter cavity to the combustion chamber.

A gas turbine engine combustor includes a dome plate, an inner liner, and an outer liner. The inner liner and the outer liner are separately coupled to a rear side of the dome plate and both extend rearward therefrom. The outer and inner liners define an annular combustion chamber therebetween that extends rearward from the dome plate. At least one of the outer liner or the dome plate includes an igniter cavity formed therein that is separated from the combustion chamber by a partition wall. The partition wall defines one or more transfer holes therethrough that fluidly connect the igniter cavity to the combustion chamber.

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 gas turbine engine including a fan and an oil pump operatively connected to the fan by a main input drive gear, the drive gear rotating when the fan rotor rotates in either a first or second direction of the fan. Further included is a gear train intermediate the main input drive gear and the oil pump, the gear train including a first and second pinion gear, the first and second pinion gear each driven by the main input drive gear, the first pinion gear driving a first gear through a first clutch, the second pinion gear driving a second gear through a second clutch. Only one of the clutches transmits rotation from the respective pinion gear to the respective gear when the fan is rotating in the first direction, with the only the other clutch transmitting rotation when the fan is rotating in the second direction.

A gas turbine engine including a fan and an oil pump operatively connected to the fan by a main input drive gear, the drive gear rotating when the fan rotor rotates in either a first or second direction of the fan. Further included is a gear train intermediate the main input drive gear and the oil pump, the gear train including a first and second pinion gear, the first and second pinion gear each driven by the main input drive gear, the first pinion gear driving a first gear through a first clutch, the second pinion gear driving a second gear through a second clutch. Only one of the clutches transmits rotation from the respective pinion gear to the respective gear when the fan is rotating in the first direction, with the only the other clutch transmitting rotation when the fan is rotating in the second direction.

A propulsion system includes a gas turbine designed so that a combustion chamber can be ignited in a first ignition range of rotational speeds of a compressor shaft. The system further includes a control device designed to control an electric starter to accelerate the compressor shaft and, when the compressor shaft is accelerated, to control an attempt to ignite the combustion chamber. The gas turbine is designed so that the combustion chamber can be ignited in a second ignition range which is higher than the first ignition range, but not between these two ignition ranges, and the ignition attempt is carried out in the second ignition range.

A method for igniting a continuous combustion engine including an electronic engine control member, a high energy box, a spark plug ignition circuit and a fuel solenoid valve, cooperating with a starter motor, the method being implemented by the electronic engine control member and including precharging the high energy box before an engine starting procedure, activated on an engine starting command, the precharging being controlled by switching on the electronic engine control member, or by putting the engine in idle mode.

A system for automated management of in-flight restarting of engines of an aircraft includes controllers, each engine of the aircraft being managed by one of the controllers. A controller that detects an engine that has stopped: cuts off the energy supply of the engine and performs a windmill engine start. If at least one other engine has stopped, prioritization of engine restarting includes: collecting information concerning a state of health of each engine; determining from the information collected information representing a probability of restarting each stopped engine; determining a sequential order of restarting the stopped engines as a function of information representing the probability of restarting each stopped engine. Each stopped engine continues to be windmill started until selection of the engine in question in the sequential order of restarting the stopped engines. Thus, the operational status of the aircraft is improved as quickly as possible.

A system for automated management of in-flight restarting of engines of an aircraft includes controllers, each engine of the aircraft being managed by one of the controllers. A controller that detects an engine that has stopped: cuts off the energy supply of the engine and performs a windmill engine start. If at least one other engine has stopped, prioritization of engine restarting includes: collecting information concerning a state of health of each engine; determining from the information collected information representing a probability of restarting each stopped engine; determining a sequential order of restarting the stopped engines as a function of information representing the probability of restarting each stopped engine. Each stopped engine continues to be windmill started until selection of the engine in question in the sequential order of restarting the stopped engines. Thus, the operational status of the aircraft is improved as quickly as possible.