A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.

A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor has a flame outlet opening into the main flow passage of the fuel nozzle for issuing flame into the main flow passage.

A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor has a flame outlet opening into the main flow passage of the fuel nozzle for issuing flame into the main flow passage.

A method of operating a torch ignitor for continuous ignition includes issuing a flame from a combustion chamber of a torch ignitor into a combustor of a gas turbine engine while the gas turbine engine is not issuing fuel through fuel injectors into the combustor. The method includes heating interior surfaces of the combustor with the flame, wherein heat from the flame reacts with carbon deposits on the interior surfaces to remove the carbon deposits.

A method of operating a torch ignitor for continuous ignition includes issuing a flame from a combustion chamber of a torch ignitor into a combustor of a gas turbine engine while the gas turbine engine is not issuing fuel through fuel injectors into the combustor. The method includes heating interior surfaces of the combustor with the flame, wherein heat from the flame reacts with carbon deposits on the interior surfaces to remove the carbon deposits.

A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle includes a nozzle body that defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor with a flame outlet opens into the main flow passage of the fuel nozzle for issuing flame into the main flow passage. The flame outlet meets the main flow passage at a position that is downstream of the fuel outlet with respect to the downstream direction along the injection axis.

A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle includes a nozzle body that defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor with a flame outlet opens into the main flow passage of the fuel nozzle for issuing flame into the main flow passage. The flame outlet meets the main flow passage at a position that is downstream of the fuel outlet with respect to the downstream direction along the injection axis.

An aircraft comprising a turbine engine, an atomizer, a reservoir, a conduit connecting the reservoir to the atomizer, and a unit for controlling the flow of liquid in the atomizer. The turbine engine, the atomizer, the reservoir, the conduit and the control unit are fixed to the aircraft. This allows cleaning in flight of at least some parts of the turbine engine.

An aircraft comprising a turbine engine, an atomizer, a reservoir, a conduit connecting the reservoir to the atomizer, and a unit for controlling the flow of liquid in the atomizer. The turbine engine, the atomizer, the reservoir, the conduit and the control unit are fixed to the aircraft. This allows cleaning in flight of at least some parts of the turbine engine.

A fuel injector includes a fuel nozzle configured to issue a spray of fuel from a fuel outlet in a downstream direction along an injection axis. The fuel nozzle defines a main flow passage therethrough. An injection fuel line is in fluid communication with the fuel nozzle to supply fuel to the fuel nozzle. A torch ignitor has a flame outlet opening into the main flow passage of the fuel nozzle for issuing flame into the main flow passage.