BACKGROUND

The present disclosure relates to continuous ignition devices within gas turbine engines, and more particularly to an exhaust manifold used with a continuous ignition device within a gas turbine engine.

Torch ignitors can be used in lieu of spark ignitors to provide an ignition source for combustors located in gas turbine engines. Torch ignitors provide a flame to the combustor of a gas turbine engine as an ignition source rather than the electric current provided by spark ignitors. Consequently, torch ignitors can provide a larger target for fuel injectors within the combustor, allowing for utilization of a greater range of fuel injector designs. Traditionally, torch ignitors include a single torch or flame jetting into the combustor of the gas turbine engine to ignite the fuel sprayed from the fuel nozzles within the gas turbine engine.

SUMMARY

According to one aspect of the disclosure, a torch ignitor system for use with a gas turbine engine including a high-pressure compressor, a high-pressure case, fuel nozzles, and a combustor is disclosed. The torch ignitor system includes a torch ignitor, a manifold, and a combustion chamber. The torch ignitor is coupled to the high-pressure case of the gas turbine engine. The manifold is positioned within the high-pressure case and the manifold includes a plurality of torch nozzles extending from the manifold into the combustor of the gas turbine engine. The combustion chamber is positioned within the high-pressure case and the combustion chamber includes a first end coupled to the torch ignitor and a second end coupled and fluidly connected to the manifold. The combustion chamber is configured such that in operation, an ignited fuel and air mixture flows through the combustion chamber, into and through the manifold, and exits through each of the plurality of torch nozzles into the combustor of the gas turbine engine.

According to another aspect of the disclosure, a method of igniting fuel within a combustor of a gas turbine engine including a high-pressure compressor, a high-pressure case, fuel nozzles, and a combustor is disclosed. The method including: igniting, by a torch ignitor of a torch ignitor system, a fuel and air mixture within a combustion chamber of the torch ignitor system, wherein the torch ignitor is coupled to the high-pressure case of the gas turbine engine; flowing the ignited fuel and air mixture through the combustion chamber from a first end of the combustion chamber to a second end of the combustion chamber, wherein the first end is coupled to the torch ignitor and the second end is coupled and fluidly connected to a manifold, and wherein the combustion chamber is positioned within the high-pressure case of the gas turbine engine; flowing the ignited fuel and air mixture from the second end of the combustion chamber into and through the manifold, wherein the manifold is positioned within the high-pressure case of the gas turbine engine; and flowing the ignited fuel and air mixture from the manifold through a plurality of torch nozzles extending from the manifold into the combustor of the gas turbine engine, wherein the ignited fuel and air mixture exits the torch nozzles into the combustor and ignites the fuel sprayed from the fuel nozzles into the combustor of the gas turbine engine.

