Continuous ignition device exhaust manifold

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, the method comprising:

• 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 wherein the manifold is annular in shape with a circular cross-section such that the manifold is a torus shaped manifold;
• 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.

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, the torch ignitor system comprising:

• a torch ignitor coupled to the high-pressure case of the gas turbine engine;
• a manifold positioned within the high-pressure case, the manifold comprising a plurality of torch nozzles extending from the manifold into the combustor of the gas turbine engine;
• and
• a combustion chamber positioned within the high-pressure case, the combustion chamber comprising:
• a first end coupled to the torch ignitor;
• and
• a second end coupled and fluidly connected to the manifold;
• wherein 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;
• wherein the manifold is split at a location opposite the location where the second end of the combustion chamber is coupled to the manifold, and wherein at least one cap is positioned over an aperture created by the split.