COMBUSTOR FOR GAS TURBINE ENGINE WITH RADIALLY ORIENTED INTERNALLY MOUNTED TORCH IGNITER

An embodiment of a combustor for a gas turbine engine includes a combustor case (20), a combustor liner (24) disposed within the combustor case, a fuel nozzle (27), and a torch igniter (10) within the combustor case (20). The torch igniter (10) includes a combustion chamber (22), a cap (18) defining the upstream end of the combustion chamber and configured to receive a fuel injector and a surface igniter, a tip (14) defining the downstream end of the combustion chamber, an annular igniter wall (32) extending from the cap (18) to the tip (14) and defining a radial extent of the combustion chamber (22), a structural wall (36) coaxial with and surrounding the igniter wall (32), and an outlet passage (34) within the tip (14) that fluidly connects the combustion chamber (22) to the combustor. The torch igniter (10) is situated such that the tip (14) is mounted through the combustor liner (24), the combustion chamber (22) is within the combustor case (20), and the cap (18) extends through the combustor case (20).