A combustor of a gas turbine engine oriented about an engine axis, the combustor comprising: a combustor case extending along a primary combustor centerline to convey compressed airflow from a compressor to a turbine section, wherein the combustor case comprises a torch igniter opening; a combustor liner disposed within the combustor case to define a main combustor zone; at least one fuel nozzle situated at an upstream end of the combustor liner, relative to the primary combustor centerline; and a torch igniter situated partially within the combustor case, the torch igniter comprising: a combustion chamber extending along a torch igniter axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber with respect to the torch igniter axis; a cap defining the axially upstream end of the combustion chamber with respect to the torch igniter axis, wherein the cap is configured to receive at least one surface igniter and at least one fuel injector; a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis; an annular igniter wall extending along and surrounding the torch igniter axis from the cap to the tip and defining a radial extent of the combustion chamber; a structural wall coaxial with and surrounding the igniter wall; and an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber; wherein the torch igniter is situated within the torch igniter opening such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case, wherein the torch igniter is oriented such that the torch igniter axis extends radially inward with respect to the primary combustor centerline and the engine axis, characterized in that the tip comprises an elbow between the combustion chamber and the combustor liner, and wherein the elbow turns 90 degrees from the combustion chamber to the combustor liner, wherein the tip of the torch igniter is mounted to the combustor liner at an axially upstream end of the combustor liner with respect to the primary combustor centerline. a combustor case extending along a primary combustor centerline to convey compressed airflow from a compressor to a turbine section, wherein the combustor case comprises a torch igniter opening; a combustor liner disposed within the combustor case to define a main combustor zone; at least one fuel nozzle situated at an upstream end of the combustor liner, relative to the primary combustor centerline; and a torch igniter situated partially within the combustor case, the torch igniter comprising: a combustion chamber extending along a torch igniter axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber with respect to the torch igniter axis; a cap defining the axially upstream end of the combustion chamber with respect to the torch igniter axis, wherein the cap is configured to receive at least one surface igniter and at least one fuel injector; a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis; an annular igniter wall extending along and surrounding the torch igniter axis from the cap to the tip and defining a radial extent of the combustion chamber; a structural wall coaxial with and surrounding the igniter wall; and an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber; wherein the torch igniter is situated within the torch igniter opening such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case, wherein the torch igniter is oriented such that the torch igniter axis extends radially inward with respect to the primary combustor centerline and the engine axis, a combustion chamber extending along a torch igniter axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber with respect to the torch igniter axis; a cap defining the axially upstream end of the combustion chamber with respect to the torch igniter axis, wherein the cap is configured to receive at least one surface igniter and at least one fuel injector; a tip defining the axially downstream end of the combustion chamber with respect to the torch igniter axis; an annular igniter wall extending along and surrounding the torch igniter axis from the cap to the tip and defining a radial extent of the combustion chamber; a structural wall coaxial with and surrounding the igniter wall; and an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber; wherein the torch igniter is situated within the torch igniter opening such that the tip is mounted through the combustor liner, the combustion chamber is within the combustor case, and the cap extends through the combustor case, wherein the torch igniter is oriented such that the torch igniter axis extends radially inward with respect to the primary combustor centerline and the engine axis,