A torch igniter for a combustor of a gas turbine engine, the torch igniter comprising: a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis; a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and a glow plug; a tip defining the axially downstream end of the combustion chamber; an igniter wall extending 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; an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber; a glow plug; a glow plug housing that receives said glow plug and the innermost end of the glow plug extends into the combustion chamber, the glow plug housing extending through the structural and igniter walls (116, 115) at the cap; characterized in that the torch igniter further comprises a cooling system comprising: an air inlet formed within an exterior of the structural wall, the air inlet configured to intake a flow of air from a compressor section of the gas turbine engine; a cooling channel forming a flow path extending from the air inlet and through the structural wall at the glow plug housing, the flow path including a section surrounding the glow plug housing and configured to flow air taken in at the air inlet around the glow plug housing to cool the glow plug housing; an air passage extending through the igniter wall transverse to the axis, wherein the air passage fluidly connects the cooling channel to the combustion chamber; and wherein the cooling channel comprises: a first helical portion that helically extends through the glow plug housing, is fluidly connected to the air inlet, and is configured to flow air outward from the combustion chamber and toward an end of the glow plug housing; a second helical portion that helically extends through the glow plug housing, is fluidly connected to the air passage, and is configured to flow air inward toward the combustion chamber and away from the end of the glow plug housing; and an annular portion fluidly connected to the first and second helical portions and configured to turn the flow exiting the first helical portion to enter the second helical portion. a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis; a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and a glow plug; a tip defining the axially downstream end of the combustion chamber; an igniter wall extending 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; an outlet passage defined by the igniter wall within the tip, wherein the outlet passage is fluidly connected to the combustion chamber; a glow plug; a glow plug housing that receives said glow plug and the innermost end of the glow plug extends into the combustion chamber, the glow plug housing extending through the structural and igniter walls (116, 115) at the cap; characterized in that the torch igniter further comprises a cooling system comprising: an air inlet formed within an exterior of the structural wall, the air inlet configured to intake a flow of air from a compressor section of the gas turbine engine; a cooling channel forming a flow path extending from the air inlet and through the structural wall at the glow plug housing, the flow path including a section surrounding the glow plug housing and configured to flow air taken in at the air inlet around the glow plug housing to cool the glow plug housing; an air passage extending through the igniter wall transverse to the axis, wherein the air passage fluidly connects the cooling channel to the combustion chamber; and wherein the cooling channel comprises: a first helical portion that helically extends through the glow plug housing, is fluidly connected to the air inlet, and is configured to flow air outward from the combustion chamber and toward an end of the glow plug housing; a second helical portion that helically extends through the glow plug housing, is fluidly connected to the air passage, and is configured to flow air inward toward the combustion chamber and away from the end of the glow plug housing; and an annular portion fluidly connected to the first and second helical portions and configured to turn the flow exiting the first helical portion to enter the second helical portion.