A torch ignitor system for use within a gas turbine engine, the torch ignitor system comprising: a housing comprising an outer case, an inner case, and an internal chamber, wherein the inner case includes a plurality of swirler holes extending through the inner case such that the plurality of swirler holes are spaced equidistance about a circumference of the inner case and the plurality of swirler holes extend through the inner case at an oblique angle with respect to a tangential plane adjacent an outer surface of the inner case; a flow channel including: a first end suitable to be positioned within and fluidly connected to a high-pressure compressor region of the gas turbine engine; and a second end coupled to and fluidly connected to the housing; wherein the flow channel provides a flow path for high-pressure air from the high-pressure compressor region through the second end of the flow channel to the housing; wherein the second end of the flow channel is offset from the swirler holes in the inner case, such that high-pressure air flowing from the second end of the flow channel engages the inner case before flowing through the swirler holes into the internal chamber of the housing; a torch ignitor positioned at least partially within the internal chamber of the housing; and an outlet nozzle fluidly connected to the internal chamber of the housing and fluidly connected to a combustor of the gas turbine engine; wherein a gap is located between the outer case and the inner case of the housing, wherein the gap allows high-pressure air received from the high-pressure compressor region to flow in a circular motion between an inner surface of the outer case and an outer surface of the inner case; wherein the torch ignitor is configured to ignite a fuel and air mixture within the internal chamber of the housing, and wherein the outlet nozzle is configured to expel the ignited fuel and air mixture into the combustor of the gas turbine engine, characterized in that the flow channel is angled such that the angle of flow channel and the angles in which the swirler holes extend through the inner case are similar to limit pressure loss within the torch igniter system when high-pressure air from the high-pressure compressor flows into the gap of the housing and then through the swirler holes. a housing comprising an outer case, an inner case, and an internal chamber, wherein the inner case includes a plurality of swirler holes extending through the inner case such that the plurality of swirler holes are spaced equidistance about a circumference of the inner case and the plurality of swirler holes extend through the inner case at an oblique angle with respect to a tangential plane adjacent an outer surface of the inner case; a flow channel including: a first end suitable to be positioned within and fluidly connected to a high-pressure compressor region of the gas turbine engine; and a second end coupled to and fluidly connected to the housing; wherein the flow channel provides a flow path for high-pressure air from the high-pressure compressor region through the second end of the flow channel to the housing; a first end suitable to be positioned within and fluidly connected to a high-pressure compressor region of the gas turbine engine; and a second end coupled to and fluidly connected to the housing; wherein the flow channel provides a flow path for high-pressure air from the high-pressure compressor region through the second end of the flow channel to the housing; wherein the second end of the flow channel is offset from the swirler holes in the inner case, such that high-pressure air flowing from the second end of the flow channel engages the inner case before flowing through the swirler holes into the internal chamber of the housing; a torch ignitor positioned at least partially within the internal chamber of the housing; and an outlet nozzle fluidly connected to the internal chamber of the housing and fluidly connected to a combustor of the gas turbine engine; wherein a gap is located between the outer case and the inner case of the housing, wherein the gap allows high-pressure air received from the high-pressure compressor region to flow in a circular motion between an inner surface of the outer case and an outer surface of the inner case; wherein the torch ignitor is configured to ignite a fuel and air mixture within the internal chamber of the housing, and wherein the outlet nozzle is configured to expel the ignited fuel and air mixture into the combustor of the gas turbine engine, characterized in that the flow channel is angled such that the angle of flow channel and the angles in which the swirler holes extend through the inner case are similar to limit pressure loss within the torch igniter system when high-pressure air from the high-pressure compressor flows into the gap of the housing and then through the swirler holes.