A gas turbine engine comprising: a high pressure turbine system; a low pressure turbine system; a mid-turbine frame system (304; 900) arranged axially between the high pressure turbine system and the low pressure turbine system along an engine axis; a cooling air conduit (310; 904) fluidly connected to the mid-turbine frame system (304; 900), the cooling air conduit configured to supply a cooling air to the mid-turbine frame system through a conduit outlet; and a flow diverter (318; 400; 902) installed at the conduit outlet, the flow diverter having a diverter body comprising: a connector portion (408; 912) defining a diverter inlet (402; 916); a diverter extension (410; 920) at least partially defining a diverter outlet (404; 918); and a curved portion (418; 922) arranged between the connector portion (408; 912) and the diverter extension (410; 920), the curved portion configured to change a direction of flow that is substantially radial relative to the engine axis to substantially axial relative to the engine axis as the flow passes from the diverter inlet (402; 916) to the diverter outlet (404; 918), wherein the flow diverter (318; 400; 902) is installed within the conduit outlet such the air passing through the flow diverter is directed aftward toward the low pressure turbine system, characterized in that the flow diverter (318; 400) includes at least one diversion slot arranged proximate the connector portion (408; 912) and closer to the diverter inlet (402; 916) than the diverter outlet (404; 918), the at least one diversion slot configured to allow a portion of the flow through the flow diverter to flow in a non-aftward direction, and in that the non-aftward direction portion of the flow is between about 0% and about 50% of the total flow through the flow diverter (318; 400). a high pressure turbine system; a low pressure turbine system; a mid-turbine frame system (304; 900) arranged axially between the high pressure turbine system and the low pressure turbine system along an engine axis; a cooling air conduit (310; 904) fluidly connected to the mid-turbine frame system (304; 900), the cooling air conduit configured to supply a cooling air to the mid-turbine frame system through a conduit outlet; and a flow diverter (318; 400; 902) installed at the conduit outlet, the flow diverter having a diverter body comprising: a connector portion (408; 912) defining a diverter inlet (402; 916); a diverter extension (410; 920) at least partially defining a diverter outlet (404; 918); and a curved portion (418; 922) arranged between the connector portion (408; 912) and the diverter extension (410; 920), the curved portion configured to change a direction of flow that is substantially radial relative to the engine axis to substantially axial relative to the engine axis as the flow passes from the diverter inlet (402; 916) to the diverter outlet (404; 918), wherein the flow diverter (318; 400; 902) is installed within the conduit outlet such the air passing through the flow diverter is directed aftward toward the low pressure turbine system, characterized in that the flow diverter (318; 400) includes at least one diversion slot arranged proximate the connector portion (408; 912) and closer to the diverter inlet (402; 916) than the diverter outlet (404; 918), the at least one diversion slot configured to allow a portion of the flow through the flow diverter to flow in a non-aftward direction, and in that the non-aftward direction portion of the flow is between about 0% and about 50% of the total flow through the flow diverter (318; 400). a connector portion (408; 912) defining a diverter inlet (402; 916); a diverter extension (410; 920) at least partially defining a diverter outlet (404; 918); and a curved portion (418; 922) arranged between the connector portion (408; 912) and the diverter extension (410; 920), the curved portion configured to change a direction of flow that is substantially radial relative to the engine axis to substantially axial relative to the engine axis as the flow passes from the diverter inlet (402; 916) to the diverter outlet (404; 918), wherein the flow diverter (318; 400; 902) is installed within the conduit outlet such the air passing through the flow diverter is directed aftward toward the low pressure turbine system, characterized in that the flow diverter (318; 400) includes at least one diversion slot arranged proximate the connector portion (408; 912) and closer to the diverter inlet (402; 916) than the diverter outlet (404; 918), the at least one diversion slot configured to allow a portion of the flow through the flow diverter to flow in a non-aftward direction, and in that the non-aftward direction portion of the flow is between about 0% and about 50% of the total flow through the flow diverter (318; 400).