Flow diverter for mid-turbine frame cooling air delivery

A gas turbine engine comprising:

• a high pressure turbine system;
• a low pressure turbine system;
• a mid-turbine frame system arranged axially between the high pressure turbine system and the low pressure turbine system along an engine axis;
• a cooling air conduit fluidly connected to the mid-turbine frame system, the cooling air conduit configured to supply a cooling air to the mid-turbine frame system through a conduit outlet;
• and
• a flow diverter installed at the conduit outlet, the flow diverter having a diverter body comprising:
• a connector portion defining a diverter inlet;
• a diverter extension at least partially defining a diverter outlet;
• a curved portion arranged between the connector portion and the diverter extension, the curved portion configured to change a direction of flow that is a radial flow relative to the engine axis to an axial flow relative to the engine axis as the flow passes from the diverter inlet to the diverter outlet;
• at least one diversion slot formed in the diverter body and positioned proximate the connector portion at a location closer to the diverter inlet than the diverter outlet, wherein the at least one diversion slot is configured to direct a portion of the cooling air through the flow diverter to flow in a second direction different from the axial flow, wherein the second direction portion of the cooling air is equal to or less than 50% of a total flow through the flow diverter,
• wherein the flow diverter is installed within the conduit outlet such the air passing through the flow diverter is directed aftward toward the low pressure turbine system.