Gas turbine engine with bypass TOBI cooling/purge flow and method

A gas turbine engine having an axial centerline, comprising:

• a high-pressure compressor (HPC) having an HPC rotor stage and an HPC stator vane stage, the HPC rotor stage having a disk and a plurality of HPC rotor blades, and the HPC stator vane stage having a plurality of HPC stator vanes, the HPC having an HPC discharge at an aft end of the HPC;
• a combustor section having a combustor;
• a high-pressure turbine (HPT) having an HPT rotor stage and an HPT stator vane stage, the HPT rotor stage having a disk and a plurality of HPT rotor blades, and the HPT stator vane stage having a plurality of HPT stator vanes;
• wherein a core gas path extends through the HPC, the combustor section, the HPT, and exits through the HPC discharge;
• wherein a gas leakage flow is a bled gas off of the core gas path forward of the HPC discharge;
• a bypass tangential on board injector (TOBI) system that extends circumferentially around the engine axial centerline, the bypass TOBI system having a plurality of nozzles, an inner radial side, an outer radial side, a plurality of first radial passages, and a plurality of second radial passages,
• wherein the gas turbine is configured such that a portion of core gas exiting the core gas path through the HPC discharge is directed to the bypass TOBI system as a diffuser inner diameter (ID) flow that passes through the plurality of nozzles,
• wherein the configuration of the plurality of first radial passages is different from the configuration of the plurality of second radial passages where the second radial passages each have a fluid flow path that directs the bled gas in an upstream direction with respect to the ID flow and the first radial passages do not direct the bled gas in the upstream direction,
• wherein the plurality of first radial passages are configured to allow the bled gas from the HPC to pass from the inner radial side of the bypass TOBI system to the outer radial side of the bypass TOBI system without mixing with the diffuser ID flow passing through the plurality of nozzles,
• and wherein the plurality of second radial passages are configured to allow the bled gas from the HPC to pass from the inner radial side of the bypass TOBI system to the outer radial side of the bypass TOBI system without mixing with the diffuser ID flow passing through the plurality of nozzles.