Turbine engine with TOBI supporting vanes

A gas turbine engine comprising:

• a circumferential row of vanes arranged about a central engine axis, each of the vanes including an airfoil section that has an internal through-cavity, inner and outer platforms between which the airfoil section extends, and a vane outlet port for conveying cooling air;
• and
• a tangential onboard injector (TOBI) radially supporting the vanes at an inner diameter of the circumferential row, the TOBI including fore and aft annular walls and an outer diameter annular wall, the fore and aft annular walls and the outer diameter annular wall defining there between an annular plenum, the outer diameter annular wall including TOBI inlet ports that are connected, respectively, with the vane outlet ports to receive the cooling air from each of the vanes into the plenum, the TOBI including a plurality of axially-oriented nozzles for discharging the cooling air from the plenum in an aft direction, and the outer diameter annular wall of the TOBI has an outer diameter surface that is in full interfacial contact with an inner diameter surface of each of the inner platforms.