TURBINE ENGINE WITH TANGENTIAL ONBOARD INJECTOR (TOBI) SUPPORTING VANES

A gas turbine engine (20) includes a circumferential row of vanes (62) arranged about a central engine axis (A). The vanes (62) include respective internal cavities (66) and vane outlet ports (72) for conveying cooling air. A tangential onboard injector (TOBI) (76) radially supports the vanes (62) a...

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Bibliographische Detailangaben
1. Verfasser:	LILES, Howard J
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Zusammenfassung:	A gas turbine engine (20) includes a circumferential row of vanes (62) arranged about a central engine axis (A). The vanes (62) include respective internal cavities (66) and vane outlet ports (72) for conveying cooling air. A tangential onboard injector (TOBI) (76) radially supports the vanes (62) at an inner diameter of the circumferential row. The TOBI (76) includes fore and aft annular walls (78a, 78b) and an outer diameter annular wall (80). The fore and aft annular walls (78a, 78b) and the outer diameter annular wall (80) define an annular plenum (82). The outer diameter annular wall (80) includes TOBI inlet ports (86) that are connected, respectively, with the vane outlet ports (72) to receive the cooling air from each of the vanes (62) into the plenum (82). The TOBI (76) includes axially-oriented nozzles (84) for discharging the cooling air from the plenum (82) in an aft direction.