GAS TURBINE ENGINE WITH COOLING PASSAGE CIRCUIT EXTENDING THROUGH BLADE, SEAL AND CERAMIC VANE

A gas turbine engine (20) includes a rotor carrying a blade (68), a ceramic vane (70) adjacent the blade (68), a seal (80) carried on the rotor adjacent the tip of the ceramic vane (70), and a cooling passage circuit (82) extending through the blade (68), the seal (80), and the ceramic vane (70). Th...

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Bibliographische Detailangaben
1. Verfasser:	ZELESKY, Mark F
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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Beschreibung
Zusammenfassung:	A gas turbine engine (20) includes a rotor carrying a blade (68), a ceramic vane (70) adjacent the blade (68), a seal (80) carried on the rotor adjacent the tip of the ceramic vane (70), and a cooling passage circuit (82) extending through the blade (68), the seal (80), and the ceramic vane (70). The cooling passage circuit (82) is configured to provide cooling air (84) into the blade (68), then from the blade (68) into the seal (80), and then from the seal (80) into the ceramic vane (70).