Gas turbine engine turbine nozzle bifurcated impingement baffle

• Main Authors: POWIS, ANDREW CHARLES, CLARKE, JONATHAN PHILIP, MCRAE, RONALD EUGENE, JR, GIBLER, EDWARD EUGENE, KEITH, BRIAN DAVID, FREDERICK, ROBERT ALAN, PETERMAN, JONATHAN JORDAN
• Format: Patent
• Language: English; French; German
• Published: 28.02.2007
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

A turbine nozzle bifurcated impingement baffle (30) includes axially forward and aft chambers (53 and 55) with a gap (57) therebetween, impingement holes (70) through forward and aft baffle walls (73 and 75) of the forward and aft chambers (53 and 55) respectively, and a plenum chamber (105) in fluid flow communication with the forward and aft chambers (53 and 55). An exemplary embodiment of the bifurcated impingement baffle (30) further includes a single cooling air inlet (114) to the plenum chamber (105) enclosed within a plenum chamber enclosure (108) the plenum chamber (105). A sealing plate (109) is mounted between and sealed to the plenum chamber enclosure (108) and the forward and aft chambers (53 and 55). The sealing plate (109) has forward and aft inlet apertures (131 and 133) disposed between the plenum chamber (105) and the forward and aft chambers (53 and 55) respectively. Forward and aft end plates (113 and 115) cap radially inner ends (111) of the forward and aft chambers (53 and 55). An outlet aperture (117) in the forward end plate (113) has an interstage seal cavity feed tube (119) disposed therethrough.