Turbine nozzle segment cantilevered mount

• Main Authors: POWIS, ANDREW CHARLES, CLARKE, JONATHAN PHILIP, GIBLER, EDWARD EUGENE, MCRAE, RONALD EUGENE JR, KEITH, BRIAN DAVID, FREDERICK, ROBERT ALAN, PETERMAN, JONATHAN JORDAN
• Format: Patent
• Language: English; French; German
• Published: 21.02.2007
• 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 segment (10) includes at least one hollow airfoil (28) extending radially between radially outer and inner band segments (24 and 26), a clockwise open hook (124) on a clockwise end (138) at an aft end (128) of the outer band segment (24), and counter-clockwise open hook (126) on a counter- clockwise end (140) at the aft end (128) of the outer band segments (24). An exemplary embodiment of the turbine nozzle segment (10) includes a load stop (144) extending radially outwardly from the outer band segment (24). At least one aftwardly facing load face (150) is at the aft end (128) of the nozzle segment (10) at the outer band segment (24). The clockwise open hook (124) is C-shaped and the counter-clockwise open hook (126) is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.