METHODS AND APPARATUS FOR ASSEMBLING TURBINE ENGINES

• Main Authors: LU, WENFENG, LEE, CHING-PANG, GNIAZDOWSKI, ROBERT ANDRZEJ, RONIEWICZ, JAKUB, FORTUNA, DOUGLAS MARTI
• Format: Patent
• Language: English; French
• Published: 16.12.2014
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; 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; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE; WEAPONS

A combustion assembly for a gas turbine engine (10) is provided. The combustion assembly includes a combustor (16) including a plurality of circumferentially- spaced cooling openings (190), and a turbine nozzle assembly (50) downstream from and in flow communication with the combustor, the nozzle assembly including an outer band (54), an inner band (56), and at least one vane (52) extending between the outer and inner bands, the outer band and the inner band each including a leading edge (64), the at least one vane including a first sidewall (60) and a second sidewall (62) connected together at a leading edge and a trailing edge (66), the at least one vane leading edge positioned downstream from the inner and outer band leading edges, the plurality of circumferentially-spaced cooling openings configured to bias cooling air discharged therefrom towards the nozzle vane leading edge.