Methods and apparatus for operating gas turbine engine...

F - Mech Eng,Light,Heat,Weapons – 02 – C

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F02C 1/00 (2006.01) F23M 5/04 (2006.01) F23R 3/00 (2006.01) F23R 3/02 (2006.01) F23R 3/42 (2006.01) F23R 3/60 (2006.01)

Patent

CA 2464849

A method facilitates assembling a gas turbine engine (10). The method comprises coupling a combustor (16) including a dome assembly (94) and a combustor liner (90, 92) that extends downstream from the dome assembly to a combustor casing (95) that is positioned radially outwardly from the combustor, coupling a ring support (112) that includes a first radial flange (114), a second radial flange (116), and a plurality of beams (118) that extend therebetween to the combustor casing, and coupling a primer nozzle (30) including an injection tip (34) to the combustor such that the primer nozzle extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor during engine start-up operating conditions.

Méthode facilitant l'assemblage d'une turbine à gaz (10). La méthode consiste à accoupler une chambre de combustion (16) comportant un dôme (94) et une chemise de chambre de combustion (90, 92) qui se prolonge derrière le dôme vers une enveloppe de chambre de combustion (95) qui est placé de manière radiale vers l'extérieur de ladite chambre de combustion, accouplée à un support annulaire (112) qui comprend une première bride radiale (114), une seconde bride radiale (116) et plusieurs longerons (118) qui se prolongent de là jusqu'à l'enveloppe de la chambre de combustion, et qui sont accouplés à une buse d'amorçage (30) qui inclue une pointe d'injection (34) vers la chambre de combustion, de telle sorte que la buse d'amorçage se prolonge sur le plan axial à travers le dôme, de manière à ce que le carburant puisse être injecté de la buse d'amorçage dans la chambre de combustion pendant la mise en marche de la turbine à gaz.

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