| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustor of a gas turbine engine having sufficient performance and durability, and capable of reducing the emission of control subjects. SOLUTION: A fuel distribution manifold disc 38 belongs to an upstream-side end 52 of a nozzle 42. Combustion air passages 56, 58, 60 are made to corresponded to an air passage in the nozzle 42, and aligned with the passage. A fuel distribution groove 66 is formed at one end of the fuel distribution manifold disc 38, and extends to the air passage from a central opening 68. A fuel circuit cover closes the fuel distribution groove 66, and forms a fuel passage extending from the central opening 68 to the combustion air passages 46, 48, 50. A fuel supply conduit communicate with the central opening 68 and the fuel passage, and supplies the fuel to the combustion air in the air passage. COPYRIGHT: (C)2010,JPO&INPIT
|
