| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustor 16 for a gas turbine engine 10. SOLUTION: The combustor comprises an outside combustor liner 32 defining at least a part of a combustion chamber 30. The outside combustor liner 32 has a first end 34 radially extended to define a combustion chamber input opening, and a second end 38 axially extended to define an output opening of the combustion chamber. The first end shifts to the second end to define the circular arc shaped cross section of the combustor liner. The combustor comprises a dome assembly 50 connected to the first end extending downstream of the dome assembly, and the dome assembly 50 comprises a cyclone 120 having a plurality of cyclone stator blades 122 arranged around the cyclone. The combustor comprises fuel nozzles 64 arranged within a range of the cyclone of radial constitution. COPYRIGHT: (C)2007,JPO&INPIT |
