| 摘要 |
A gas turbine engine has a core gas generator engine 18, 16, 20, 22 for generating combustion gases, a power turbine 34, a front fan section 60, 62, and a booster compressor 64. The power turbine includes two counter rotatable turbine blade rows 38, 42 which are alternately interdigitized and serve to rotate counter rotating first and second drive shafts 46, 48 respectively. The fan section also includes counter rotating spaced apart fan blade sections 60, 62 which are respectively connected to the first and second drive shafts. The booster compressor 64 is axially positioned between the spaced apart fan sections. The booster compressor likewise includes first and second blade rows 68, 72 which are counter rotating alternately interdigitized and are likewise driven by the first and second drive shafts 46, 48. The engine is supported from two frames to permit the nacelle to be non-structural. The core engine is a modular unit so that it can be separable from the counter rotating turbine, fans and booster. A fan duct 56, may be supported via struts 58 (six or eight) which remove swirl from the air. <IMAGE> |
