| 摘要 |
1,113,087. Gas turbine ducted fan engines; axial-flow fans. ROLLS-ROYCE Ltd. Feb. 27, 1967, No. 9300/67. Headings F1C and F1J. A gas turbine power plant comprises an annular main flow duct having mounted in flow series therein compressor means, combustion equipment, first turbine means driving the compressor means, and separate turbine means. An annular fan duct surrounds the main flow duct, the fan comprising at least two fan rotor stages with no intermediate stage of blading therebetween, the said fan rotor stages being mounted on a common rotor which is driven by the separate turbine means. The gas turbine ducted fan engine shown comprises LP compressor 8, HP compressor 9, combustion equipment 10, HP turbine 11 and LP turbine 12, the HP and LP turbines driving the HP and LP compressors respectively. The gases discharging from the LP turbine pass into an annular duct 15 of S-shape in which is disposed a fan-driving turbine assembly 17. The turbine assembly 17 comprises a first centrifugal stage 21, a second, outward radial flow stage 22 and a third axial flow stage 23, the gases finally discharging through a propulsion nozzle 19. The three turbine stages 21, 22, 23 are mounted on a common rotor 28 which is connected to a ducted fan rotor 27 on which are mounted two ducted fan rotor stages 25, 26, the fan blades being disposed in a duct formed between inner and outer walls 3 and 2. No stator blade stage is disposed between the fan stages 25, 26. Outlet guide blades 24 are disposed downstream of the fan rotor stage 26, being spaced therefrom by a distance between two and three times the mean chord length of the blades of the fan stage 26. The fan blades 26 may be offset circumferentially with respect to the blades 25. |
