| 摘要 |
PROBLEM TO BE SOLVED: To provide a turbo fan engine capable of improving output in an output part installed separately from an engine body. SOLUTION: In the turbo fan engine 1, a duct D diverging from between a high-pressure turbine 14 and a low-pressure turbine 15 is connected to a lift fan part 20 installed separately from the engine body part 10. The duct D is provided with a valve 25. By adjusting the valve 25 to flow gas into the duct D, the high-temperature high-pressure combustion gas combusted in a combustor 13 passes through the high-pressure turbine 14, flows in the duct D, and is supplied to the lift fan part 20. Accordingly, as the gas supplied to the lift fan part 20 is high-temperature gas after combustion, the output in the lift fan part 20 of an aircraft can be improved. COPYRIGHT: (C)2010,JPO&INPIT
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