| 摘要 |
PROBLEM TO BE SOLVED: To provide a rear FLADE type engine for an aircraft. SOLUTION: The rear FLADE type gas turbine engine 1 comprises a fan section 115 drivenly connected to a low pressure turbine section 150, a core engine 18 installed between the fan section 115 and the low pressure turbine section 150, a fan bypass duct 40 encircling the core engine 18 in fluid communication with the fan section, a mixer 49 installed on the downstream side of the low pressure turbine section in fluid communication with the fan bypass duct, and a rear FLADE turbine 160 installed on the downstream side of the mixer. At least one train of rear FLADE fan blades 5 are installed on the radial outside of the rear FLADE turbine and joined to the rear FLADE turbine, and they radially extend across a FLADE duct 3 encircling the fan bypass duct. COPYRIGHT: (C)2005,JPO&NCIPI
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