| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine exhaust system suitable for a VTOL aircraft. SOLUTION: An engine assembly 10 includes a first engine 102. The first engine includes a first exhaust duct 114 coupled only to the first engine in fluid communication, and the first exhaust duct includes a primary outlet and a secondary outlet. The engine assembly 10 further includes a second engine 104. The second engine includes a second exhaust duct 116 coupled only to the second engine in fluid communication. The second exhaust duct includes a primary outlet and a secondary outlet, and a portion of the first engine secondary outlet is aligned concentrically within a portion of the second engine secondary outlet. COPYRIGHT: (C)2008,JPO&INPIT
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