| 摘要 |
In a gas turbine engine 12 having a compressor 14, a combustor, an air inlet duct 20, and an engine exhaust nozzle 16, an improved engine intake protection system comprises: a first intake particle separator located in the inlet duct, a first duct 22 leading from the first intake particle separator to the compressor section, and a second duct 24 leading from the first intake particle separator and bypassing the engine, the first inlet particle separator comprising lips 30, 32, 34 so as to split an incoming air stream into first and second streams so that the first stream consists of relatively clean air for the compressor and the second stream consists of relatively dirty scavenge air to be mixed with the engine exhaust to reduce its infra-red signature. There is no line of sight from outside the aircraft to the compressor. A second vortex particle separator may be provided at 38. |
