| 摘要 |
A system is provided in an aircraft that includes a power unit (102) and an eductor (104). The power unit (102) has a nozzle (108), and is configured to exhaust gas, a portion of which flows in a swirling motion, through the nozzle (108). The eductor (104) communicates with the power unit (102) and includes a housing (112) and a plurality of flow straighteners (114). The housing has an inlet (116), an outlet (118), and an inner surface (120) that defines a flow passage (124). The inlet (116) is configured to surround at least a portion of the nozzle (108) and to receive the gas, and the outlet (118) is configured to exhaust the gas. The plurality of low straighteners (114) extend radially inwardly from the housing inner surface (120) into the flow passage (124) and are configured to reduce swirl motion of the gas that flows therethrough. The power unit (102) may be an auxiliary power unit or a turboshaft engine.
|
