| 摘要 |
A gas turbine engine assembly (10) is provided for use with an aircraft. The gas turbine engine assembly comprises a propelling gas turbine engine and an auxiliary power unit (12). The propelling gas turbine engine includes a fan (14) and a core engine (11) for generating thrust for the aircraft. The gas turbine engine also includes a bypass duct (50) extending downstream from an exit of the fan to the core engine. The auxiliary power unit includes at least one turbine and an inlet that is coupled in flow communication with the gas turbine engine bypass duct, such that a portion of airflow (52) entering the gas turbine bypass duct is channeled for use by said auxiliary power unit. <IMAGE>
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