| 摘要 |
PROBLEM TO BE SOLVED: To provide a method and a device for operating a gas turbine engine used for aircraft propulsion and auxiliary power. SOLUTION: A gas turbine engine assembly 10 includes a propelling gas turbine engine 11 including a fan 14, a core engine 13 on the downstream side of the fan and a plurality of extracting positions 124, 122 and 120; an adjusting valve 100 connected to the propelling gas turbine engine in the state of fluid-communication; and an auxiliary engine 12 used for generating power. The auxiliary engine includes a turbine 44 and an inlet. The inlet is connected to the adjusting valve in the state of fluid-communication, and a part of an airflow 30 flowing through the propelling engine is extracted to be used in the auxiliary engine, and the adjusting valve controls the flow of the airflow 54 from the propelling engine to the auxiliary engine. The adjusting valve can be selectively operated so as to extract the airflow from two of a plurality of the extracting positions. COPYRIGHT: (C)2007,JPO&INPIT |
