Patent ID: 8117827
Filing Date: 2012-02-21
Classification: F02C,F05D

Abstract:
1. A gas turbine engine assembly comprising: at least one propelling gas turbine engine comprising a fan assembly and a core engine assembly downstream from said fan assembly, said core engine comprising a high pressure compressor, a high pressure turbine assembly, and a low pressure turbine assembly coupled together in serial-flow arrangement; and an auxiliary engine used for generating power, said auxiliary engine comprising at least one turbine and an inlet, said inlet coupled upstream from said turbine and in flow communication with said propelling gas turbine engine core engine, such that a portion of airflow entering said at least one propelling gas turbine engine is extracted for use by said auxiliary engine, wherein at least a portion of the airflow used by said auxiliary engine is selectively extracted from at least one interstage location between an inlet of said fan assembly and an exit of said fan assembly.