Patent ID: 8371806
Filing Date: 2013-02-12
Classification: F01D,F02K

Abstract:
1. A gas turbine engine system, comprising: a nacelle assembly defined about an axis; a core engine positioned at least partially within said nacelle assembly and having a core passage and at least one core auxiliary duct passage, wherein said at least one core auxiliary duct passage includes an inlet for receiving a portion of a core airflow from said core engine and an outlet for discharging said portion of said core airflow, and at least one of said inlet and said outlet are selectively translatable to divert said portion of said core airflow into said at least one core auxiliary duct passage; a mixer disposed between said nacelle assembly and said core engine; wherein said inlet includes at least one door and a translating ring that selectively translates said at least one door; and wherein said door of said inlet is stored in a cavity when translated to an open position of said inlet.