An exhaust duct for a turbine engine is provided including a duct having a generally hollow interior configured to receive a primary flow from a turbine section of the turbine engine and an ejector cooling air flow from an ejector of the turbine engine. The duct has a first end arranged in a first plane and a second end arranged in a second, distinct plane. The first plane and the second plane are arranged at an angle to one another between 70 degrees and 110 degrees.
HIGH TURNING ANGLE EJECTOR COOLED TURBINE ENGINE EXHAUST DUCT
2016-09-08
Patent
Electronic Resource
English
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES |