A bifurcated inlet scoop frame for a gas turbine engine and method of using such frame for a gas turbine engine are disclosed. The bifurcated inlet scoop frame having a nose, a first side panel, and a second side panel. The first side panel and the nose defining a first inlet port. The second side panel and the nose defining a second inlet port. The method including the steps of providing a bifurcated inlet scoop frame, splitting the fan air flow, and receiving fan air through the bifurcated inlet scoop frame.
BIFURCATED INLET SCOOP FOR GAS TURBINE ENGINE
VERZWEIGTE EINLASSHUTZE FÜR GASTURBINENMOTOR
PRISE D'AIR À ENTRÉE BIFURQUÉE POUR MOTEUR À TURBINE À GAZ
2020-02-26
Patent
Electronic Resource
English
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