A gas turbine engine includes an aerodynamic track fairing adjacent to a convergent-divergent nozzle, the aerodynamic track fairing including a localized curvature along an outside edge. The aerodynamic track fairing is configured to offset a circumferential pressure gradient otherwise introduced in part by a transition between the convergent-divergent nozzle with the aerodynamic track fairing.
AERODYNAMIC TRACK FAIRING FOR A GAS TURBINE ENGINE FAN NACELLE
AERODYNAMISCHE SCHIENENVERKLEIDUNG FÜR DIE LÜFTUNGSGONDEL EINES GASTURBINENMOTORS
CARÉNAGE DE GLISSIÈRE AÉRODYNAMIQUE POUR UNE NACELLE DE VENTILATEUR DE TURBINE À GAZ
04.03.2020
Patent
Elektronische Ressource
Englisch
Aerodynamic track fairing for a gas turbine engine fan nacelle
Europäisches Patentamt | 2019
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