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
26.03.2019
Patent
Elektronische Ressource
Englisch
AERODYNAMIC TRACK FAIRING FOR A GAS TURBINE ENGINE FAN NACELLE
Europäisches Patentamt | 2020
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