A nacelle (100) for housing a fan within a gas turbine engine (10) having a longitudinal centre line (101) includes a leading edge (108) and a trailing edge (110). A nacelle length (Lnac) is defined as an axial distance between the leading edge (108) and the trailing edge (110). An azimuthal angle (θ) is defined about the longitudinal centre line (101). The nacelle length (Lnac) varies azimuthally. The nacelle length (Lnac) decreases azimuthally from an inboard end (116) of the nacelle (100) to an outboard end (118) of the nacelle (100).
NACELLE FOR GAS TURBINE ENGINE AND AIRCRAFT COMPRISING THE SAME
GONDEL FÜR GASTURBINENTRIEBWERK UND FLUGZEUG DAMIT
NACELLE POUR MOTEUR À TURBINE À GAZ ET AÉRONEF LA COMPRENANT
2024-03-06
Patent
Electronic Resource
English
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