An inner cowl structure (48) for circumscribing at least a portion of a jet engine (10) extending from an aircraft includes an apron (58) configured to mount directly to the engine independent of the pylon (38) and overly an upper portion of the jet engine, and an inner body (60,62) configured to circumscribe a portion of the jet engine not circumscribed by the apron.
Inner cowl structure for aircraft turbine engine
Innenverkleidungsstruktur für ein Flugzeugturbinentriebwerk
Structure de capot interne pour turbomoteur d'aéronef
2018-12-26
Patent
Electronic Resource
English