Acoustic panel type noise insulating structure for use in inner wall of nacelle of turboshaft engine of aircraft, has notch formed on part of circumference of insert, and damping interface provided between body and insert
作者： Tran Julien , Thorel Christophe Jean-Francois
DOI:
关键词: Turboshaft 、 Insert (composites) 、 Interface (computing) 、 Circumference 、 Composite material 、 Honeycomb structure 、 Nacelle 、 Noise 、 Materials science
摘要: The structure (301) has a body (211) comprising honeycomb (208) filled with filler resin (209). extends around metal insert (207). comprises an opening (201) that is utilized for receiving fastening screw (202), and notch (210) formed on part of circumference the insert. A damping interface (302) provided between insert, where over entire
lens.org 参考文章(3)
Rainer Müller, Benjamin Grenzing, Christian Thomas, Insulation design for thermal and acoustic insulation of an aircraft ,(2009)
Carlos M. Figueroa, Matthew F. Kluesener, Anthony J. Durchholz, Method and system for damped acoustic panels ,(2009)
Teysseyre Pierre Michel, Pluquet Alain Alfred, Rosa Roger Andre, Tabet Mansour, Forestier Alexandre, GARNITURE INSONORISANTE POUR CONDUIT DE GAZ NOTAMMENT POUR VEINE DE SOUFFLANTE DE TURBOREACTEUR ET OUTILLAGE POUR SA FABRICATION ,(1982)