Integrated nacelle inlet and metallic fan containment case
作者： James L. Lucus
DOI:
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摘要: A fan nacelle includes a metallic containment case. inlet is secured to the case by permanent fastening elements. gas turbine engine core has static structure housing compressor section, combustor section and section. The configured receive airflow. arranged within coupled in bypass flowpath provided between
google.de 参考文章(26)
Thomas J. Robertson, Darin S. Lussier, Metallic radius block for composite flange ,(2010)
Darin S. Lussier, Thomas G. Cloft, Ron I. Prihar, Integrated inlet fan case ,(2008)
Alan Binks, Norman John James, Michael John Layland, Inlet section of an aircraft engine nacelle ,(2011)
Louis G. Dhoore, William H. Schultz, Turbofan engine having variable geometry fan duct ,(1976)
Darin S. Lussier, Composite fan containment case ,(2009)
John Strunk, Integrated inlet attachment ,(2006)
Alison J. McMillan, Ducted fan with containment structure ,(2005)
Gerald Alexander Pauley, Reverser inner cowl with integral bifurcation walls and core cowl ,(1991)
Ian G Martindale, Julian M Reed, Sivasubramaniam K Sathianathan, David Geary, Paul Hodgson, Gas turbine engine blade containment assembly ,(2002)
Jeffrey W. Moe, John J. Wunsch, Michael S. Sperling, Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip ,(2004)