Accession Number:

ADD009794

Title:

Composite Blade for Turbofan Engine Fan.

Descriptive Note:

Patent,

Corporate Author:

DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s):

Report Date:

1982-08-10

Pagination or Media Count:

4.0

Abstract:

A turbofan engine fan blade made of composite material and a method of making the fan, are taught. The fan blade essentially comprises an airfoil section having a root end and made of a plurality of bonded plies of composite material which are splayed and which are in a staggered condition at the root end a two-piece platform section made of titanium or of aluminum, with one piece of the platform on each side of the airfoil section and a steel outsert section which holds and secures the platform section to the airfoil section, with the outsert section having a triangular shaped cavity located at the root end of the airfoil section, between the splayed and staggered plies of the airfoil section. Among other advantages, the cavity eliminates the insert plies or wedge used in the prior art and the inherent disadvantages associated with such use. Author

Subject Categories:

  • Laminates and Composite Materials
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE