Accession Number : AD0777098
Title : Beryllium Reinforced Titanium Matrix Composite Blade for Turbine Fans and Compressors.
Descriptive Note : Final rept. 15 Jan 72-15 Dec 73,
Corporate Author : GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
Personal Author(s) : Sippel,G. R. ; Stusrud,R. W. ; Herman,M.
Report Date : FEB 1974
Pagination or Media Count : 129
Abstract : A total of thirteen Be/Ti composite TF41-A100 LP1 fan blade forgings were produced by isothermal forging two types of composite material. Both composite material preforms were initially produced by coextruding Be/Ti composite material surrounded by a sheath of titanium alloy. One type composite was a single extrusion of beryllium and Ti 6Al-6V-2Sn alloy powders, while the other was a multiple extrusion of beryllium rods in wrought Ti 6Al-4V alloy sheaths, with the final extrusion containing a Ti 6Al-4V wrought sheath around the composite bundle. Ti 6Al-4V root block split halves were contour machined to fit the elliptical composite extrusions and subsequently diffusion bonded by hot isostatic pressing. Tensile properties and metallographic structures were determined from one blade forging of each type composite material. Tensile strengths of the Be rod/Ti composite blade airfoil ranged from 90-91 ksi compared to 46-67 ksi for the Be/Ti powder composite blade. (Modified author abstract)
Descriptors : *Beryllium, Titanium alloys, *Composite materials, Compressor blades, Fabrication, Aluminum alloys, Vanadium alloys, Turbine blades, Tin alloys, Tensile properties, Microstructure, Reinforcing materials
Subject Categories : Laminates and Composite Materials
Properties of Metals and Alloys
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE