Beryllium Reinforced Titanium Matrix Composite Blade for Turbine Fans and Compressors.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1974
- Accession Number
- AD0777098
Entities
People
- G. R. Sippel
- Michael F. Herman
- R. W. Stusrud
Organizations
- General Motors