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):

Report Date:

1974-02-01

Pagination or Media Count:

129.0

Abstract:

A total of thirteen BeTi 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 BeTi 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 rodTi composite blade airfoil ranged from 90-91 ksi compared to 46-67 ksi for the BeTi powder composite blade. Modified author abstract

Subject Categories:

  • Laminates and Composite Materials
  • Properties of Metals and Alloys
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE