The test was sponsored by Hybrid Material Deposition and Removal project
in Center for Aerospace Manufacturing Technologies program. The program
mission is to serve as a center of excellence for research, development,
evaluation and demonstration of new and optimal methodologies and tools
for rapid and affordable manufacture of aerospace products. The program
was contract funded by Air Force Research Laboratory with cost match
from Boeing. University of Missouri at Rolla provided technical support.


Titanium 5Al-5V-5Mo-3Cr wrought and casting exhibited higher mechanical
properties than 6Al-4V titanium alloy products and offers good potential
for aerospace applications. This presentation summarized the machining
and tests of Laser Additive Manufactured (LAM) Ti 5Al-5V-5Mo-3Cr
specimens excised from three (3) powder deposited test panels. One panel
was as-deposited, one panel was solution treated and aged for high
strength, and one panel was beta annealed slow cooled and aged for high
toughness.

A total of 88 specimens were tested in different test matrix. They
included 52 tensile at room and elevated temperatures, 4 fracture
toughness, 2 compact tension for fatigue crack growth, 12 strain-life
for fatigue crack initiation, and 18 open hole fatigue. All the fatigue
tests were performed at room temperature. The specimens were machined
from the 3 panels in accordance with Boeing drawings. In addition, 6
metallography specimens were di-sected from the panels for evaluation.
The specimens were NDT inspected and met Boeing requirements. The
mechanical tests were performed in accordance with applicable ASTM
specifications and the Boeing test matrix in laboratory environment. The
test results from the LAM Ti 5Al-5V-5Mo-3Cr panels are discussed in the
presentation and were also compared with those generated from LAM 6Al-4V
titanium powder. The predicted results show a good agreement with test
data.