Microwave processing of MIM preforms
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[0018] Referring to the drawings wherein identical reference numerals denote the same elements throughout the various views, FIG. 1 depicts an exemplary compressor blade 10 for a gas turbine engine. The present invention is equally applicable to the construction of other types of metallic components, non-limiting examples of which include rotating turbine blades, stationary turbine vanes, turbine shrouds, and the like. The compressor blade 10 comprises an airfoil 12 having a leading edge 14, a trailing edge 16, a tip 18, a root 19, and opposed sides 20 and 22. An arcuate inner platform 24 is attached to the root 19 of the airfoil 12. A dovetail 26 extends downward for mounting the blade 10 in a rotor slot. The compressor blade 10 is made from a metal alloy suitable for the intended operating conditions.
[0019]FIG. 2 depicts the process for constructing the compressor blade 10 according to the method of the present invention. Initially, as shown in block 28, a metallic powder and a s...
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