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Gas turbine engines, such as those that power modern commercial and military aircraft, generally include a compressor section to pressurize an airflow, a combustor section to burn a hydrocarbon fuel in the presence of the pressurized air, and a turbine section to extract energy from the resultant combustion gases.
The first stage turbine rotor blades and buckets typically require a platform, a shank, a dovetail, and other structural details. The platform forms the aerodynamic outer surface of the blade while the shank provides strength and mounting to the blade. The dovetail includes tabs that interlock with corresponding slots defined in the turbine disk to fix the blade in position. The structural details require significant amounts of material, thus increasing the weight of the blade. The increased weight negatively affects the performance of the blade.
To reduce the amount of material required to manufacture the blades, the platform, the shank, and the dovetail of the blades have been formed from a single ac619d1d87
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