G.E.® Stage 2 High Pressure Turbine Blade 1881M52G34
GE Engines TRIO II
Part # 1881M52G34=CK
8130-3 Eligible
8130-3 Eligible
The 1881M52G34 stage-2 turbine blade is engineered for GE engines, featuring a pressure gradient that maintains uniform axial air velocity. Made from high-strength super alloys, it withstands high operating temperatures while managing mechanical stress and transferring heat, essential for generating high-pressure, high-velocity air for thrust production.
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Overview
The 1881M52G34 stage-2 GE engine high pressure turbine rotor blade is designed to provide a pressure gradient along its length to ensure that the air is maintained at a suitably uniform axial velocity. The air stream's centrifugal force is countered by the rotor's centrifugal action due to the increased pressure at the tip. This high-resistance super polished high-pressure turbine rotor blade 1881M52G34 is fabricated from high strength super alloys that can withstand engine operating temperature. 1881M52G34 stage-2 turbine rotor blades work to create the high-pressure and high-velocity air that is necessary for the engine to produce thrust. In such circumstances 1881M52G34 turbine blade manages mechanical stress and also transfers heat to survive in these conditions.
Features & Benefits
Resistant to oxidation and corrosion at high temperatures
Reduces gas turbine engine downtime
Increased efficiency thus lowering the fuel consumption
Highly reliable on harsh environmental conditions
Technical Information
ATA Number
72
ATA Chapter
Engine Turbine / Turbo Prop Ducted Fan / Unducted Fan
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