Model: 1-100-078-07
Tur Centrifugal Compressor RotorSpecial Features:
Titanium alloy m3403, fscm 91547, shot peened ams2430, 36 blades, 13.048 in. Min, 13.051 in. Max od, 4.8694 in. Min, 4.8700 in. Max id bore, 12 holes 0.337 in. Min, 0.344 in. Max diameter on 5.440 in. Nom bolt circle dia, 3 thd holes on 5.440 in. Nom bolt circle dia, 0.250-28unf class 2b thd, thd holes countersunk 90 degrees by 0.280 in. Nom dia, 12 holes 0.154 in. Min, 0.159 in. Max diameter 0.150 in. Nom deep on 5.290 in. Nom bolt circle dia.
Properties:
Inc 60245 cancelled/replaced by ,inc 50588, fiig a10700, app-key j ,inc 50587, fiig a10700, app-key j ,on 021513 ~(all except usa). An item consisting of a series of blades on one or both sides of the rotor disk extending from the axis of rotation radially to the rim of the disk. It is designed to centrifugally cause the air between the blades to move outward to the rim of the compressor section of a turbine engine.
Part 1-100-078-07 NSN 2840-00-176-3745
Material Classification
Hazardous material, precious metals, criticality, enviroment, and electrostatic discharge indicatorsPackaging & Shipping
Freight Classification
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Schedule B and Export
- Schedule B: 8411997050
- SITC: 71499
- End Use: Engines and turbines for military aircraft
- NAICS: 336412
- USDA: 1
Freight Class: Parts of gas turbine aircraft engines, other than for use in civil aircraft
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