Part Details | AIRCRAFT GAS TURBINE ENGINE TURBINE ROTOR BLADE
2840-01-444-7012 An item mounted on a DISK, TURBINE, AIRCRAFT GAS TURBINE ENGINE. It is designed to create the flow of air in the turbine section of an ENGINE, GAS TURBINE, AIRCRAFT.
Alternate Parts: 1807M26G01, 1807M26, 2840-01-444-7012, 01-444-7012, 2840014447012, 014447012
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 28 | MAY 14, 1997 | 01-444-7012 | 50535 ( BLADE, TURBINE ROTOR, AIRCRAFT GAS TURBINE ENGINE ) |
REFERENCE DRAWINGS & PICTURES
Cross Reference | NSN 2840-01-444-7012
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| 1807M26G01 | 07482 | GENERAL ELECTRIC COMPANYDBA GE |
| 1807M26 | 07482 | GENERAL ELECTRIC COMPANYDBA GE |
Technical Data | NSN 2840-01-444-7012
| Characteristic | Specifications |
|---|---|
| DESIGN TYPE | AXIAL COMPRESSOR |
| ENGINE SECTION LOCATION | HIGH PRESSURE TURBINE |
| STAGE NUMBER | 2 |
| BLADE ATTACHMENT METHOD | FIR TREE |
| OVERALL LENGTH | 4.891 INCHES NOMINAL |
| OVERALL WIDTH | 1.347 INCHES MINIMUM AND 1.352 INCHES MAXIMUM |
| SPECIAL FEATURES | MATERIAL EXTERNAL PLATINUM ALUMINIDE COATING, THIS IS PART OF THE HT90 MOD FOR THE TF39, ORIGINAL DRAWING NAME BLADE,HIGH PRESSURE TURBINE ROTOR STAGE 2, TRAIL |
| CRITICALITY CODE JUSTIFICATION | AGAV |
| END ITEM IDENTIFICATION | ACFT ENG TF39 |