Part Details | AIRCRAFT TURBINE ENGINE TURBINE BLADE DAMPER
2840-01-440-1697 A device used to reduce high cycle fatigue on a BLADE, TURBINE ROTOR, AIRCRAFT GAS TURBINE ENGINE. It also acts as a seal. It may be of various shapes and cross sections.
Alternate Parts: 4082885, 4082885, 2840-01-440-1697, 01-440-1697, 2840014401697, 014401697
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 28 | JAN 06, 1997 | 01-440-1697 | 50557 ( DAMPER, TURBINE BLADE, AIRCRAFT TURBINE ENGINE ) |
REFERENCE DRAWINGS & PICTURES
Cross Reference | NSN 2840-01-440-1697
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| 4082885 | 52661 | UNITED TECHNOLOGIES CORPORATIONDBA PRATT & WHITNEY |
| 4082885 | 77445 | UNITED TECHNOLOGIES CORPORATIONDBA PRATT WHITNEY-SPARE PARTS |
Technical Data | NSN 2840-01-440-1697
| Characteristic | Specifications |
|---|---|
| DESIGN TYPE | AXIAL COMPRESSOR |
| ENGINE SECTION LOCATION | COMPRESSOR |
| OVERALL LENGTH | 0.565 INCHES MINIMUM AND 0.571 INCHES MAXIMUM |
| DIAMETER | 16.788 INCHES NOMINAL |
| SPECIAL FEATURES | T.O. 2J-F100-54, FIG 99, IND 21; REPL P/N 4074864 ONCE TCTO HAS BEEN ACCOMPLISHED; RETAINING PLATE DAMPER IS SYMMETRICAL IN SHAPE AND HAS 6 RETENTION TABS FORWARD AND AFT TO PRECLUDE POSSIBLE REVERSE INSTALLATION AND RESULTING CUT-OFF OF COOLING AIR TO THE 2ND STAGE BLADES |
| CRITICALITY CODE JUSTIFICATION | AFEAT$$ACZBJ |
| END ITEM IDENTIFICATION | F100-PW-229 AIRCRAFT GAS TURBINE ENGINE |