Part Details | AIRCRAFT GAS TURBINE ENGINE TURBINE NOZZLE
2840-01-394-5228 A single stationary item designed for the purpose of directing air at the proper angle and velocity to a ROTOR, TURBINE, AIRCRAFT GAS TURBINE ENGINE. It has provisions for attaching to a CASE (3), TURBINE, AIRCRAFT GAS TURBINE ENGINE. It may have an inner support shroud.
Alternate Parts: 804351CL20, 804351CL20, 804351CL20, 804351, 2840-01-394-5228, 01-394-5228, 2840013945228, 013945228
| Supply Group (FSG) | NSN Assigned | NIIN | Item Name Code (INC) |
|---|---|---|---|
| 28 | AUG 09, 1994 | 01-394-5228 | 50585 ( NOZZLE, TURBINE, AIRCRAFT GAS TURBINE ENGINE ) |
REFERENCE DRAWINGS & PICTURES
Cross Reference | NSN 2840-01-394-5228
| Part Number | Cage Code | Manufacturer |
|---|---|---|
| 804351CL20 | 99160 | THERM, INCORPORATED |
| 804351CL20 | 96965 | TURBINE AIRFOIL DESIGNS INC. |
| 804351CL20 | 77445 | UNITED TECHNOLOGIES CORPORATIONDBA PRATT WHITNEY-SPARE PARTS |
| 804351 | 77445 | UNITED TECHNOLOGIES CORPORATIONDBA PRATT WHITNEY-SPARE PARTS |
Technical Data | NSN 2840-01-394-5228
| Characteristic | Specifications |
|---|---|
| DESIGN TYPE | AXIAL COMPRESSOR |
| ENGINE SECTION LOCATION | HIGH PRESSURE TURBINE |
| STAGE NUMBER | 1 |
| BLADE ATTACHMENT METHOD | SLOT |
| OVERALL LENGTH | 2.035 INCHES MINIMUM AND 2.045 INCHES MAXIMUM |
| OVERALL WIDTH | 1.110 INCHES MINIMUM AND 1.130 INCHES MAXIMUM |
| OVERALL HEIGHT | 4.270 INCHES MINIMUM AND 4.300 INCHES MAXIMUM |
| SPECIAL FEATURES | FLOW AREA 1.446-1.455; PITCH 34 DEG. 20 MIN. 28 SEC.; 2ND END WIDTH 0.760-0.780 IN. |
| CRITICALITY CODE JUSTIFICATION | AAPGF$$ACZBJ$$ACZCJ$$ABGLW$$AFEAT |
| REFERENCE DATA AND LITERATURE | T.O. 2J-TF33-4 FIG31 IND50 |
| END ITEM IDENTIFICATION | TF-33 AIRCRAFT ENGINE |
| PART NAME ASSIGNED BY CONTROLLING AGENCY | VANE,HPT 1 STG |