Special Features:

38 blades; 6.189 min 6.192 max in. O/a od; 1st end stepped hub; ext thd 1st step 1st end, 3/4-20 unjef series cl 3a thd, lh; 0.375 in. Nom lg 1st step 1st end; 0.66 in. Nom od 2nd step 1st end; 0.125 in. Nom lg 2nd step 1st end; 0.7874 min 0.7876 max in. Od 3rd step 1st end; 0.6 in. Nom lg 3rd step 1st end; 2 circular grooves on od 3rd step 1st end; 0.1 in. Nom w by 0.75 in. Nom diameter grooves; 0.8195 min 0.82 max in. Od 4th step 1st end; 0.47 in. Nom lg 4th step 1st end; 1 circular groove located on od 4th step 1st end; 0.2 in. Nom w by 0.75 in. Nom diameter groove; 0.92 in. Max lg 5th step 1st end; 2nd end grooved hub; 1.809 min 1.811 max in. O/a od hub; 0.318 min 0.326 max in. Lg from 2nd end to disk; 2 circular u-grooves on od hub; 0.07 in. Nom w by 1.65 in. Nom diameter grooves; stepped id 0.52 min 0.522 max in. Id countersunk 60 degrees to 0.575

Properties:

A single or multistage assembly designed to receive thermal energy from the combustion section and convert it to mechanical energy to drive the rotor, compressor, aircraft gas turbine engine and/or the rotor, fan, aircraft gas turbine engine through a shaft, turbine, aircraft gas turbine engine. It consists of disks, blades, hubs, and the like. It is the moving part of a turbine assembly, aircraft gas turbine engine. It has facilities for attaching to a shaft, turbine, aircraft gas turbine engine.