Special Features:

58 blades; 8.547 min 8.549 max in. O/a od; 1st end stepped hub; 1.12 min 1.1207 max od 1st step 1st end; 0.2 min 0.21 max lg 1st step 1st end; ext splines 2nd step 1st end; 38 teeth; 30 degrees pressure angle; 1.2188 in. Nom pitch diameter 0.54 min 0.57 max in. Lg 2nd step 1st end; 1.11 min 1.13 max od 3rd step 1st end; 0.07 min 0.08 max in. Lg 3rd step 1st end; 1.3 min 1.3007 max in. Od 4th step 1st end; 0.155 min 0.16 max in. Lg 4th step 1st end; 1.82 min 1.83 max in. Od 5th step 1st end; 6th step 1st end tapered: 1.675 min 1. 685 max smallest od; 0.635 min 0.705 max in. Lg 6th step 1st end; 1.77 min 1.825 max lg from 1st end to disk; 2nd end plain hub; 1.408 min. 1.412 max in. Od hub 2nd end ; 0.495 min 0.515 max in. Lg from 2nd end to disk; 4 holes 0.208 min 0.212 max in. Dia; 0.125 min 0.145 max in. Lg 5th step 1st end

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.