Pre-System and Development Demonstration (SDD) phase 
PHASE I (1995-1997)
Engine definition completed

PHASE II (1997-2001)
Critical Design Review 
80 hours of core testing, successful fan testing 

PHASE III (2002-2005) 
Detail design completed in 2002 
Subsystem testing in 2002-2003 
Engine systems interchangeability 2002-2003 
Critical Design Review 2003 
First engines to test 2004 
STOVL demonstration 2005 
Successfully completed all testing requirements in April 2005 200 hours of combined testing 

System and Development Demonstration (SDD) phase 
PHASE IV (2005-2012) 
Contract proposals in 2003 
Contract award anticipated in 2005 
12,000+ testing hours 
Flight test anticipated in 2009 
First engine delivery in 2012 

F136 TECHNICAL CHARACTERISTICS 
FRONT FAN (Rolls-Royce) 
Long wide-chord titanium, three-stage blisk 
Stage one - hollow core blade; stage two & three-solid blade 
Two builds tested to date, verified fan flow and efficiency 
Linear friction welding for blade attachment 

HIGH-PRESSURE COMPRESSOR (GE) 
Five-stage, all-blisk system 
Two rotors: stage one; stages two to five 
Forward swept airfoils, robust blade tips 
Bowed/swept stators from 3-D aero codes 
High-stage loading to support 40,000-pound-thrust class 

COMBUSTOR (Rolls-Royce) 
Single annular, simplified design 
Fabricated from Lamilloy(TM) cooling material 
Technology grounded in IHPTET experience 
Successfully rig-tested 

TURBINE (GE & Rolls-Royce) 
Single-stage high-pressure turbine (HPT) 
Three-stage low-pressure turbine (LPT) 
HPT & stage 1 LPT in a coupled, vaneless counterrotating system 
HP turbine blades feature single crystal material 
Successfully rig-tested 

AUGMENTOR (GE) 
Radial, non-stage, variable flow control 
Based on GE F110-129 and F110-132 engines