Pre-System Development and 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 completed in 2003 
First full engine to test 2004 (same engine in endurance testing 2005) 
Second full engine to run STOVL (short take-off and vertical landing) demonstration 2005 

System Development and Demonstration (SDD) phase 
PHASE IV (2005-2012) 
Contract proposal planning in 2004 
Contract award anticipated in 2005 
12,000+ testing hours 
Flight test anticipated in 2009 
First production engine delivery in 2011 

F136 TECHNICAL CHARACTERISTICS 
FAN (Rolls-Royce) 
Long wide-chord, titanium, three-stage blisk 
Stage one: hollow core blade; stages 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 
Three rotors: stage one and stage two: three to five stages inertia-welded together 
Forward swept airfoils, robust blade tips 
Bowed/swept stators from 3-D aerodynamic codes 
High-stage loading to support 40,000-pound-thrust class 

COMBUSTOR (Rolls-Royce) 
Single annular, simplified design 
Fabricated from Lamilloy cooling material 
Technology grounded in IHPTET (Integrated High Performance Turbine Engine) experience 
Rig-testing ongoing 

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

AUGMENTOR (GE) 
Radial, non-stage, variable flow control 
Based on GE YF120, F414-GE-100, F110-GE-129 and F110-GE-132 engines