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 in 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
Contract proposal plannning 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
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
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 aero 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 counterrotating 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, F110-129 and F110-132 engines