June 13, 2005 --
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
Rick Kennedy
GE Aviation
[email protected]
+1 513 243 3372
+1 513 607 0609