July 22, 2002 (by Anonymous) -
Pre-system development demonstration (SDD).
PHASE I (1995-1997)- Completed in 1997
- Engine definition completed.
PHASE II (1997-2001)- Completed in 2001.
- Critical Design Review
- 80 hours of core testing, successful fan testing
PHASE III (2002-2005)- Detail design work completed in 2002
- Subsystem testing in 2002-2003
- Engine systems interchangeability
- First engine to test in 2004
ANTICIPATED FUTURE JSF FUNDING: PHASE IV System Development Demonstration (SDD)- Contract proposals in 2003
- Contract award anticipated in 2005
- 12,000+ testing hours
- Flight test anticipated in 2008
- Engine qualification/first 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
- 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 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
