GE/Rolls-Royce JSF F136 Program Details
July 22, 2002
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
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