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GE/Rolls-Royce JSF F136 Program Details

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


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