General Electric F101

• Type: Turbofan
  
• Length: 181 in. (460 cm)
  
• Diameter: 55 in. (140 cm)
  
• Dry weight: 4,400 lbf (1995 kg)
  

• Compressor: Axial, 1 stage fan, 1 stage low pressure compressor, 9 stage high pressure compressor
  
• [Vous devez être inscrit et connecté pour voir ce lien]: Annular
  
• [Vous devez être inscrit et connecté pour voir ce lien]: 1 stage high pressure turbine, 2 stage low pressure turbine
  

• Maximum power output: 31,000 lb (138 kN) (with afterburner)
  
• [Vous devez être inscrit et connecté pour voir ce lien]: 26.8:1
  
• [Vous devez être inscrit et connecté pour voir ce lien]: 2.46 lb/lbf-hr (max thrust)
  
• [Vous devez être inscrit et connecté pour voir ce lien]: 7.04:1 (afterburner)
  

Fan

Two stages. The rotors have solid titanium blades with tip shrouds.

The 17-strut front frame incorporates variable-incidence trailing guide vanes.

The inlet guide vanes and fan vanes (stators) are installed in a horizontally split casing, enabling blades and vanes to be individually replaceable.

In May 1999 GE was awarded a USAF contract for US$9,954,800 for 164 fan-blade modification kits.

Pressure ratio about 2.1.

Mass flow 159.7 kg (352 lb)/s.

Compressor


Nine stages, with pressure ratio over 11.

First three vane stages and inlet guide vanes variable. Horizontally split casing, forward section of titanium and aft section of steel. Inertia welded discs make continuous steel spool. Blades and vanes individually replaceable.

Borescope inspection of vanes, blades and clearances.

Overall pressure ratio 26.8. Bypass ratio 2.01.


Combustion Chamber


Very short annular, with dual cone nozzles to inject fuel into dome area.

Dual high- and low-energy igniters.


HP Turbine


Single-stage, high energy extraction, high tip speed design.

Both blades and vanes (stators) are hollow airfoils which are convective and film-cooled.

The stationary shroud is segmented and cooled, to provide
tip-clearance control.

TET 1,427ºC class.


LP Turbine

Two stages, tip-shrouded and uncooled.
Blades individually replaceable, and second-stage vanes replaceable in segmented groups.


Fan Duct


Upper and lower halves of titanium alloy chem-milled to leave circumferential and closely spaced longitudinal ribs.


Jetpipe


Single pipe with convergent-divergent nozzle.

Area variations obtained by hydraulic actuators translating actuation ring which positions flaps and seals through cams and links.


Afterburner


Mixed flow type, with convoluted flow mixer to provide efficient mixing and burning of both fan and core streams.

Fan and core flows mix in plane of flameholder where automatic ignition begins on inner ring.

Radial flameholders in core stream, for lightoff and stable high-altitude operation. Smooth and continuous temperature rise over the entire modulation range.



Accessories


The two engines in each nacelle are linked via an APU to an accessory-drive gearbox mounting two 115 V IDG alternators, two 276 bar (4,000 lb/sq in) hydraulic pumps and a pneumatic (air-turbine) starter.


Control System


Hydro-mechanical with electronic supervision of MFC (main fuel control) and fan speed.

In 1998, Hamilton Standard (now Hamilton Sundstrand) was awarded a contract for an entirely new advanced Fadec control.

The order was for 450 replacement systems, to be delivered from the third quarter of 2002, but this quantity may now be reduced.