Williams F121

Maximum Takeoff Thrust
0.31 kN
Bypass Ratio
1.7
Diameter
215.9 mm
Length
1016 mm
Dry Weight
22.226 kg
Thrust To Weight
1.43

Architecture

Fan Fan Stages — Fan Blades — Fan Technology — Fan Pressure Ratio —
Gearbox Geared Fan No Gear — Reduction Ratio —
LP compressor Low-Pressure Compressor Stages — Low-Pressure Compressor Technology — BP Compressor Pressure Ratio —
IP compressor Intermediary-Pressure Compressor Stages — Intermediary-Pressure Compressor Technology — IP Compressor Pressure Ratio —
HP compressor High-Pressure Compressor Stages — High-Pressure Compressor Technology — HP Compressor Pressure Ratio —
Combustor Combustion Chamber Turbomeca Piméné-type
HP turbine High Pressure Compressor Stages — High-Pressure Turbine Technology —
IP turbine Intermediary-Pressure Turbine Stages — Intermediary-Pressure Turbine Technology —
LP turbine Low-Pressure Turbine Stages — Low-Pressure Turbine Technology —
Whole engine Streams 2 Bypass Ratio 1.7 Overall Pressure Ratio — Afterburner No

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All data (16 fields)
Name
Williams F121
Aircraft Engine Manufacturer
Williams International
Aircraft Engine Type
Turbofan
Dry Weight (kg)
22.226
Diameter (mm)
215.9
Length (mm)
1016
Wikipedia Article (URL)
en.wikipedia.org/wiki/Williams_F121
Geared Fan
No
Combustion Chamber
Turbomeca Piméné-type
Afterburner
No
Streams
2
Bypass Ratio
1.7
Maximum Takeoff Thrust (kN)
0.31
Thrust To Weight
1.43
Compressor Description
1 stage axial fan, 6-stage axial compressor
Turbine Description
2-stage axial