Rolls-Royce Avon

Turbojet · Rolls-Royce
Reaction Turbines
Diameter
906.78 mm
Length
3200.4 mm
Dry Weight
1310.882 kg
Thrust To Weight
5.66

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 cannular, 150 lb/s (68 kg/s)
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 1 Bypass Ratio — Overall Pressure Ratio — Afterburner No

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Airplanes

Name Aircraft Engine Number of Engines Length (m) Flat Wing Span (m) Max Seating
CAC CA-23 Rolls-Royce Avon 2 16.4592 13.4112
Fairey Delta 2 Rolls-Royce Avon 1 15.74 8.18
Ryan X-13 Vertijet Rolls-Royce Avon 1 7.14 6.4
Short Sperrin Rolls-Royce Avon 4 31.0896 33.2232
Sud Aviation Caravelle Rolls-Royce Avon 32.01 34.3 80
Supermarine Type 525 Rolls-Royce Avon 2 16.764 11.5824
Vickers Valiant Rolls-Royce Avon 4 32.9184 34.7472
All data (15 fields)
Name
Rolls-Royce Avon
Aircraft Engine Manufacturer
Rolls-Royce
Aircraft Engine Type
Turbojet
Dry Weight (kg)
1310.882
Diameter (mm)
906.78
Length (mm)
3200.4
Wikipedia Article (URL)
en.wikipedia.org/wiki/Rolls-Royce_Avon
Fuel
kerosene
Geared Fan
No
Combustion Chamber
cannular, 150 lb/s (68 kg/s)
Afterburner
No
Streams
1
Thrust To Weight
5.66
Compressor Description
15-stage axial flow
Turbine Description
two-stage axial flow