BMW 109-718

Rocket · BMW
Reaction Turbines
Maximum Takeoff Thrust
12.2625 kN
Specific Fuel Consumption
15.89 g/(kN·s)

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 Catalyst ignited or Hypergolic combustion in a single combustion chamber
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

Pictures

No pictures yet for this family.

Similar reaction turbines

Name Aircraft Engine Manufacturer Maximum Takeoff Thrust (kN) Bypass Ratio Overall Pressure Ratio
Armstrong Siddeley Viper Armstrong Siddeley 12 Compare
Heinkel HeS 011 Heinkel-Hirth 12.7 Compare
Lyulka TR-1 Lyulka-Saturn 12.8 Compare
JT15D-5, -5A, -5B Pratt & Whitney Canada 12.9 2.1 12.3 Compare
JT15D-4 series Pratt & Whitney Canada 11.12 2.68 10.1 Compare
Ishikawajima-Harima J3 IHI Corporation 13.7 Compare
All data (11 fields)
Name
BMW 109-718
Aircraft Engine Manufacturer
BMW
Aircraft Engine Type
Rocket
Wikipedia Article (URL)
en.wikipedia.org/wiki/BMW_109-718
Fuel
Diesel fuel and red fuming nitric acid (RFNA / S-Stoff) oxidiser with injected catalyst or R-stoff / SV-stoff fuel and …
Geared Fan
No
Combustion Chamber
Catalyst ignited or Hypergolic combustion in a single combustion chamber
Afterburner
No
Streams
1
Maximum Takeoff Thrust (kN)
12.2625
Specific Fuel Consumption (g/(kN·s))
15.89