Page 144 - Aeronautical Engineer Data Book

Principles of propulsion 119
gases then pass out through the engine tailpipe,
providing thrust, or can be passed through a
further turbine stage to drive a propeller or
helicopter rotor. For aeronautical applications
the two most important criteria in engine
choice are thrust (or power) and specific fuel
consumption. Figure 8.3 shows an outline of

Turbojet
Optional afterburner (reheater) for military use

Power from gas
thrust only

Compressor Combustion
chamber

Turbofan (fan-jet)
Thrust reverser cowls

Gas thrust

Bypass air merges
with gas thrust
Fan
Turboprop
Extra tubine stage

Turbine-driven
Gas thrust
propeller

Propeller thrust

Turboshaft
Shaft power

Output
(e.g. to drive helicopter rotor)
Fig. 8.3 Gas turbine engine types