TM 55-2835-208-23
1-11. TURBINE AND COMBUSTOR ASSEMBLIES
a.
During the start cycle, air is drawn by the compressor wheel (A) into the compressor section
of the turbine assembly .
The air is compressed and directed into the combustor assembly (B). Fuel
entering the combustor assembly from the start fuel nozzle (C) is mixed with compressed air and ignited by
the igniter plug (D).
b.
At a predetermined speed, six fuel nozzles (E) add fuel, resulting in additional hot gas mass
flow. The hot gasses flow through the turbine nozzle (F) and impact the turbine wheel blades (G). The
rotation of the turbine rotor shaft provides power to drive the compressor and input pinion (H) of the
turbine assembly.
c.
The compressor wheel (A), mounted on the same shaft as the turbine wheel (G), continues
to draw air into the compressor. Ignition and start fuel are cut off at a predetermined point. All fuel is then
supplied through the six fuel nozzles (E). Combustion is self-sustaining. A continuous cycle of intake,
compression, combustion, and exhaust is maintained within the engine.
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