T-45C TS, ADV & IUT ENG-27/ENG-28
Engineering Review
(2) Compressed air from N1 then routed to N2
five stage compressor and to bypass duct
b.
Combustion
(1) Fuel is introduced through 18 fuel spray
nozzles and mixed with N2 compressed air
in annular combustion chamber
(2) Two high energy 12-joule igniter plugs
ignite fuel/N2 air mixture. Mixture expands,
forcing high pressure gases into turbine
section
c.
Power generation
(1) N2 and N1 turbines extract energy from
gases exiting combustion chamber to drive
their respective compressors through
coaxial shafts
(2) Internal gearbox extracts mechanical
energy from N2 shaft, providing power to
external gearbox
(3) External gearbox mechanically drives
aircraft accessories, e.g., generator,
hydraulic pumps, and fuel pumps
2.
Engine fuel system: engine-driven low- and high-
Sg 2, fr 18
pressure fuel pumps with manual and automatic
Engine Fuel
Control System
fuel metering controls
Fig 4: Engine Fuel
a.
Automatic (NORMAL) controls override
System Block Diagram
mechanical controls, preventing engine from
exceeding operating limits (fuel control selector
switch set to NORMAL)
b.
Fuel transferred to engine LP fuel pump from
aircraft fuel system
c.
LP fuel pump: mounted on and driven by
external gearbox; maintains fuel pressure to HP
fuel pump, preventing HP fuel pump cavitation
(9-98) Original
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