T-45C TS, ADV & IUT ENG-27/ENG-28
Engineering Review
d.
HP fuel pump: mounted on and driven by
external gearbox; supplies HP fuel to fuel
control unit (FCU) and sub-idle fuel control unit
(SIFCU)
e.
Engine control amplifier (ECA): trims fuel flow
in response to T6 temp (EGT) and N1 speed
3.
Engine lubrication system: self-contained, engine-
Sg 2, fr 29
driven, full-flow recirculating system
Lubrication System
4.
Engine starting system: engine is started (on
Sg 2, fr 40
ground or by assisted relight in flight) by gas turbine
Engine Starting System
starter (GTS) and air turbine starter
Fig 5: Engine Starting
System Block Diagram
a.
Starting system component function
(1) Gas turbine starter: annular reverse-flow
gas turbine air-producer unit which supplies
starting air to motor the Air Turbine Starter
(ATS)
(2) Air turbine starter: output shaft drives
(3) Start control unit: sequences start cycle by
monitoring speeds of GTS, air turbine
starter, and engine
b.
Engine starting component function
(1) Bleed air valve: relieves pressure from N2
compressor to ease engine starting and
prevent N1 compressor stalls
(2) Igniters: two high-energy, 12-joule igniter
plugs fitted to engine combustion chamber
are supplied by 28 VDC essential services
bus
5.
Bleed air system
a.
Internal airflow: continuous flow of compressor
air, used internally in engine for
(9-98) Original
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