Engine and Related Systems
T-45C TS, ADV & IUT ENG-04
II.
Engine operating characteristics 1.4.6.2.1
Sg 2, fr 2
Lesson Organization
ENGINE AND RELATED SYSTEMS
LESSON NOTES
* Major components of the T-45C engine
Use the graphic displayed in Sg 2, fr 3 (Fig 6: Engine Pressure
* Engineoperating
characteristics
and Temperature) throughout the discussion on engine
* Controls, switches, and indicators
operating characteristics.
* Engine servicing
* Engine/aircraft interfaces
A.
Engine
Sg 2, fr 3
1.
Air intake and compression
Engine Pressure and
Temperature
a.
Compressor (N1): two compressor stages with
a 2.5:1 pressure ratio
(acts as turbocharger)
(2) Output split between N2 compressor and
annular bypass duct, with 40% bypassed
to exhaust nozzle
b.
Compressor (N2): five compressor stages with
a 4.4:1 pressure ratio, which raises air pressure
and discharges it into combustion chamber
NOTE: Overall compression ratio is approxi-
mately 11:1.
c.
Bypass air (N1 compressor air)
an annular bypass duct and mixed with
turbine exhaust gases in exhaust mixer
(2) Small portion of bypass air is tapped from
bypass duct and used to cool exhaust cone
Original (9-98)
Page 4-6
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