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7-26 Oil Pressure and Temperature Window (Reversionary)......................................... 7-18
7-27 CAS Window ......................................................................................................... 7-19
7-28 Engine Battery Start Schematic ............................................................................. 7-21
TABLE
Table Title Page
7-1 Target N1 Bug......................................................................................................... 7-17
INTRODUCTION
This chapter describes the Citation Mustang powerplants, including the engines and their
subsystems. The Mustang is powered by two turbofan engines. Each powerplant includes
ignition, oil, and fuel systems. This chapter also describes powerplant controls and indicating
systems.
CITATION MUSTANG OPERATING MANUAL
CHAPTER 7
POWERPLANT
510OM-00 7-1
GENERAL
The Mustang is powered by two Pratt &
Whitney PW615F turbofan engines (Figure
7-1). Each Mustang powerplant installation includes
a fuel metering unit (FMU), an
accessory gear box (to drive accessories with
engine power), and ports to provide bleed air
for the environmental control system (ECS)
and ice-protection systems.
A remotely located dual-channel full-authority
digital engine control (FADEC) monitors
and controls each engine. The two FADECS
are in the tail cone on the aft pressure bulkhead.
FADECs adjust engine settings in
response to pilot throttle settings, ambient air
conditions, and engine conditions to provide
optimum engine performance. A dual-coil,
permanent-magnet alternator (integral to the
FMU) powers each engine FADEC when normal
DC power is not available.
Each powerplant includes ignition, fuel, and oil
systems. Engine indications are integrated into
the G1000 electronic cockpit displays. This
chapter includes information on normal engine
operations (including starting, ground operation,
and flight), powerplant limitations, and
emergency/abnormal procedures. Fire detection
and extinguishing systems for the powerplant
are described in Chapter 8—“Fire Protection.”
DESCRIPTION
Two Pratt & Whitney PW615F turbofan engines
are in nacelles mounted on pylons on
each side of the tail cone. Each engine is flatrated
at 1,460 pounds of maximum continuous
thrust (sea level static, standard day). Engine
station numbers are assigned at particular points
to locate various components and functions,
usually relating to air temperature and pressure
(Figure 7-2).
The PW615F is a twin-spool, counter-rotating
turbofan engine (the N1 spool and N2 spool rotate
in opposite directions). It has a single-stage,
low-pressure axial turbine that directly drives
a single-stage, high-efficiency fan. A singlestage,
high-pressure axial turbine drives a
single-stage, mixed-flow compressor and a single-
stage centrifugal compressor (Figure 7-3).
CITATION MUSTANG OPERATING MANUAL
7-2 510OM-00
Figure 7-1. Mustang Engine Mounting
1
STATIC
2
DYNAMIC
3
COMPRESSED
4
TURBINE INLET
5
TURBINE OUTLET
6
EXHAUST
INDUCTION AIR
LEGEND
CENTRIFUGAL COMPRESSION AIR
TURBINE AIR
EXHAUST AIR
AXIAL COMPRESSOR
COMBUSTION CHAMBER
Figure 7-2. Engine Stations
TURBOFAN ENGINE BASICS
Turbofan engines provide thrust from two
sources: the fan and the high-speed engine
exhaust. The fan provides thrust like a propeller,
pulling air into the fan and pushing it
aft. The mass of exhaust exiting aft from the
engine at high speed and pressure creates an
equal reaction, pushing the engine (and the airplane)
in the opposite direction (forward).
The core of the engine operates a continuous sequence
of air intake, air compression, fuel/air
mixture combustion, and exhaust. The exhaust
turns turbines that provide torque to the fan and
continuous air compression for the engine core.
The compressed air is mixed with fuel and ignited,
resulting in rapid expansion. The exhaust
then exits the engine at high speed to provide
the additional thrust (Figure 7-4).
Intake and Compression
The spinning fan pulls ambient air into the
engine inlet and sends some of it through the
fan bypass duct for direct thrust. The fan also
pushes air into the compressor section, where
the axial-flow and centrifugal-flow compressors
compress the incoming air to a very high
pressure and temperature.
Combustion
The compressed air enters the combustion chamber
where it is mixed with fuel and ignited. At
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Cessna塞斯纳公务机飞行手册(34)
