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Figure 19−10−15 Engine Start/Ignition Panel 19−10−23
Figure 19−10−16 ENGINE CONTROL Panel 19−10−24
Figure 19−10−17 Thrust Levers 19−10−25
Figure 19−10−18 GND SPOILERS/THRUST REVERSER Panel 19−10−26
Figure 19−10−19 Impending Bypass and Chip Detector Annunciators (JB−5) 19−10−27
Figure 19−10−20 N1 Indications 19−10−28
Figure 19−10−21 ITT Indications 19−10−29
Figure 19−10−22 N2 Indications 19−10−30
Figure 19−10−23 Engine Secondary Indications 19−10−31
POWER PLANT
Table of Contents
Vol. 2 19−00−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
Page
GENERAL
The Challenger 604 is equipped with two General Electric CF34-3B high-bypass ratio turbofan
engines.
The dual-assembly engine consists of a fan rotor (N1) and a compressor rotor (N2). The N1 rotor is
comprised of a single-stage fan connected through a shaft to a four-stage low-pressure turbine. The
N2 rotor is a 14-stage axial flow compressor connected through a shaft to a two-stage high-pressure
turbine. The accessory gearbox is mechanically driven by the N2 compressor.
Normal takeoff thrust rating is 8,729 pounds per engine. During engine-out operation, the automatic
performance reserve (APR) system increases thrust on the operable engine to 9,220 pounds.
FLAT-RATED THRUST
Outside air temperature and pressure altitude are determining factors in achieving takeoff and APR
power. Increases in ambient temperature or pressure altitude adversely affect the engine’s ability to
produce rated thrust. The CF34-3B is flat-rated to ISA + 15°C at sea level.
ENGINE CONSTRUCTION
Description
The CF34 power plant has two independently rotating major assemblies. The N1 section consists
of a fan rotor that is driven through a shaft by a four-stage low-pressure turbine. The N2 section is
comprised of a 14-stage axial flow compressor, a combustor, an accessory gearbox and a
two-stage high-pressure turbine. The compressor is driven by the high-pressure turbine.
Flow Distribution
Engine airflow passes through the single-stage fan and is divided into two airflow paths:
• Bypass Air − Air is accelerated by the single-stage N1 fan only and is ducted around the
engine nacelle. Bypass airflow produces approximately 80% of the thrust at takeoff.
Thrust reversers are used to divert the bypass air forward to assist in airplane braking on
the ground.
• Core Air − Air that is accelerated by the N1 fan enters the N2 core where it is
compressed, mixed with fuel, and ignited. The resulting combustion gases are
exhausted through the high-pressure two-stage N2 turbine, which drives the N2
assembly. The exhaust gases are then discharged through the low-pressure four-stage
N1 turbine to drive the N1 fan. Jet pipe thrust produces approximately 20% of the takeoff
thrust.
POWER PLANT
Description
Vol. 2 19−10−1
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ENGINE CONSTRUCTION (CONT'D)
Flow Distribution
Figure 19−10−1
Major Power Plant Components
N1 Fan
The N1 fan is a single-stage fan that consists of 28 titanium blades. A Kevlar blanket is
wrapped around the inlet housing to contain damage from a failed fan blade. The N1 fan rpm is
displayed on the EICAS primary page.
Variable Geometry (VG) Compressor
The VG system regulates airflow across the compressor by changing the position of the
compressor inlet guide vanes and the first five stages of the stator vanes. Fuel metered by the
Fuel Control Unit (FCU) is used to hydraulically change the vane angle. The VG system
optimizes the airflow’s angle of attack at the compressor blades and provides compressor stall
and surge protection.
Accessory Gearbox
The engine-mounted accessory gearbox is driven by the N2 compressor. The gearbox drives
the:
• Engine lubrication pumps;
• Alternator that powers the N1 Control Amplifier;
• Engine-driven hydraulic pump (Hydraulic Pump 1A or 2A);
• Engine-driven fuel pump; and
• Integral drive AC generator (IDG).
Mounted on the gearbox is the air turbine starter (ATS).
The N2 rpm is displayed on the EICAS primary page.
POWER PLANT
Description
Vol. 2 19−10−2
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ENGINE FUEL SYSTEM
Description
Fuel is delivered to the fuel injectors at pressures and flow rates required to maintain the desired
　
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