曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

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
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
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 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 page.
POWER PLANT
Description
Vol. 2 19−10−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
ENGINE FUEL SYSTEM
Description
Fuel is delivered to the fuel injectors at pressures and flow rates required to maintain the desired
engine thrust. The engine fuel system, in addition to providing fuel for combustion, is used for:
• Controlling and actuating the VG compressor linkage;
• Cooling the engine oil (heat exchange);
• Actuating and lubricating servos within the fuel control unit (FCU); and
• Providing motive flow for the main ejector and scavenge ejector pumps.
Combustion fuel can be interrupted by moving the thrust lever to SHUT OFF, or by selecting the
engine FIRE PUSH switch/light. The SHUT OFF position shuts off the fuel at the FCU. The FIRE
PUSH switch/light closes the fuel shutoff valve.
Components and Operation
Engine-Driven Fuel Pump
The accessory gearbox-mounted fuel pump is comprised of three separate pumps contained
within a single housing. The engine-driven fuel pump provides high-pressure fuel at a flow rate
that exceeds the requirements of the engine at any power setting. Fuel pump pressure is used
to generate motive flow for the scavenge and main ejectors of the aircraft fuel system.
Fuel/Oil Heat Exchanger and Fuel Filter
A fuel/oil heat exchanger is used to warm engine fuel and cool engine oil. The fuel temperature
at the fuel filter is indicated on the SUMMARY page. A fuel filter is used to remove solid
contaminants from the fuel. If the filter becomes clogged, the fuel bypasses the filter to ensure
continued operation. A clogged filter is indicated by the L (R) FUEL FILTER caution EICAS
message.
Fuel Control Unit (FCU)
The fuel control unit is a hydromechanical metering device that supplies fuel in response to
mechanical inputs from the thrust levers. In addition, the FCU controls and actuates the VG inlet
guide vanes and stator vanes of the engine compressor.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者605機組操作手冊 CL605-POWER_PLANT(2)