ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101, 109, 114, 115, 314-999; CF6-80A2 ENGINES (Continued)
Table 2/72-00-00-993-802-G00 CF6-80A2 ENGINE DATA (Continued)
Installed Cruise thrust (ECS on, at 35,000 ft.)
10,877 lbs.
Bypass ratio 4.6 to 1
Compressor pressure ratio 29 to 1
Specific fuel consumption (max. cruise, ECS on, at 35,000 ft.) 0.635 lbs/hr/l
Maximum N1 rpm 4,016 rpm (117%)
Maximum N2 rpm 10,859 rpm (110.5%)
Weight (bare engine) 8,496 lbs.
Nominal Engine Length 157 inches
Nominal Fan Diameter 86.4 inches
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101, 109, 114, 115, 314-999
2. Component Details
A. Compressor Section
(1) Ambient air is compressed in compressor section. Principal modules of compressor section
consist of a fan rotor, fan stator, and high pressure compressor.
(a) Fan rotor is an assembly consisting of a single stage fan and a 3-stage low pressure
compressor rotor.
(b) Fan stator is an assembly consisting of 4 stages of stator casings bolted together. When
fan stator assembly is coupled with fan rotor assembly, a low pressure compressor is
formed.
(c) High pressure compressor consists of a high pressure compressor rotor assembly and a
high pressure compressor stator/case assembly.
1) High pressure compressor rotor assembly is rotating component of a 14-stage axial
flow compressor.
2) High pressure compressor stator/case assembly consists of 5 stages of variable
vanes and 9 stages of fixed vanes.
3) Case provides structural support between the fan frame and the compressor rear
frame.
(2) For a more detailed description of the compressor section, (PAGEBLOCK 72-30-00/001).
B. Combustion Section
(1) Combustion section is located in compressor rear frame. Proper amounts of fuel are combined
with compressor discharge air and are ignited in combustion section.
(2) For a more detailed description of the combustion section, (PAGEBLOCK 72-40-00/001).
C. Turbine Section
(1) Energy from combustion is used to drive turbines. Modules consist of a low pressure turbine
and a high pressure turbine.
(a) Low pressure turbine consists of 4 stages of rotor blades and stator vanes. Turbine drives
low pressure compressor rotor.
(b) High pressure turbine consists of 2 stages of rotor blades and stator vanes. Turbine
drives high pressure compressor rotor.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-00-00
NoC
Page 2
D633T1B7 Dec 22/2016
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
EFFECTIVITY
ABX 001-007, 011, 012, 016-019, 021, 022, 025, 101,
109, 114, 115, 314-999
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