2. Component Details
A. Compressor Rear Frame Assembly (Figure 1)
(1) Compressor rear frame assembly is a structural weldment located between high pressure
compressor and high pressure turbine. Frame is a major structural support for engine. It is also
a flowpath between high pressure compressor and high pressure turbine.
(2) Compressor rear frame assembly consists of case structural weldment, combustion liner
assembly, No. 4 roller and ball bearings, No. 5 roller bearing, fuel nozzles, fuel manifold and
igniter plugs. Ten struts are provided which are used for air extraction purposes and support B
sump.
(3) Sump housing is fabricated from a casting that forms sump cavity and supports sealing
hardware, sheet metal support cone, and a machined circumferential flange. All pieces are butt
welded together. Sump tubing attachment points are made with standard mechanical joint
fittings which allow housing to be removed from frame without breaking permanent
connections. To provide for differential thermal growth between sump service tubing and
surrounding structure, tubes are attached only at the sump with slip joints and wear sleeves
where they pass through outer strut ends.
B. Combustion Liners (Figure 2)
(1) Combustion liner assembly is contained in extended aft portion of compressor rear frame. It is
an annular fabricated structure which uses film cooling to reduce thermal stresses. A support
ring is attached to outer liner and bolted to compressor rear frame outer flange with high
pressure turbine case. Inner liner is supported by high pressure turbine 1st stage nozzle.
Combustion liner assembly consists of a cowl assembly, dome, and inner and outer liners.
(a) Cowl assembly consists of two parts: inner and outer cowls, separated by dome. Its
purpose is to form a smooth leading edge which splits and meters incoming airflow to
combustor.
Cowl assembly is constructed of a toroidal casting with sheet metal rings welded at inner
and outer walls.
(b) Dome is a fabricated component consisting of 30 vortex-inducing, axial swirl cups with
venturis (one at each fuel nozzle tip). Its purpose is to provide flame stabilization and
mixing of fuel air mixture. Entire surface is swept by a film of cooling air. Parts are
provided at 3 and 4 o'clock for the igniter plugs.
(c) Inner and outer liners are composed of a series of circumstantially rolled ring strips joined
together by resistance welding and brazing. They are protected from connective and
radiant heat by continuous circumferential cooling. Primary combustion zone cooling air
entry is provided by closely spaced holes in each ring. These holes also increase
recirculation for flame stabilization and admit balance of primary combustion air.
767
AIRCRAFT MAINTENANCE MANUAL
CF6-80A SERIES ENGINES
72-40-00
NoC
Page 4
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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