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SECTION 7 CESSNA
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AIRPLANE AND SYSTEMS DESCRIPTION MODEL 2088 (675 SHP)
ENGINE
(Continued)
The comoressor and
oower turbines are located in the aooroximate
center of'the eng ne
w
tn their shafts extending in opposae'directons.
Tne exnaust aas from the
oower turbine is d rected tnrouah an exhausr
plenum to
theatrnosphere'via a single exhaust port on th-e right side of
the engine.
The engine is flat rated at 675 shaft horsepower (1865 foot-pounds
torque at 1900 RPM varying linearly to 1970 foot-pounds torque at
1800 RPM; below 1800 RPM, the maximum torque value remains
constant at 1970 foot-pounds). Between 1800 and 1600 propeller RPM,
the gearbox torque limit of 1970 foot-pounds will not allow the full flat
rating of 675 SHP to be achieved. The speed of the gas generator
(compressor) turbine
(Ng) is 37,500 RPM at 100% Ng. Maximum
permissible speed of the gas generator is 38,100 RPM which equals
101.6%
Ng. The power turbine speed is 33,000 RPM at a propeller
shaft speed of 1900 RPM (a reduction ratio of
0.0576:l).
All engine-driven accessories, with the exception of the propeller
lachonieter-generator and tne propeller governors, are mounted on lne
accessory gearbox located at the rear of the engine. These are driven
by the compressor turbine with a coupling
shafl vihich extends the drive
through a conical tube in the oil tank center section.
The engine oil supply is contained in an integral tank which forms part
of the compressor inlet case. The tank has a capacity of 9.5 U.S. quarts
and is provided with a dipstick and drain plug.
(Continued Next Page)
Revision 23
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