Pilot’s Operating Handbook
7-74
DO NOT USE FOR FLIGHT OPERATIONS
Section 7
AIRPLANE & SYSTEMS DESCRIPTIONS
100 SERIES
Systems
The compressor and power turbines are located in the approximate center of
the engine with their respective shafts extending in opposite directions. This
feature provides for simplied installation and inspection procedures. The
exhaust gas from the power turbine is directed through an annular exhaust
plenum to the atmosphere, via twin opposed exhaust ports provided in the
exhaust duct.
Interturbine temperature (ITT) is monitored by a cold junction thermocouple
system comprising a bus-bar, probes, and harness assembly, installed
between the compressor and power turbines, with the probes projecting into
the gas path. A terminal block mounted in the gas generator case provides a
connection point to cockpit instrumentation and to an ITT trim thermocouple
mounted externally in the air inlet zone.
The engine is rated at 750 shaft horsepower for takeoff and maximum
continuous emergency power (1790 foot pounds of torque at 2200 RPM,
varying linearly to 1970 foot pounds of torque at 2000 RPM; below 2000
RPM, the maximum takeoff/emergency power torque setting remains constant
at 1970 foot pounds).
The engine is rated at 700 shaft horsepower for maximum climb and
maximum cruise (1670 foot-pounds of torque at 2200 RPM, varying linearly
to 1840 foot pounds of torque at 2000 RPM; below 2000 RPM, the maximum
climb and cruise power torque setting remains constant at 1840 foot pounds).
The gas generator (compressor) turbine speed is 37,500 RPM at 100%
.
The maximum permissible gas generator speed is 38,100 RPM or 101.6%
.
The power turbine speed is 33,000 RPM at a propeller shaft speed of 2200
RPM (a reduction gear ratio of 0.0663:1)
All of the engine-driven accessories, with the exception of the propeller
tachometer-generator and the propeller governors, are mounted on the
accessory gearbox at the rear of the engine. The accessory gearbox is driven
by the compressor turbine with a coupling shaft, which extends from the
compressor section through a conical tube in the center of the oil tank.
The engine is self-sufcient since its gas generator driven oil system provides
lubrication for all areas of the engine, pressure for the torquemeter, and power
for propeller pitch control. The engine oil supply is contained in an integral
tank which forms part of the compressor inlet case. The integral tank has
a capacity of 9.2 US quarts (6.0 US quarts usable) and is equipped with a
dipstick/ller cap and drain plug.
NOTE: Refer to Section 1-4, Descriptive Data: Oil, for total installed
lubrication system oil capacity.
The power turbine drives the propeller shaft through a two-stage planetary
reduction gearbox on the front of the engine. The gearbox incorporates an
integral torquemeter device which provides an accurate indication of the
engine power output to the cockpit.
To Next Page
Loading...
Need help?
General