The annular combustion chamber liner (ring shaped) has perforations which allow entry of
compressed air. The flow of air changes direction to enter the combustion chamber liner, where it
reverses direction and mixes with fuel. The location and shape of the combustion chamber liner
eliminates the need for a long shaft between the compressor and turbine, reducing the overall length and
weight of the engine.
Fuel is injected into the combustion chamber liner by fourteen simplex nozzles. The fuel-air
mixture is ignited by two glow plugs which protrude into the combustion chamber liner. The expanding
gas from the combustion chamber liner reverses direction and passes through the compressor turbine
guide vanes to the compressor turbine. The gases then pass forward through the turbine guide vanes to
drive the power turbine.
The compressor and power turbines, items 3 and 4 in figure 9.2, are located approximately in
the center of the engine with their shafts extending in opposite directions. The exhaust gas from the
power turbine is directed through an exhaust plenum to two exhaust ducts.
governors, are mounted on the accessory gearbox and driven by the compressor. The oil tank is located
forward of the accessory gearbox and forms part of the compressor inlet case. The tank has a total oil
capacity of 2.3 gallons and has a dipstick and drain plug.
The power turbine drives a propeller through a two-stage planetary reduction gearbox located
at the front of the engine. The torquemeter is located in the reduction gearbox.
STATIONS, FLANGES, AND SPECIFICATIONS
The engine stations and flanges are illustrated in figure 9.3. Stations, identified by numbers
in the figure, are specific locations in the engine. Flanges, identified by letters in the figure, are rims or
edges providing strength in the attachment of one engine section to another.