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T56 Turboprop Engine Compressor

The engine has a 14-stage, axial-flow compressor which supplies air for combustion, internal engine cooling, and operation of the aircraft pneumatic systems.

T56 Turboprop

The compressor has alternate rows of rotor blades and stator vanes. The rotor (rotating) blades are attached to the compressor wheels. (See below)

3D Model of T56 Engine Compressor Rotor

The stator (stationary) vanes are attached to the compressor housing. Each rotor blade adds energy, in the form of acceleration, to the air and directs the accelerated air at the proper angle onto the following stator vane.

3D Model of T56 Engine Compressor Stator

The stator vanes take the rotor air and diffuse it while directing it at the most efficient angle onto the following rotor stage. The diffuser action converts the velocity energy of the rotor air into static pressure at the outlet of the stator. Each combination of rotor blade and stator vane make up a single stage of compression. As the air passes through each stage of compression, its pressure is increased as a function of both the conversion of velocity to pressure and the compressing of air into a progressively smaller area.

3D Model of T56 Engine Compressor Stator/Rotor Combination

The compressor has a pressure ratio of 9.5 to 1. If the absolute pressure (psia) at the inlet to the first stage of the compressor is 14.7, the pressure at the fourteenth stage will be about 140 psia. This means that the air pressure has increased 9.5 times.


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