7.6 -
Powerplant
T
urboprop Engine Operation
See Figure 7.6.1.
The Pratt & Whitney
Canada PT6E-66XT turboprop engine model is a free turbine
engine flat-rated at 895 SHP, electronically controlled by a Full Authority Digital
Engine Control (FADEC).
Intake air enters the engine through an annular casing and is ducted towards the
compressor.
The compressor is composed of four axial stages and one centrifugal stage
forming a whole assembly that compresses the air.
Fuel is sprayed by fuel nozzles into the combustion chamber and mixed with the
compressed air. The mixture is first ignited by two spark igniter plugs; then
combustion continues as a result of air-fuel mixture flow.
Gases resulting from combustion expand through a series of turbines:
- the gas generator turbine which drives the compressor assembly and
accessories. The accessory gearbox is located rearward of the engine,
- the power turbines (two stages), independent from the gas generator turbine
and rotating reverse way, which drive the propeller shaft through a reduction
gearbox.
Hot gases are evacuated through two exhaust stubs located laterally on both sides
forward of engine cowling.
Section 7
Description
Pilot's Information Manual
PIM TBM 960 - Edition 0
Rev. 02
Page 7.6.1
PIM - DO NOT USE FOR FLIGHT OPERATIONS
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