Daher TBM 850, Руководство пилота

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SECTION 7
DESCRIPTION
TBM
850 PILOT’S OPERATING HANDBOOK
Page 7.6.1 Edition 1 -- June 22, 2007
Rev. 0
7.6 -- POWERPLANT
TURBOPROP ENGINE OPERATION (Figure 7.6.1)
The PRATT & WHITNEY CANADA turboprop engine (PT6A--66D model) is a
free turbine engine rated at 850 SHP and developing a thermodynamic
power of 1825 ESHP. An electrically driven device limits the power of the
engine to 770 SHP (110 % TRQ -- 2000 RPM) at sea level, when the flap
control lever is not on “850” position (UP/TO/LDG).
Intake air enters engine through an annular casing and is then ducted toward
compressor. The latter consists of four axial stages and one single centrifugal
stage assembly to form a whole assembly. Compressed air and fuel are
mixed and sprayed into combustion chamber by fuel nozzles. 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 first one (gas generator turbine) drives compressor
assembly and accessories, the two other ones (power turbines),
independant from the first one, drive propeller shaft through a reduction gear
box. Hot gases are evacuated through two exhaust stubs located laterally on
both sides forward of engine cowling.
All engine driven accessories, except power turbine tachometer and
propeller governor, are installed on accessory gearbox located rearward of
engine.
PIM - DO NOT USE FOR FLIGHT OPERATIONS