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Engine Selection :

As per the power requirement for our aircraft we have selected FJ44-1A. It is a small, two spool turbofan

engine produced especially for Light Business Aircraft. Production started in 1992 with the 1900 lbf

(8.45 kN) thrust FJ44-1A, which comprises a 20.9 in (531 mm) diameter single stage blisk fan plus a

single intermediate pressure (IP) booster stage, driven by a 2 stage low pressure (LP) turbine,

supercharging a single stage centrifugal high pressure (HP) compressor, driven by a single stage uncooledhigh pressure (HP) turbine. The combustor is an impingement cooled annular design. Fuel is delivered to

the combustor through an unusual rotating fuel nozzle system, rather than the standard fuel-air mixers or

vapourisers. The bypass duct runs the full length the engine. Specific fuel consumption at 1900 lbf

(8.45 kN) thrust at SL.

FJ44-1A Specification

Thrust (N) 8452

Specific fuel consumption(lb/hr/lbf) 0.456

Dry Weight (Kg) 209

Overall Length (mm) 1354

Bypass Ratio 3.28