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IL-114 Engines
The aircraft is equipped with two TV7-117C turboprop engines with electronic system of automatic control
developed by Klimov's plant (St. Petersburg) with Aerosila plant's (Stupino) propellers CB-34. Structurally the engine is made in modular
system and consists of 9 modules. The replacement of modules does not require additional balancing and can be implemented in airport
conditions. Two-channel electronic system of regulation is used in the engine (hydro mechanical management ensures the end of flight in case
of refusal of plane's electronics). The independent onboard monitoring system provides the control of parameters and provides the crew with
information about malfunctions and gives recommendations for their elimination. The system also allows carrying out operative on the ground
after flight control of engines. The fuel usage efficiency of the engine is provided with high parameters of a thermodynamic cycle (degree of
compression - 16, temperature of gas in front of the turbine - 1500 K) and with high efficiency of components (compressor efficiency is
higher for 81 %, the efficiency of the turbine of the compressor is higher for 88 %, the efficiency of the free turbine is higher for 92 %,
completeness of combustion of the chamber of combustion is 0.99). The engine has the big capacity of gas dynamic stability. Design Features:
axle -centrifugal force compressor consisting of five axial and one centrifugal steps; the entrance directing device and directing devices of
first two steps are adjustable; reverse-flow chamber of combustion; 2step axial turbines of the compressor with four cooling rings; 2 step
axial free turbines; shaft of capacity selection; coaxial reducer of the screw, which is located in front of the compressor. The basic
parameters at H=0, V=0, ISA
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Degree of rising of air pressure in the compressor
take-off regime
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16
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Max.temperature of gases in front of turbine, K
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1 500
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IL-114-100 Engine
The aircraft is equipped with two PW-127H turboprop engines produced by "Pratt & Whitney Canada" with
propellers HS 568 F-7 of "Hamilton Sundstrand" (USA). Three-roll turboprop engine with independent turbine consists of two centrifugal
compressors, the counter flow ring chamber of combustion. Two axial one-stage turbines rotate rotors of compressors. The independent turbine
- axial two-level. Turbines of compressors and the independent turbine are connected among themselves with only gas dynamic connection. The
system of automatic control of the engine consists of electronic, hydro mechanical regulators and a regulator of spin-up restriction of the
air screw. A reducer is planetary, differential, closed type with a measuring instrument of twisting moment. The engine is equipped with
the system of electronic management with the program of automatic increase of capacity from normal take-off up to maximal take-off, and also
with the fuel pump, the systems of regulation of submission and heating of fuel, the system of ignition without power supply, the indicator
of a shaving in oil, the regulator of spin up restriction and a lay brake of the air screw. The air screw is six bladed with the hydraulic
mechanism of change of double action blades' step and balance weights. Together with the controlling systems of the air screw and the engine, it provides automatic
maintenance of constant frequency of rotation, its given change, drafts reversing and feathering of the air screw. Connection of the air
screw with a power shaft of the engine is flange-mounting. Blades of the air screw are sword type with a graphite longeron, covering supplied
with lightning protection aluminum grid, nickel overlay on the forward edge and electro heaters in the forward edge ensuring the protection
against an icing.
IL-114 Avionics
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