Jet turbine engine compressor controller
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Jet turbine engine compressor controller

Jet turbine engine compressor controller

 

 

Jet regulators have been successfully used to control the position of the blades HA and bleed valves of the compressor GTE. Schemes such regulators (development of "OEDB"). The parameter is the degree of control to increase air pressure in the compressor n = pk / PBX.

As the pressure ratio sensor in the controller using a flat jet 1 sensor with an oblique cut. When driving shaft via servomotor 2 mechanical feedback 3 about proceeds resetting output choke 4 5 pneumatic reducer as long as the supply pressure air jet planar divider reaches a value at which the pressure drop across the output channels of the jet element becomes zero. The motion of the rod stops.

As a result, each value 7G will match a certain position servo rod blades and BHA.

The jet regulator valve positions 5 bleed air from the compressor applied jet pressure ratio sensor, which consists of pneumatic and gear divider 1 2, as well as an element of comparison with the jet booster 3 4. Accuracy of the regulator is not more than ± 3%.

For years, jet regulators are in operation at GTE series, confirming the high reliability and service life: their MTBF exceeds 1 ppm.

Fuel systems (STP) FCD should ensure the supply of fuel into the combustion chamber with the desired characteristics of flow, pressure, temperature and purity required for operation of the engine and its systems in all operating conditions.

To solve this problem STP shall perform the following functions:

- creation of the required fuel consumption and pressure at the inlet of the pumps and in front of the nozzles to power the combustion chambers of the GTE;

- filtration of fuel coming from aircraft tanks;

- fuel supply of ACS units and its executive bodies;

- fuel distribution over the collectors of the combustion chambers;

- cessation of fuel supply to the engine by a signal from the control system or by the pilot's command (turning on the stop valve);

- fuel cooling of oil in the lubrication system of the engine rotor bearings and in the units installed on it (central gearbox, PPO, etc.);

- ensuring the required thermal state of the fuel system;

- draining fuel from the manifolds into the drainage system when the engine is stopped;

- emergency discharge of fuel from aircraft tanks;

- fuel cooling of ACS units (if necessary) and a number of others.

 

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