DEVICE FOR CONTROL OF POSITION OF ACTUATOR, DEVICE FOR CONTROL OF FUEL FLOW IN AIRCRAFT ENGINE WITH MENTIONED DEVICE FOR CONTROL OF POSITION AND AIRCRAFT ENGINE Russian patent published in 2012 - IPC F15B13/43 F15B11/48 F15B20/00 F02C9/46 F02C9/26 

FIELD: engines and pumps.

SUBSTANCE: device is meant for control of position of actuator in aircraft engine using electrically controlled servo-valve. Actuator (50) includes a slide (52) with at least two steps (54, 56) meant for sliding in cylinder, and two chambers (62, 64) of control connected with corresponding workholes (85, 86) of electrically controlled hydraulic distributor (20) of servo-valve. Chambers (62, 64) of control are located each on one side of corresponding step, and intermediate chamber connected to high or low pressure is located between other sides of steps. In case of failure of electrical control a slider of distributor (20) is set to protection position in which in chambers (62, 64) of control of actuator the same low or high pressure is settled opposite to pressure generated in intermediate chamber (66), so that each step (54, 56) of actuator slider is influenced by high pressure on one side and low pressure on the other side. Tightness between each step (54, 56) of actuator slider and actuator cylinder (60) is provided by dynamic sealing (70) producing friction force between step and cylinder depending on pressure difference influencing two sides of step, so that in case of failure of electrical control actuator slide valve stops in its position at the moment of failure ("failure freezing"). Actuator (50) may be a unit for aircraft engine fuel measurement.

EFFECT: higher reliability.

4 cl, 10 dwg