Actuator position control device using a fail freeze servo-valve
The actuator ( 50 ) comprises a slide ( 52 ) carrying at least two stages ( 54, 56 ) and being capable of sliding in a cylinder and two control chambers ( 62, 64 ) connected to respective use holes (U 1 , U 2 ) of an electrically controlled servo-valve hydraulic distributor ( 20 ). The control chambers ( 62, 64 ) are each situated on one side of a respective stage and an intermediate chamber connected to high or low pressure is situated between the other sides of the stages. In the event of electrical control failure, the distributor ( 20 ) slide is taken to a safety position in which the control chambers ( 62, 64 ) of the actuator ( 50 ) are at the same low or high pressure opposed to that applying in the intermediate chamber ( 66 ) so that each stage of the actuator slide is then subjected to high pressure on one side and to low pressure on the other side. Sealing between each actuator slide stage ( 54, 56 ) and the actuator cylinder ( 60 ) is carried out by a dynamic seal ( 70 ) producing a frictional force between stage and cylinder, depending on the difference between the pressures exerted on the two sides of the stage so that, in the event of electrical control failure, the actuator slide valve is immobilized in its position at the moment of the failure (“fail freeze”). The actuator ( 50 ) can be an aeronautical engine fuel metering unit.
1. An actuator position control device comprising:
an electrically controlled servo-valve including a hydraulic distributor having at least one high pressure (HP) supply hole, at least one low pressure (LP) outlet and at least two use holes, each use hole being connectable to high pressure or low pressure, depending on the controlled position of a slide of the hydraulic distributor; and
an actuator including a slide carrying at least two stages and being slidable in a cylinder, the actuator having two control chambers connected to respective use holes of the servo-valve distributor and each situated on one side of a respective stage and an intermediate chamber connected to high or low pressure and situated between another side of each of the said stages,
the hydraulic distributor slide being taken, in the event of electrical control failure, to a safety position in which it causes the immobilization of the actuator slide substantially in its position at the moment of the failure, wherein
in the safety position of the hydraulic distributor slide, the actuator control chambers are taken, via their connection with the distributor use holes, to a same low or high pressure opposed to a pressure applied in the intermediate chamber so that each actuator slide stage is then subjected to high pressure on one of the sides and to low pressure on the other side, and
sealing between each of the said stages of the actuator slide and the actuator cylinder is carried out by a dynamic seal which is elastically deformable under an effect of a pressure difference between the sides of each of the said stages to produce a frictional force between each of the said stages and the cylinder, which increases as a function of the difference between the pressures exerted on the two sides of the stage.
2. The actuator position control device according to claim 1 , wherein the actuator intermediate chamber is connected to high pressure and, in its safety position, the distributor slide connects the distributor use holes to low pressure.
3. The actuator position control device according to claim 1 , wherein the dynamic seal further comprises:
a first O-ring and a second ring both housed in a groove, the second ring being supported by the first O-ring and contacting the slide stage, the first O-ring being made of an elastically deformable material allowing it to be deformed under the effect of the pressure difference between the sides of each slide stage and to exert a pressure on the second ring producing said frictional force between each stage and the cylinder.
4. An aeronautical engine comprising an actuator position control device according to any of claims 1 , 2 , or 3 .
5. A fuel flow control device in an aeronautical engine, comprising an actuator position control device according to claim 1 , 2 , or 3 , in which the actuator forms a fuel metering unit, the intermediate chamber being connected to a high pressure fuel source and having an outlet hole, of which the cross section of flow is a function of the actuator slide valve position.