RU2592359C1 - Double seat float valve - Google Patents

Abstract

FIELD: manufacturing technology.

SUBSTANCE: invention relates to double seat float valve and is intended for automation of process of filling tanks with working fluids in oil or fuel tank design during preflight preparation of aircraft. Double seat float valve comprises body with mounting seats, where lever with float is mounted on axis of rotation, connected with stem to displace axially by two valves interacting with mounting seats. Float is fixed relative to lever on axis of rotation. In area of axis of rotation on adjacent to each other elements of float and lever is angular division unit in form of through holes of the same diameter arranged regularly on identical circles with different pitch on mating surfaces and mutual angular location of the float retainer relative to lever, installed inside holes coinciding during float rotation relative to lever.

EFFECT: simplified adjustment of tank filling level with working fluid and reduces cycle of aircraft preflight preparation.

1 cl, 1 dwg

Description

The invention relates to a two-seat float valve used in the construction of an oil or fuel tank to automate the process of filling tanks with working fluids during pre-flight preparation of the aircraft.

A two-seat float valve is known, comprising a housing with landing seats, in which a lever with a float is fixed on the axis of rotation, and is connected to two valves mounted on the stem with the possibility of axial movement and interacting with landing seats (see patent for invention RU No. 2170868, publ. 20.07 .2001).

In the known device for adjusting the amount (level) of the working fluid in the tank using adjustable stops, move two valves simultaneously relative to the center of gravity of the float up (to reduce refueling) or down (to replenish the tank) along the stem, while maintaining a distance between them equal to the distance between the seat saddles in the housing. Since the valves on the stem occupy a different position (different from the initial one), it is necessary to re-check the tightness of the float valve with the adjustment of the seat seats (for example, grinding) and only after that the adjustable stops are assembled, the valve is assembled and installed on the product, which increases the preflight preparation cycle apparatus.

The objective of the invention is to simplify the adjustment of the float valve. The technical result is a reduction in the complexity of work on adjusting the level of filling the tank with a working fluid and a reduction in the cycle of pre-flight preparation of the aircraft.

The specified technical result is achieved in that in a two-seat float valve containing a housing with landing seats, in which a lever with a float is fixed on the axis of rotation, connected with two valves mounted on the stem with the possibility of axial movement interacting with the landing seats, according to the invention, the float is fixed relative to the lever on the axis of rotation, and in the zone of the axis of rotation on adjacent to each other elements of the float and lever made an angular divider in the form located x uniformly on identical circles with different pitch of the through holes of the same diameter on the mating surfaces of the retainer and the mutual angular arrangement of the float relative to the lever installed inside coincident with rotation of the float relative to the lever openings.

The latch can be made in the form of a cotter pin.

Fastening the float to the lever on the axis of rotation will allow it to change the distance of the center of gravity of the float to the valve block when it is rotated in one direction or another without moving them on the stem. Therefore, there is no need to disassemble the device, then re-check the tightness of the float valve and fine-tune the seat seats in the body and valve edges to ensure tightness, which greatly simplifies the adjustment of the level of filling the tank with working fluid and reduces the cycle of pre-flight preparation of the aircraft.

The proposed two-seat float valve in longitudinal section is shown in the drawing.

The valve comprises a housing 1 with a lever 2 rotating on the axis 3. A float 5 is fixed on the lever 2 on the other axis 4, and also an arm 6 is fixed on the lever 2, which is connected to the valve block by means of an earring 7, consisting of a stem 8 mounted on it with the free travel of the valves 9, 10, the spring 11 and the control stops 12 and 13. In the body on the thread there is a stop 14, which limits the stroke of the valves 9, 10 for opening, and the seat seats 15 and 16 are made. In the area of the axis 4 on adjacent to each other friend elements 17 of the lever 2 and 18 of the float 5 formed by an angular divider in de spaced uniformly on the same circumferential «D» with different pitch of the holes 19 and 20 of equal diameter «d» and retainer 21 mounted inside the holes, which coincide with the rotation axis 4 around the float.

The valve operates as follows.

When lowering the liquid level in the vessel (for example, in the oil tank of an aircraft engine) below the specification for refueling, the float 5 with lever 2 under the action of gravity of the valves 9, 10 and rod 8 with stops 12, 13 drops down to touch the stop 14 while the valves are detached from the seat seats 15 and 16. The liquid to be filled into the oil tank through the windows in the housing 1 enters the gaps between the valves 9, 10 and the landing seats interacting with them 15, 16 and further into the oil tank. Upon reaching the specified level of refueling, the float 5, touching the surface of the liquid, floats up, turning the lever 2 around the axis 3, which is detached from the stop 14, while the valves 9 and 10 abut against the seat seats 15, 16, blocking the access of liquid into the oil tank.

To adjust the oil tank filling level, it is necessary to change the distance of the valve block to the center of gravity of the float 5, for which the latch 21 is removed from the axially displaced holes 19, 20 in the parts 17, 18, respectively, and the part 18, which is an element (part), is rotated around the axis 4. the float adjacent to the part 17, which is an element (part) of the lever 2, at the angle of closest coincidence of the axes of the holes 19, 20. Since the pitch of the holes 19 and 20 on the circle “D” in the parts 17, 18 is different (achieved, for example, by the fact that the number of holes in them is different per unit), the coincidence of the axes of the holes 19 and 20 occurs only in one place, where the latch 21 will be installed. By turning the float 5 around the axis 4 clockwise or counterclockwise, we can reduce or increase the distance of its center of gravity to the valve block, therefore , decrease or increase the level of oil tank filling.

In connection with the foregoing, according to the applicant, it is obvious on the basis of the prior art that when implementing the claimed two-seat float valve, the claimed technical result is achieved, consisting in reducing the complexity of work on adjusting the level of filling the tank with working fluid and shortening the cycle of pre-flight preparation of the aircraft.

Claims (2)

1. Two-seat float valve, comprising a housing with landing seats, in which a lever with a float is fixed on the axis of rotation, coupled to axially displaced two valves interacting with landing seats, characterized in that the float is fixed relative to the lever on the axis of rotation moreover, in the zone of the axis of rotation on adjacent to each other elements of the float and the lever is made an angular divider in the form of uniformly arranged on the same circles with different pitch through holes of the same diameter on the mating surfaces and the latch of the relative angular location of the float relative to the lever installed inside coincident during rotation of the float relative to the lever of the holes. 2. The two-seat float valve according to claim 1, characterized in that the latch is made in the form of a cotter pin.

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