阅读说明：本技术 一种用于直升机燃油系统的通气阀 (Breather valve for helicopter fuel system ) 是由 杨勇志 孟庆会 周佐俊 王成 邹高鹏 贾彭辉 屈子悦 段伟杰 于 2020-11-03 设计创作，主要内容包括：本发明属于直升机燃油系统设计领域,公开了一种用于直升机燃油系统的通气阀,所述通气阀包括：壳体、钢球、第二密封圈、浮子组件、阀座；壳体底部和阀座连接,且在壳体和阀座结合部位设有第二密封圈,浮子组件设置在壳体内部,并安装在阀座导轨内；钢球位于浮子组件和阀座之间。在直升机飞行姿态较大时,通过限位补偿构件,避免燃油从通气阀流出。(The invention belongs to the field of design of a helicopter fuel system, and discloses a vent valve for the helicopter fuel system, which comprises: the shell, the steel ball, the second sealing ring, the floater component and the valve seat; the bottom of the shell is connected with the valve seat, a second sealing ring is arranged at the joint of the shell and the valve seat, and the floater component is arranged in the shell and is arranged in the valve seat guide rail; the steel ball is located between the float assembly and the valve seat. When the flight attitude of the helicopter is large, the fuel oil is prevented from flowing out of the vent valve through the limiting compensation component.)

1. A vent valve for a helicopter fuel system, said vent valve comprising: the device comprises a shell (1), a steel ball (5), a second sealing ring (6), a floater component and a valve seat (7);

the bottom of the shell (1) is connected with the valve seat (7), a second sealing ring (6) is arranged at the joint of the shell (1) and the valve seat (7), and the floater component is arranged inside the shell (1) and is arranged in a guide rail of the valve seat (7);

the steel ball (5) is positioned between the float assembly and the valve seat (7).

2. A vent valve for a helicopter fuel system according to claim 1,

the float assembly includes: the device comprises a floater (3), a gland (4), a third sealing ring (8), a support (9) and a limit compensation component (10);

the floater (3) is arranged in the shell (1) and is arranged in the guide rail of the valve seat (7);

the bottom of the floater (3) is connected with a gland (4), and the steel ball (5) is positioned between the gland (4) and the valve seat (7);

a limiting compensation member (10) is fixedly connected below the support (9), the support (9) is movably connected with the floater (3), a cavity is formed below the support (9) and above the floater (3), and the limiting compensation member (10) is positioned in the cavity;

the third sealing ring (8) is arranged above the support (9) and used for sealing the support (9) and the inner surface of the shell (1).

3. A vent valve for a helicopter fuel system according to claim 2,

the position-limiting compensation member (10) can freely rotate and tilt in a cavity formed below the support (9) and above the floater (3).

4. A vent valve for a helicopter fuel system as claimed in claim 1, said vent valve further comprising: first sealing washer (2), casing (1) are connected with helicopter oil tank upper portion flap through first sealing washer (2).

5. A vent valve for a helicopter fuel system as claimed in claim 3 wherein when the vent valve is in an upright position, the float moves vertically upwardly under the influence of buoyancy and the third sealing ring seals against the inner surface of the housing.

6. A vent valve for a helicopter fuel system according to claim 3 wherein a preset angle of inclination of the vent valve is set;

when the actual inclination angle of the vent valve is smaller than the preset inclination angle, the floater moves upwards, the floater assembly generates restoring moment under the double action of buoyancy and gravity, the floater assembly deflects under the action of the restoring moment, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation component rotates and inclines freely in a cavity formed below the support and above the floater, so that the upper end of the floater assembly and the sealing surface of the shell are automatically aligned and compensated to form uniform contact and sealing.

7. A vent valve for a helicopter fuel system according to claim 6,

when the actual inclination angle of the vent valve is larger than the preset inclination angle, the buoyancy is not enough to push the floater to move upwards, the steel ball pushes the floater to move along the guide rail on the valve seat under the action of gravity, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation member freely rotates and inclines in a cavity formed below the support and above the floater, so that the upper end of the floater assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing.

8. A vent valve for a helicopter fuel system according to claim 6,

the preset inclination angle is between 5 degrees and 45 degrees.

Technical Field

The invention belongs to the field of design of a helicopter fuel system, and particularly relates to a vent valve for the helicopter fuel system.

Background

In order to meet the normal oil supply capacity of an engine and the pressure bearing capacity of an oil tank and an oil tank cabin, when the oil tank is used for gravity refueling, pressure refueling, oil drainage, fuel oil transfer and normal flight, a ventilation interface is usually required to be arranged to be communicated with the atmosphere to ensure the balance of the internal and external pressure difference of the oil tank. In order to improve the survival capability of the helicopter, fuel oil needs to be prevented from leaking from the air vent during crash, and ignition is avoided.

The float valve of ventilating of prior art installs outside the oil tank at present, and one end is connected with the oil tank air vent, and the other end and ventilation system tube coupling can guarantee to seal when the liquid level rises, nevertheless can not totally seal when helicopter flight gesture is great.

Disclosure of Invention

The technical problems to be solved by the invention are as follows: the problem that the existing vent valve cannot guarantee complete sealing of the helicopter when the flight attitude is large is solved.

In order to achieve the purpose, the invention is realized by adopting the following technical scheme.

A vent valve for a helicopter fuel system, said vent valve comprising: the device comprises a shell 1, a steel ball 5, a second sealing ring 6, a floater component and a valve seat 7;

the bottom of the shell 1 is connected with a valve seat 7, a second sealing ring 6 is arranged at the joint of the shell 1 and the valve seat 7, and the floater component is arranged in the shell 1 and is arranged in a guide rail of the valve seat 7;

the steel ball 5 is located between the float assembly and the valve seat 7.

The technical scheme of the invention has the characteristics and further improvements that:

(1) the float assembly includes: the device comprises a floater 3, a gland 4, a third sealing ring 8, a support 9 and a limit compensation component 10;

the floater 3 is arranged inside the shell 1 and is arranged in the guide rail of the valve seat 7;

the bottom of the floater 3 is connected with a gland 4, and a steel ball 5 is positioned between the gland 4 and a valve seat 7;

a limiting compensation member 10 is fixedly connected below the support 9, the support 9 is movably connected with the floater 3, a cavity is formed below the support 9 and above the floater 3, and the limiting compensation member 10 is positioned in the cavity;

a third sealing ring 8 is arranged above the abutment 9 for sealing the abutment 9 against the inner surface of the housing 1.

(2) The position-limiting compensating member 10 is free to rotate and tilt in the cavity formed below the seat 9 and above the float 3.

(3) The vent valve further comprises: first sealing washer 2, casing 1 are connected with helicopter oil tank upper portion flap through first sealing washer 2.

(4) When the vent valve is in a vertical state, the floater vertically moves upwards under the action of buoyancy, and the third sealing ring is tightly pressed and sealed with the inner surface of the shell.

(5) Setting a preset inclination angle of the vent valve;

when the actual inclination angle of the vent valve is smaller than the preset inclination angle, the floater moves upwards, the floater assembly generates restoring moment under the double action of buoyancy and gravity, the floater assembly deflects under the action of the restoring moment, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation component rotates and inclines freely in a cavity formed below the support and above the floater, so that the upper end of the floater assembly and the sealing surface of the shell are automatically aligned and compensated to form uniform contact and sealing.

(6) When the actual inclination angle of the vent valve is larger than the preset inclination angle, the buoyancy is not enough to push the floater to move upwards, the steel ball pushes the floater to move along the guide rail on the valve seat under the action of gravity, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation member freely rotates and inclines in a cavity formed below the support and above the floater, so that the upper end of the floater assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing.

(7) The preset inclination angle is between 5 degrees and 45 degrees.

The ventilation valve for the helicopter fuel system keeps the pressure balance between the fuel tank and the outside in the working process of the helicopter, and prevents fuel from flowing out of the ventilation valve through the limiting compensation component when the flight attitude of the helicopter is larger.

Drawings

FIG. 1 is a detailed structural schematic view of a vent valve of the present invention;

FIG. 2 is a schematic illustration of the vent valve tilt angle fueling of the present invention;

FIG. 3 is a schematic view of the float assembly of the vent valve of the present invention;

FIG. 4 is a schematic view of the non-rigid inclined configuration of the float assembly of the present invention;

FIG. 5 is a schematic view of the tank of the present invention vented to atmosphere;

FIG. 6 is a schematic view of the present invention illustrating the atmosphere venting to the fuel tank;

FIG. 7 is a schematic view of the inertial seal of the vent valve in a high profile of the present invention;

the device comprises a shell, a first sealing ring, a floater, a gland, a steel ball, a second sealing ring, a valve seat, a third sealing ring, a support, a limit compensation component, a first sealing ring, a second sealing ring, a third sealing ring, a support and a support, wherein the shell is 1, the first.

Detailed Description

According to the 'Archimedes principle' of fluid mechanics and the structural characteristics of a product, the buoyancy of the float assembly is greater than the gravity and belongs to a floating body, after the helicopter is refueled until the product float assembly and the shell are sealed, the float assembly is converted into a submerged body (completely immersed in fuel oil) under the limiting position of the valve seat, and the buoyancy of the float assembly is at the maximum value. When the product is in a vertical state, the buoyancy of the floater component can be completely converted into sealing pressure, at the moment, the floater component cannot deflect, and the sealing between the sealing gasket and the shell is uniformly compressed; when the floater assembly inclines for a certain angle, the floater assembly deflects under the action of restoring torque, floats upwards to be in contact with the sealing surface of the shell, and at the moment, the limiting compensation component freely rotates and inclines in a cavity formed below the support and above the floater, so that the upper end of the floater assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing; when the inclination angle is larger, the buoyancy is not enough to push the floater to move upwards, the steel ball pushes the floater to move along the guide rail on the valve seat under the action of gravity, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation member freely rotates and inclines in a cavity formed below the support and above the floater, so that the upper end of the floater assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing.

An embodiment of the present invention provides a vent valve for a helicopter fuel system, as shown in fig. 1, said vent valve comprising: the device comprises a shell 1, a steel ball 5, a second sealing ring 6, a floater component and a valve seat 7;

the bottom of the shell 1 is connected with a valve seat 7, a second sealing ring 6 is arranged at the joint of the shell 1 and the valve seat 7, and the floater component is arranged in the shell 1 and is arranged in a guide rail of the valve seat 7;

the steel ball 5 is located between the float assembly and the valve seat 7.

Further:

(1) the float assembly includes: the device comprises a floater 3, a gland 4, a third sealing ring 8, a support 9 and a limit compensation component 10;

the floater 3 is arranged inside the shell 1 and is arranged in the guide rail of the valve seat 7;

the bottom of the floater 3 is connected with a gland 4, and a steel ball 5 is positioned between the gland 4 and a valve seat 7;

a limiting compensation member 10 is fixedly connected below the support 9, the support 9 is movably connected with the floater 3, a cavity is formed below the support 9 and above the floater 3, and the limiting compensation member 10 is positioned in the cavity;

a third sealing ring 8 is arranged above the abutment 9 for sealing the abutment 9 against the inner surface of the housing 1.

(2) The position-limiting compensating member 10 is free to rotate and tilt in the cavity formed below the seat 9 and above the float 3.

(3) The vent valve further comprises: first sealing washer 2, casing 1 are connected with helicopter oil tank upper portion flap through first sealing washer 2.

(4) When the vent valve is in a vertical state, the floater vertically moves upwards under the action of buoyancy, and the third sealing ring is tightly pressed and sealed with the inner surface of the shell.

(5) Setting a preset inclination angle of the vent valve;

when the actual inclination angle of the vent valve is smaller than the preset inclination angle, the floater moves upwards, the floater assembly generates restoring moment under the double action of buoyancy and gravity, the floater assembly deflects under the action of the restoring moment, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation component rotates and inclines freely in a cavity formed below the support and above the floater, so that the upper end of the floater assembly and the sealing surface of the shell are automatically aligned and compensated to form uniform contact and sealing.

(6) When the actual inclination angle of the vent valve is larger than the preset inclination angle, the buoyancy is not enough to push the floater to move upwards, the steel ball pushes the floater to move along the guide rail on the valve seat under the action of gravity, the floater assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation member freely rotates and inclines in a cavity formed below the support and above the floater, so that the upper end of the floater assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing.

(7) The preset inclination angle is between 5 degrees and 45 degrees.

Fig. 2 shows that when the helicopter is in an inclined state, fuel oil in an oil tank rises to a float valve, a float assembly floats upwards to be in contact with a sealing surface of a shell, and at the moment, a limiting compensation component freely rotates and inclines in a cavity formed below a support and above the float, so that the upper end of the float assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing.

FIG. 3 is a detailed structural schematic diagram of the vent valve float assembly;

fig. 4 shows the position-limiting compensation member of the float assembly of the vent valve freely rotating and tilting in the cavity formed below the support and above the float, so that the upper end of the float assembly and the sealing surface of the shell are automatically aligned and compensated.

FIG. 5(a) shows that when the helicopter is refueled, the fuel in the fuel tank increases, the fuel level rises, and the air in the fuel tank is discharged out of the helicopter through the float valve. Fig. 5(b) shows that as the fuel tank rises, the float valve is submerged, the float assembly floats to contact the sealing surface of the housing, and the buoyancy of the float assembly is converted into sealing pressure to prevent fuel from overflowing from the fuel tank.

FIG. 6 shows the fuel system supplying fuel to the engine, the fuel in the tank decreasing, the level decreasing and the outside air entering the tank through the float valve when the helicopter is operating.

Fig. 7 shows that when the helicopter flies by maneuvering, the helicopter has a large inclination attitude, the buoyancy is not enough to push the float to move upwards, the steel ball pushes the float to move along the guide rail on the valve seat under the action of gravity, the float assembly floats upwards to be in contact with the sealing surface of the shell, and the limiting compensation member freely rotates and inclines in the cavity formed below the support and above the float, so that the upper end of the float assembly is automatically aligned and compensated with the sealing surface of the shell to form uniform contact and sealing, and fuel oil is prevented from overflowing from the fuel tank.

The ventilation valve for the helicopter fuel system keeps the pressure balance between the fuel tank and the outside in the working process of the helicopter, and prevents fuel from flowing out of the ventilation valve through the limiting compensation component when the flight attitude of the helicopter is larger. The vent valve is installed at the top of the oil tank, and the outlet of the vent valve is connected with a vent system pipeline.