CN112407305B - Breather valve for helicopter fuel system - Google Patents

Breather valve for helicopter fuel system Download PDF

Info

Publication number
CN112407305B
CN112407305B CN202011214560.9A CN202011214560A CN112407305B CN 112407305 B CN112407305 B CN 112407305B CN 202011214560 A CN202011214560 A CN 202011214560A CN 112407305 B CN112407305 B CN 112407305B
Authority
CN
China
Prior art keywords
floater
shell
sealing
valve seat
support
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202011214560.9A
Other languages
Chinese (zh)
Other versions
CN112407305A (en
Inventor
杨勇志
孟庆会
周佐俊
王成
邹高鹏
贾彭辉
屈子悦
段伟杰
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
China Helicopter Research and Development Institute
Original Assignee
China Helicopter Research and Development Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by China Helicopter Research and Development Institute filed Critical China Helicopter Research and Development Institute
Priority to CN202011214560.9A priority Critical patent/CN112407305B/en
Publication of CN112407305A publication Critical patent/CN112407305A/en
Application granted granted Critical
Publication of CN112407305B publication Critical patent/CN112407305B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M37/00—Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatus; Arrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
    • F02M37/0076—Details of the fuel feeding system related to the fuel tank
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K1/00—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K1/00—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces
    • F16K1/32—Details
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K31/00—Actuating devices; Operating means; Releasing devices
    • F16K31/12—Actuating devices; Operating means; Releasing devices actuated by fluid
    • F16K31/18—Actuating devices; Operating means; Releasing devices actuated by fluid actuated by a float
    • F16K31/20—Actuating devices; Operating means; Releasing devices actuated by fluid actuated by a float actuating a lift valve

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Self-Closing Valves And Venting Or Aerating Valves (AREA)

Abstract

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 device comprises a shell, a steel ball, a second sealing ring, a floater assembly and a 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.

Description

Breather valve for helicopter fuel system
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 ability of the helicopter, fuel oil needs to be prevented from leaking from the air vent when the helicopter crashes, 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 sealing ring is 3, the floater is 4, the gland is 5, the steel ball is 6, the second sealing ring is 7, the valve seat is 8, the third sealing ring is 9, the support is 10, and the limit compensation component is arranged.
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, thereby automatically aligning and compensating the upper end of the float assembly with the sealing surface of the shell.
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 pipeline of a ventilation system.

Claims (3)

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 floater component and the valve seat (7);
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);
the limit compensation component (10) can freely rotate and incline in a cavity formed below the support (9) and above the floater (3);
when the vent valve is in a vertical state, under the action of buoyancy, the floater vertically moves upwards, and the third sealing ring is tightly pressed and sealed with the inner surface of the shell;
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 component generates a restoring moment under the double action of buoyancy and gravity, the floater component deflects under the action of the restoring moment, the floater component 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 component and the sealing surface of the shell are automatically aligned and compensated to form uniform contact and sealing;
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.
2. 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).
3. A vent valve for a helicopter fuel system according to claim 1,
the preset inclination angle is between 5 degrees and 45 degrees.
CN202011214560.9A 2020-11-03 2020-11-03 Breather valve for helicopter fuel system Active CN112407305B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011214560.9A CN112407305B (en) 2020-11-03 2020-11-03 Breather valve for helicopter fuel system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011214560.9A CN112407305B (en) 2020-11-03 2020-11-03 Breather valve for helicopter fuel system

Publications (2)

Publication Number Publication Date
CN112407305A CN112407305A (en) 2021-02-26
CN112407305B true CN112407305B (en) 2022-09-16

Family

ID=74827468

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011214560.9A Active CN112407305B (en) 2020-11-03 2020-11-03 Breather valve for helicopter fuel system

Country Status (1)

Country Link
CN (1) CN112407305B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114348278A (en) * 2021-12-22 2022-04-15 石家庄飞机工业有限责任公司 Oil collecting tank ventilation device after turboprop engine is replaced on Y5B airplane

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4730218B2 (en) * 2006-06-13 2011-07-20 豊田合成株式会社 Fuel shut-off valve
CN201264523Y (en) * 2008-09-24 2009-07-01 陈恳 Leak-proof oil tank lid
CN102251891A (en) * 2011-07-20 2011-11-23 重庆润通动力有限公司 Fuel oil tank air vent valve
CN202451322U (en) * 2012-01-16 2012-09-26 重庆润通动力有限公司 Vent valve installed on general gasoline engine fuel tank
CN103383006B (en) * 2013-05-28 2015-08-12 东风汽车公司 A kind of overturn-preventing valve and using method thereof
JP2019520526A (en) * 2016-05-25 2019-07-18 スウェージロック カンパニー Valve with self-aligning stem tip
CN109357057A (en) * 2018-11-09 2019-02-19 中国直升机设计研究所 A kind of preventing oil spill breather valve for helicopter fuel system

Also Published As

Publication number Publication date
CN112407305A (en) 2021-02-26

Similar Documents

Publication Publication Date Title
US4679581A (en) Fuel tank vent valve
US20090236350A1 (en) Ventilating device for fuel tank
EP1359042A1 (en) Method of venting fuel vapor from a tank and system therefor
CN112407305B (en) Breather valve for helicopter fuel system
CN102481839A (en) Vent valve
MXPA02009181A (en) Float operated fuel tank vapor vent valve.
US6230732B1 (en) Safety valve for a liquid tank
JP4517346B2 (en) System and method for recirculation control of fuel evaporative gas during refueling
US9475383B2 (en) Aircraft fuel tank system
RU2726843C1 (en) Float valve, fuel tank and vehicle (embodiments)
US4376446A (en) Vent valve for fuel tanks and the like
KR101436180B1 (en) Liquid tank venting system
EP2584233B1 (en) Pressure regulating float valve
US10967733B2 (en) Fuel shutoff valve
US11738990B2 (en) Ullage float assembly for fuel tank and methods of use
CN110963058A (en) Float valve for aircraft ventilation and pressurization system
CN219119948U (en) Micro-pressure lip-shaped sealing structure
WO2013176602A1 (en) Vent valve
CN209524121U (en) A kind of tank pressure adjusting and integrated overturning control valve of ventilating
CN211693670U (en) Breather valve structure with low dynamic leakage and high pressure reopening function
CN206309670U (en) Pressure oil tank oil filler device
KR101257713B1 (en) Vent valve
CN117227988A (en) Vent device for a tank and tank for an aircraft
CN217074809U (en) Self-exhaust refueling mechanism for unmanned aerial vehicle vacuum oil tank
CN111098704A (en) Combined valve

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant