CN104494836A - Small aircraft fuel tank draining valve switch - Google Patents
Small aircraft fuel tank draining valve switch Download PDFInfo
- Publication number
- CN104494836A CN104494836A CN201410726618.6A CN201410726618A CN104494836A CN 104494836 A CN104494836 A CN 104494836A CN 201410726618 A CN201410726618 A CN 201410726618A CN 104494836 A CN104494836 A CN 104494836A
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- China
- Prior art keywords
- base
- valve core
- thimble
- hole
- fuel tank
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- 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.)
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Abstract
The invention discloses a small aircraft fuel tank draining valve switch. The switch comprises a shell, a base which passes on the shell, a valve core which is arranged on the base and a pressure bolt with an axial through hole in the middle, wherein the valve core is cylindrical, the lower part of the valve core is a conical thimble, the thimble extends into the through hole, a shaft shoulder is arranged on the valve core, a sealing ring capable of preventing oil leakage is arranged between the shaft shoulder and the upper end surface of the pressure bolt; the valve core passes through the middle of the base, a first spring is sleeved on the outer part of the valve core, and the lower part of the first spring is arranged on the shaft shoulder. The thimble is arranged on the lower part of the valve core, the through hole is arranged in the middle of the pressure bolt, and the first sealing ring is added. In the prior art, the bolt should be unscrewed to drain fuel, and in the invention it is only necessary to use a tool to jack up the thimble, so that the fuel is drained through the bolt through hole, the thimble is loosed, and the draining valve is closed. The draining valve switch is safe and reliable, is good in reliability and convenient to operate, and the maintainability and safety of aircrafts are greatly improved.
Description
Technical field
The present invention relates to a kind of blimp fuel tank Fuel Bleed Valve switch.
Background technology
Fuel tanker provides fuel oil under various regimes for aero-engine, and the product confrontation aircraft safety of aircraft fuel oil has significant impact, Fuel Bleed Valve switch is generally positioned at the nadir of fuel tank, the quality that fuel tank IFO intermediate fuel oil checks fuel oil is released by Fuel Bleed Valve switch, this requires that Fuel Bleed Valve switch need have flexible and convenient operation, the features such as maintainability is good, and leak tightness is strong.
Existing fuel tank Fuel Bleed Valve switch is installed on fuel tank lowest part, its complicated structure, when needing to carry out Oil drain operation, pinch device need be unscrewed drain the oil, owing to needing frequent operation herein, Long-Time Service can cause sealing effectiveness greatly to decline, and operates not convenient, need often to change seal ring, be unfavorable for safeguarding using.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of blimp Fuel Bleed Valve switching device, and to solve existing fuel tank Fuel Bleed Valve switching manipulation inconvenience, sealing effectiveness is poor, the problem that maintainability is not high.
For solving the problems of the technologies described above, the technical solution used in the present invention is: a kind of blimp fuel tank Fuel Bleed Valve switch, its gordian technique is: it comprises housing, the base be arranged on housing, be located at the valve core on base and be connected to the push bolt of base bottom, is provided with the axial through hole for draining the oil in the middle part of described push bolt;
Described valve core is column structure, and its underpart is taper thimble, and this tapered thimble extends in described through hole, and described valve core is provided with the shaft shoulder, is provided with the seal ring preventing leakage of oil between the described shaft shoulder and the upper surface of push bolt;
Described base is hollow structure, and described valve core is arranged in the middle part of this base, is provided with the first spring in described valve core outer cover, and described first spring bottom is positioned on the shaft shoulder, and top is limited on described base.
Preferably, described lower housing portion is positioned on base, is provided with the second spring between described housing and base.
Further improvement, is provided with gasket seal between described hold-down nut and base lower surface.
The beneficial effect adopting technique scheme to produce is: valve core bottom of the present invention is provided with tapered thimble, be through hole in the middle of push bolt, and increase by the first seal ring, needing before this loosers a bolt drains the oil, the present invention only needs use instrument to back down thimble, and fuel oil just can be drained the oil by bolt hole, does not need to unscrew push bolt, unclamp thimble, Fuel Bleed Valve is closed;
Adopt marquis of the present invention, Fuel Bleed Valve switch safety is reliable, and good airproof performance is easy to operate, and maintainability is strong, substantially increases maintainability and the safety of aircraft.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention (partly cuing open schematic diagram);
Fig. 2 is schematic perspective view of the present invention;
Wherein, 1 spring, 2 valve cores, 3 first seal rings, 4 second seal rings, 5 housings, 6 bases, 7 push bolts, 8 gasket seals, 9 thimbles, 10 shaft shoulders, 11 through holes.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is further detailed.
See accompanying drawing 1 and accompanying drawing 2, the present embodiment comprises to be located at outside housing 5, the base 6 be arranged on housing 5, to be located at valve core 2 on base 6 and to be connected to the push bolt 7 of base 6 bottom, is provided with the axial through hole 11 for draining the oil in the middle part of described push bolt 7;
Described valve core 2 is column structure, and its underpart is tapered thimble 9, and this tapered thimble 9 puts in described through hole 11, and described valve core 2 is provided with the shaft shoulder 10, is provided with the first seal ring 3 preventing leakage of oil between the described shaft shoulder 10 and the upper surface of push bolt 7; Gasket seal 8 is provided with between described push bolt 7 and the lower surface of base 6.
Described base 6 is hollow structure, in the middle part of it, axial location is located at the hole run through, described valve core 2 is arranged in the middle part of this base 6, spring 1 is provided with in described valve core 2 outer cover, described spring 1 bottom is positioned on the shaft shoulder 10, the top of spring 1 is positioned on the step on described base 6 top, and this step is formed by the stepped hole in the middle part of base 6, and described spring 1 top is resisted against on the step surface of formation.
Described housing 5 lower end surface is located on base 6, between the inner end surface and base 6 of described housing 5, be provided with the second seal ring 4.
When needs check fuel qualities, upper top extend into the valve core 2 in push bolt 7, and fuel oil flows out from the through hole of push bolt 7 through housing 5, base 6 inner chamber, unclamps rear Fuel Bleed Valve and automatically closes under the effect of spring 1.
When needing to release fuel tank IFO intermediate fuel oil, push bolt 7 is turned on, take out valve core 2 and spring 1, special jointing of draining the oil is installed and releases fuel oil.
The present invention checks through actual installation at certain aircraft, and good airproof performance is easy to operate, and maintainability is strong, solves before this that Fuel Bleed Valve switch seal is bad, unhandy problem.
To the above-mentioned explanation of the disclosed embodiments, professional and technical personnel in the field are realized or uses the invention.To be apparent for those skilled in the art to the multiple amendment of these embodiments, General Principle as defined herein when not departing from the spirit or scope of the invention, can realize in other embodiments.Therefore, the invention can not be restricted to these embodiments shown in this article, but will meet the widest scope consistent with principle disclosed herein and features of novelty.
Claims (3)
1. a blimp fuel tank Fuel Bleed Valve switch, it is characterized in that: it comprises housing (5), the base (6) be arranged on housing (5), be located at the valve core (2) on base (6) and be connected to the push bolt (7) of base (6) bottom, described push bolt (7) middle part is provided with the axial through hole (11) for draining the oil;
Described valve core (2) is column structure, its underpart is tapered thimble (9), this taper thimble (9) extends in described through hole (11), described valve core (2) is provided with the shaft shoulder (10), is provided with the first seal ring (3) preventing leakage of oil between the described shaft shoulder (10) and the upper surface of push bolt (7);
Described base (6) is hollow structure, and described valve core (2) is arranged in this base (6) middle part, and be provided with spring (1) in described valve core (2) outer cover, described spring (1) bottom is positioned on the shaft shoulder (10), and top is limited on described base (6).
2. blimp fuel tank Fuel Bleed Valve switch according to claim 1, is characterized in that: described housing (5) bottom is positioned on base (6), is provided with the second seal ring (4) between described housing (5) and base (6).
3. blimp fuel tank Fuel Bleed Valve switch according to claim 1, is characterized in that: be provided with gasket seal (8) between described push bolt (7) and base (6) lower surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410726618.6A CN104494836B (en) | 2014-12-04 | 2014-12-04 | Small aircraft fuel tank draining valve switch |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410726618.6A CN104494836B (en) | 2014-12-04 | 2014-12-04 | Small aircraft fuel tank draining valve switch |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104494836A true CN104494836A (en) | 2015-04-08 |
| CN104494836B CN104494836B (en) | 2017-05-10 |
Family
ID=52936322
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410726618.6A Expired - Fee Related CN104494836B (en) | 2014-12-04 | 2014-12-04 | Small aircraft fuel tank draining valve switch |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104494836B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109700A (en) * | 2015-08-12 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Residual-oil discharging system and oil discharging method of emergency oil discharging header pipe |
| CN105416599A (en) * | 2015-12-13 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Self-sealed valve device for oil draining |
| CN106838336A (en) * | 2016-12-15 | 2017-06-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft jettison gear of easy care |
| CN110979703A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Ground oil drainage device of aircraft fuel system |
| CN111058949A (en) * | 2020-01-06 | 2020-04-24 | 南京航空航天大学 | Pressure-controlled oil drainage valve for starting of turboshaft engine and use method thereof |
| CN111216906A (en) * | 2019-11-15 | 2020-06-02 | 陕西飞机工业（集团）有限公司 | Quick-release self-sealing type wing oil tank oil drainage device |
| CN111824432A (en) * | 2019-04-18 | 2020-10-27 | 成都飞机工业（集团）有限责任公司 | Lightning protection type oil drainage structure of aircraft oil tank |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU197892U1 (en) * | 2019-12-26 | 2020-06-04 | Акционерное общество "Технодинамика" | Flameproof Drain Valve |
| RU197781U1 (en) * | 2019-12-26 | 2020-05-28 | Акционерное общество "Технодинамика" | Electrically actuated drain valve for emergency fuel system |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5433410A (en) * | 1994-05-27 | 1995-07-18 | Foltz; Timothy J. | Drain valve |
| US5478049A (en) * | 1995-03-20 | 1995-12-26 | Lescoe; Robert J. | Quick drain valve |
| FR2734883A1 (en) * | 1995-05-29 | 1996-12-06 | Marin Lamellet Pierre | Oil sump emptying plug for engines in motor vehicles |
| CN2541609Y (en) * | 2002-04-12 | 2003-03-26 | 杨文志 | Automobile engine oil drainer |
| KR20040081893A (en) * | 2003-03-17 | 2004-09-23 | 에스케이 주식회사 | Plug and socket for exchanging car oil |
| CN101346278A (en) * | 2005-12-22 | 2009-01-14 | 空中客车英国有限公司 | Fuel tank valve |
| CN202493727U (en) * | 2012-03-23 | 2012-10-17 | 林菊芬 | Oil outlet valve |
| CN203035305U (en) * | 2012-12-20 | 2013-07-03 | 李祖培 | Oil drainage bolt |
-
2014
- 2014-12-04 CN CN201410726618.6A patent/CN104494836B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5433410A (en) * | 1994-05-27 | 1995-07-18 | Foltz; Timothy J. | Drain valve |
| US5478049A (en) * | 1995-03-20 | 1995-12-26 | Lescoe; Robert J. | Quick drain valve |
| FR2734883A1 (en) * | 1995-05-29 | 1996-12-06 | Marin Lamellet Pierre | Oil sump emptying plug for engines in motor vehicles |
| CN2541609Y (en) * | 2002-04-12 | 2003-03-26 | 杨文志 | Automobile engine oil drainer |
| KR20040081893A (en) * | 2003-03-17 | 2004-09-23 | 에스케이 주식회사 | Plug and socket for exchanging car oil |
| CN101346278A (en) * | 2005-12-22 | 2009-01-14 | 空中客车英国有限公司 | Fuel tank valve |
| CN202493727U (en) * | 2012-03-23 | 2012-10-17 | 林菊芬 | Oil outlet valve |
| CN203035305U (en) * | 2012-12-20 | 2013-07-03 | 李祖培 | Oil drainage bolt |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109700A (en) * | 2015-08-12 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | Residual-oil discharging system and oil discharging method of emergency oil discharging header pipe |
| CN105416599A (en) * | 2015-12-13 | 2016-03-23 | 中国航空工业集团公司西安飞机设计研究所 | Self-sealed valve device for oil draining |
| CN105416599B (en) * | 2015-12-13 | 2019-01-18 | 中国航空工业集团公司西安飞机设计研究所 | One kind is drained the oil self-styled valve arrangement |
| CN106838336A (en) * | 2016-12-15 | 2017-06-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft jettison gear of easy care |
| CN111824432A (en) * | 2019-04-18 | 2020-10-27 | 成都飞机工业（集团）有限责任公司 | Lightning protection type oil drainage structure of aircraft oil tank |
| CN111216906A (en) * | 2019-11-15 | 2020-06-02 | 陕西飞机工业（集团）有限公司 | Quick-release self-sealing type wing oil tank oil drainage device |
| CN110979703A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Ground oil drainage device of aircraft fuel system |
| CN111058949A (en) * | 2020-01-06 | 2020-04-24 | 南京航空航天大学 | Pressure-controlled oil drainage valve for starting of turboshaft engine and use method thereof |
| CN111058949B (en) * | 2020-01-06 | 2021-01-15 | 南京航空航天大学 | Pressure-controlled oil drainage valve for starting of turboshaft engine and use method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104494836B (en) | 2017-05-10 |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170510 Termination date: 20201204 |