CN102147016B - Oil drainage valve for fuel system of airplane - Google Patents
Oil drainage valve for fuel system of airplane Download PDFInfo
- Publication number
- CN102147016B CN102147016B CN 201110005845 CN201110005845A CN102147016B CN 102147016 B CN102147016 B CN 102147016B CN 201110005845 CN201110005845 CN 201110005845 CN 201110005845 A CN201110005845 A CN 201110005845A CN 102147016 B CN102147016 B CN 102147016B
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- fuel system
- valve
- bushing
- spool
- position limit
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Abstract
The invention belongs to the technical field of a fuel system of an airplane and relates to an oil drainage valve for a fuel system of an airplane. The oil drainage valve for the fuel system of the airplane consists of a shell body, a valve, a limiting device, a spring, a handle and the like; the valve is at the closing and locking position at the beginning; when the valve is opened, the handle is firstly pulled out to be rotated to the opening position and then is loosened, and finally, the valve is locked at the opening position; and when the valve is closed, the handle is pulled out to be rotated to the closing position and then is loosened, and finally, the valve is locked at the closing position. The oil drainage valve for the fuel system of the airplane is opened through rotating the handle; and the reliable locking of the valve is realized under the action of the spring force. The oil drainage valve for the fuel system of the airplane has a simple structure and high reliability, is convenient to operate, effectively improves the maintenance efficiency to the airplane, reduces the maintenance workload and shortens the maintenance period.
Description
Technical field
The invention belongs to the aircraft fuel system technical field, relate to a kind of aircraft fuel system oil discharging valve.
Background technique
The aircraft fuel system oil discharging valve is installed on the oil-fired system pipeline, is used for emitting on ground the deposition or the excess oil of oil-fired system.Awing for preventing valve, open automatically because of reasons such as vibration, overloads, cause fuel oil to reveal, valve should have reliable locking device.
Along with aircraft to maintainability require increasingly highly, various ground maintenance job requirements are simple to operate, reliable and quick.Traditional aircraft fuel system oil discharging valve adopts mostly between handle and the valve housing and locks through safety fuse cutout, after the ground crew uses oil discharging valve at every turn, all needs lock with safety fuse cutout again.Wherein, when insuring, need fuse threading be crossed the attachment hole on handle and the valve housing, operation easier is big, has increased maintenance workload, has prolonged maintenance period, has caused suitable inconvenience for the real aircraft maintenance work.
Summary of the invention
The objective of the invention is: provide a kind of and can realize aircraft fuel system oil discharging valve convenient, fast, reliable locking.
Technological scheme of the present invention is: a kind of aircraft fuel system oil discharging valve, and it comprises handle, spring, position limit socket, housing, spool, external bushing, threaded bushing, guide bush, guide pad, spring retainer, the handle inwall engages with external bushing; Position limit socket one end and external bushing end face compress interlock; Its other end is fixed on inner walls, and the threaded bushing inwall is threaded with spool, between its outer surface and the external bushing for being slidingly connected; And it radially rotates through position limit pin constraint between threaded bushing and the external bushing; Spring is arranged between external bushing and the threaded bushing, and the one of which end withstands external bushing, and the other end is compressed by the spring retainer that is arranged on the threaded bushing; Guide bush is arranged between position limit socket and the spool, and spool is provided with one and is used to retrain it and radially rotates and be arranged on the embedded guide pad of guide bush.
The external bushing end face is provided with latch, and the end face that position limit socket joins with it is provided with and the corresponding draw-in groove of latch.
Be provided with between threaded bushing and the position limit socket inwall and be used to the steel ball that prevents that handle is pulled out.
Guide bush and position limit socket are connected to an integral body, and the two one is made.
Be provided with one between spool and the housing and be used to seal spacing block, and spool is through sealing rubber ring and external connector sealing.
The invention has the beneficial effects as follows: aircraft fuel system oil discharging valve of the present invention is through the Unscrew valve of handle, and realization is to the reliable locking of valve under the effect of spring force, and it is simple in structure; Easy to operate, reliability is high, effectively improves aircraft maintenance efficient; Reduce maintenance workload; Shorten maintenance period, therefore can alleviate the workload of ground crew when using oil discharging valve greatly, improve the maintainability of oil-fired system.
Description of drawings
Fig. 1 is the outline drawing of aircraft fuel system oil discharging valve of the present invention,
Fig. 2 is the A-A sectional view of Fig. 1,
Fig. 3 is the B-B sectional view of Fig. 1,
Fig. 4 is the C-C sectional view of Fig. 1,
Wherein, 1-handle, 2-spring, 3-position limit socket, 4-housing, 5-spool, 6-external bushing, 7-threaded bushing, 8-guide bush, 9-link stopper, 10-steel ball, 11-guide pad, 12-sealing rubber ring, 13-joint, 14-spring retainer.
Embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is described in further detail:
See also Fig. 1, its be aircraft fuel system oil discharging valve of the present invention partly cut open figure.In this mode of execution, said aircraft fuel system oil discharging valve comprises housing 4, spool 5, position limit socket 3, spring 2, handle 1, external bushing 6, threaded bushing 7, guide bush 8, link stopper 9, steel ball 10, guide pad 11, sealing rubber ring 12, joint 13, spring retainer 14.
Handle 1 inwall engages with external bushing 6, and position limit socket 3 one ends are provided with draw-in groove, and with the latch interlock of external bushing end face, its other end is fixed on housing 4 inwalls through being threaded.Threaded bushing 7 passes through thread bush on spool 5; Between its outer surface and the external bushing 6 for being slidingly connected; And it radially rotates through square end surface constraint between threaded bushing 7 and the external bushing 6, is provided with between threaded bushing 7 and position limit socket 3 inwalls simultaneously to be used to the steel ball 10 that prevents that handle is pulled out.Spring 2 is arranged between external bushing 6 and the threaded bushing 7, and the one of which end withstands external bushing 6, and the other end is compressed by the spring retainer 14 that is arranged on the threaded bushing 7, and said spring retainer 14 is a position-limited nail.Guide bush 8 is arranged between position limit socket 3 and the spool 5, is used for the axially directed of spool, and guide bush 8 can connect as one the two one manufacturing with position limit socket 3.And spool is provided with one and is used to retrain it and radially rotates and be arranged on the embedded guide pad 11 of guide bush 8.Be provided with one between spool 5 and the housing 4 and be used to seal spacing block 9, and spool 5 seals through sealing rubber ring 12 with joint 13.
Aircraft fuel system oil discharging valve of the present invention is not receiving external force to do the time spent, and valve makes latch and the draw-in groove in the position limit socket 3 on the external bushing 6 lock each other under spring 2 compression force.When opening valve, at first extract handle 1, latch and position limit socket 3 inner card cages are thrown off, rotatable handle 1 drives threaded bushinges 7 rotations through external bushing 6 again, makes threaded bushing 7 relative spools 5 rotations, makes spool 5 axial retraction, thereby opens valve.When release handle 1, latch under spring 2 effects on the external bushing 6 and the draw-in groove interlock again in the position limit socket 3, the rotation of constraint threaded bushing 7, thus 5 axial motions of restriction spool realize the locking to valve.
In like manner during throttle down, extract handle 1, handle 1 rotates to closed position, and promptly joint 13 compresses spool 5, makes valve closing.Release handle 1 then, under spring 2 compression force, make latch and the draw-in groove interlock in the position limit socket 3 on the external bushing 6, thereby the axial motion of restriction spool realizes the locking of valve.
Aircraft fuel system oil discharging valve of the present invention is through the Unscrew valve of handle, and realization is to the reliable locking of valve under the effect of spring force, and it is simple in structure; Easy to operate, reliability is high, effectively improves aircraft maintenance efficient; Reduce maintenance workload, shorten maintenance period.
Claims (4)
1. aircraft fuel system oil discharging valve; It is characterized in that: comprise handle (1), spring (2), position limit socket (3), housing (4), spool (5), external bushing (6), threaded bushing (7), guide bush (8), guide pad (11), spring retainer (14); Handle (1) inwall engages with external bushing (6); Position limit socket (3) one ends and external bushing end face compress interlock; Its other end is fixed on housing (4) inwall, and threaded bushing (7) inwall is threaded with spool (5), between its outer surface and the external bushing (6) for being slidingly connected; And it radially rotates through position limit pin constraint between threaded bushing (7) and the external bushing (6); Spring (2) is arranged between external bushing (6) and the threaded bushing (7), and the one of which end withstands external bushing (6), and the other end is compressed by the spring retainer (14) that is arranged on the threaded bushing (7); Guide bush (8) is arranged between position limit socket (3) and the spool (5), and spool (5) is provided with one and is used to retrain it and radially rotates and be arranged on the embedded guide pad (11) of guide bush (8).
2. aircraft fuel system oil discharging valve according to claim 1 is characterized in that: the external bushing end face is provided with latch, and the end face that position limit socket (3) joins with it is provided with and the corresponding draw-in groove of latch.
3. aircraft fuel system oil discharging valve according to claim 2 is characterized in that: be provided with between threaded bushing (7) and position limit socket (3) inwall and be used to the steel ball (10) that prevents that handle is pulled out.
4. aircraft fuel system oil discharging valve according to claim 3 is characterized in that: guide bush (8) is connected to an integral body with position limit socket (3), and the two one is made.
5. aircraft fuel system oil discharging valve according to claim 4; It is characterized in that: be provided with one between spool (5) and the housing (4) and be used to seal spacing block (9), and spool (5) is through sealing rubber ring (12) and external connector (13) sealing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110005845 CN102147016B (en) | 2011-01-13 | 2011-01-13 | Oil drainage valve for fuel system of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110005845 CN102147016B (en) | 2011-01-13 | 2011-01-13 | Oil drainage valve for fuel system of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102147016A CN102147016A (en) | 2011-08-10 |
| CN102147016B true CN102147016B (en) | 2012-08-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110005845 Active CN102147016B (en) | 2011-01-13 | 2011-01-13 | Oil drainage valve for fuel system of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102147016B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105673868A (en) * | 2016-04-14 | 2016-06-15 | 无锡市东液机械制造有限公司 | Valve body structure of oil drainage valve |
| CN105782471A (en) * | 2016-04-14 | 2016-07-20 | 无锡市东液机械制造有限公司 | Oil drain valve structure |
| CN105782469A (en) * | 2016-04-25 | 2016-07-20 | 哈尔滨东安发动机（集团）有限公司 | Oil discharge switch structure |
| CN109114050A (en) * | 2018-11-02 | 2019-01-01 | 江苏柳工机械有限公司 | The jettison gear of hydraulic oil container |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR865659A (en) * | 1940-05-16 | 1941-05-30 | Martin | Pneumatic control device with general signaling for pipes |
| GB847362A (en) * | 1956-04-12 | 1960-09-07 | Koswa Ltd | Improvements in valves for regulating the flow of fluids |
| GB2311234A (en) * | 1996-03-20 | 1997-09-24 | Pall Corp | Liquid separating systems |
| CN201661536U (en) * | 2010-02-09 | 2010-12-01 | 陕西秦峰液压有限责任公司 | Hand hydraulic valve |
-
2011
- 2011-01-13 CN CN 201110005845 patent/CN102147016B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR865659A (en) * | 1940-05-16 | 1941-05-30 | Martin | Pneumatic control device with general signaling for pipes |
| GB847362A (en) * | 1956-04-12 | 1960-09-07 | Koswa Ltd | Improvements in valves for regulating the flow of fluids |
| GB2311234A (en) * | 1996-03-20 | 1997-09-24 | Pall Corp | Liquid separating systems |
| CN201661536U (en) * | 2010-02-09 | 2010-12-01 | 陕西秦峰液压有限责任公司 | Hand hydraulic valve |
Non-Patent Citations (1)
| Title |
|---|
| 王在俊等.《Cessna 172R飞机燃油放油活门结构缺陷分析及改进》.《润滑与密封》.2007,第180-181页. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102147016A (en) | 2011-08-10 |
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| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
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| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Shaanxi, Hanzhoung Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Shaanxi, Hanzhoung Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |