CN105464812B - A kind of aero-engine fuel control system starting exhaust apparatus - Google Patents
A kind of aero-engine fuel control system starting exhaust apparatus Download PDFInfo
- Publication number
- CN105464812B CN105464812B CN201510707839.3A CN201510707839A CN105464812B CN 105464812 B CN105464812 B CN 105464812B CN 201510707839 A CN201510707839 A CN 201510707839A CN 105464812 B CN105464812 B CN 105464812B
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- piston
- valve
- housing
- bushing
- exhaust apparatus
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- Gasket Seals (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention belongs to aero-engine fuel oil control field, a kind of aero-engine fuel control system starting exhaust apparatus.Cavity is provided with housing, bushing (6) is in the cavity, bushing (6) is provided with sealing ring (7) and housing between, valve (2) top sets fluted, rubber blanket (3) is installed in groove, rubber blanket (3) is fitted in an openend of bushing (6), sets jagged in the surrounding of valve (2) upper groove；Piston (5) is installed outside another openend of housing hollow neck bush (6), it is provided with the end face of valve (2) one end raised (4) in piston (5), spring (1) is respectively arranged between bushing (6) and piston (5), piston (5) and valve (2), sealing ring (7) is provided between the outer end of piston (5) and housing.Propose a kind of simple structure, the starting exhaust apparatus that can be automatically turned on and close with servo pressure change.
Description
Technical field
The invention belongs to aero-engine fuel oil control field, it is related to the improvement to starting exhaust apparatus.
Background technology
Aero-engine fuel control system need to empty the air that cavity mixes when starting, and this is accomplished by fuel oil control
A kind of starting exhaust apparatus is set in system.Traditional starting exhaust apparatus is a kind of simple ball valve, when starting, fuel oil control
Lead to pressurised oil in system processed, using special tooling open manually ball valve, the fuel oil discharge fuel oil control system of air will be mixed in
System is outer.The starting exhaust apparatus of this form, simple structure but automate it is poor, need to manually make using special tooling starting exhaust fill
Unlatching is put, the support cost of engine is increased.
The content of the invention
Present invention solves the technical problem that being：A kind of simple structure is proposed, can be automatically turned on and be closed with servo pressure change
The starting exhaust apparatus for closing.
The technical scheme is that：A kind of aero-engine fuel control system starting exhaust apparatus, it is characterized by：
Described device includes spring 1, valve 2, rubber blanket 3, projection 4, piston 5, bushing 6 and sealing ring 7, and sky is provided with housing
Chamber, bushing 6 is arranged in the cavity, and sealing ring 7 is provided between bushing 6 and housing, and the top of valve 2 sets fluted, groove
Rubber blanket 3 is inside installed, rubber blanket 3 is fitted in an openend of bushing 6, connection fuel tank is provided with the periphery of valve 2 low
The breach of cavity between force feed and valve 2 and piston 5；
Piston 5 is installed outside another openend of housing hollow neck bush 6, in piston 5 on one end end face of valve 2
Raised 4 are provided with, spring 1, the outer end of piston 5 and housing are respectively arranged between bushing 6 and piston 5, piston 5 and valve 2
Between be provided with sealing ring 7；
It is located on housing and through hole is provided between valve 2 and piston 5, connects oil return box, the end of device valve 2 connection fuel tank
Low pressure oil, hydraulic oil after the end of piston 5 connection fuel pump supercharging.
Improved as one kind of the technical program, the end of spring 1 is provided with adjust pad.
Improved as one kind of the technical program, raised 4 on the end face of piston 5 are screw, screw is connected through a screw thread solid
It is scheduled on piston 5.
Improved as one kind of the technical program, the sealing ring 7 set between the outer end of piston 5 and housing is U-shaped.
Beneficial effects of the present invention are：It is servo using the hydraulic oil after low pressure oil and fuel pump from fuel tanker
Oil, opening and closing automatically for exhaust apparatus, the present invention less part, better simply structure reality are realized by compression spring
Aero-Engine Start degassing function is showed.The starting device can be automatically turned on and closed, and reduce the work of engine maintenance
Amount, reduces engine support cost.
Brief description of the drawings
Fig. 1 is structural representation of the invention；
In figure, 1- springs, 2- valve, 3- rubber blankets, 4- is raised, 5- pistons, 6- bushings, 7- sealing rings, 8- pads.
Specific embodiment
The technical program is described in further details below in conjunction with the accompanying drawings.Referring to Fig. 1.
A kind of aero-engine fuel control system is sent out with exhaust apparatus, described starting exhaust apparatus is started positioned at aviation
Motivation fuel control system top, it includes spring 1, valve 2, rubber blanket 3, raised 4, piston 5, bushing 6, sealing ring 7.In shell
Cavity is provided with vivo, and bushing 6 is arranged in the cavity, and sealing ring 7 is provided between bushing 6 and housing；The top of valve 2 is provided with
Groove, is provided with rubber blanket 3 in groove, rubber blanket 3 is fitted in an openend of bushing 6, the company of being provided with the periphery of valve 2
The breach of logical cavity between fuel tank low pressure oil and valve 2 and piston 5；Another openend in housing hollow is provided with piston 5, convex
Play 4 and be fixed on piston 5 near one end of valve 2；In bushing 6 and piston 5, spring 1 is respectively arranged between piston 5 and valve 2；
Sealing ring 7 is provided between 5 outer end and housing；It is located on housing and through hole is provided between valve 2 and piston 5, connects oil return
Case；The device valve 2 connects fuel tank low pressure oil near the one end of bushing 6, and piston 5 is communicated with fuel pump supercharging away from the one end of valve 2
Hydraulic oil afterwards.
When starting exhaust apparatus work, the fuel oil air pump inoperative of fuel control system, the low pressure oil from fuel tanker is pushed away
The dynamic compression spring 1 of valve 2, the cavity that fuel oil is entered between valve 2 and piston 5 air by breach on valve 2, then by housing
Through hole between 2 and 5 is entered in oil return box, realizes the automatic ventilating function of the device；Start after the completion of being vented, fuel pump
Start working, hydraulic oil promotes the compression spring 1 of piston 5 after fuel pump, raised 4 promote valve 2 to close, and realization is automatically switched off work(
Energy.
Spring end is provided with pad 8, the decrement of spring 1 can be adjusted by the thickness of adjusting gasket 8,
And then realize that starting exhaust apparatus closing presure can adjust.
The projection of the end of piston 5 is screw 4, and screw 4 is connected through a screw thread and is fixed on 5.Screwed in by adjusting screw 4 and lived
The depth of plug 5 realizes the adjustment to starting exhaust apparatus closing presure
The sealing ring 7 set between 5 outer ends and housing is " U " type, and the hydraulic oil after fuel pump is acted in sealing ring
Side, makes sealing ring be adjacent to housing cavity surface, and sealing property is preferable.
Claims (4)
1. a kind of aero-engine fuel control system is used and starts exhaust apparatus, it is characterized by：Described device includes spring
(1), valve (2), rubber blanket (3), raised (4), piston (5), bushing (6) and sealing ring (7), are provided with cavity in housing, serve as a contrast
In the cavity, bushing (6) is provided with sealing ring (7) to set (6) and housing between, and valve (2) top sets fluted, recessed
Rubber blanket (3) is installed, rubber blanket (3) is fitted in an openend of bushing (6), is provided with the periphery of valve (2) in groove
The breach of cavity between connection fuel tank low pressure oil and valve (2) and piston (5)；
Piston (5) is installed outside another openend of housing hollow neck bush (6), in piston (5) near valve (2) one end end
Raised (4) are provided with face, spring (1) is respectively arranged between bushing (6) and piston (5), piston (5) and valve (2), it is living
Fill in and be provided with sealing ring (7) between the outer end of (5) and housing；
It is located on housing and through hole is provided between valve (2) and piston (5), connects oil return box, the device valve (2) end connection oil
Case low pressure oil, hydraulic oil after piston (5) end connection fuel pump supercharging.
2. a kind of aero-engine fuel control system according to claim 1 is used and starts exhaust apparatus, it is characterized by：
Spring (1) end is provided with adjust pad.
3. a kind of aero-engine fuel control system according to claim 1 is used and starts exhaust apparatus, it is characterized by：It is living
Projection (4) on plug (5) end face is screw, and screw is connected through a screw thread and is fixed on piston (5).
4. a kind of aero-engine fuel control system according to claim 1 is used and starts exhaust apparatus, it is characterized by：
The sealing ring (7) that piston (5) is set between outer end and housing is U-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510707839.3A CN105464812B (en) | 2015-10-27 | 2015-10-27 | A kind of aero-engine fuel control system starting exhaust apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510707839.3A CN105464812B (en) | 2015-10-27 | 2015-10-27 | A kind of aero-engine fuel control system starting exhaust apparatus |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105464812A CN105464812A (en) | 2016-04-06 |
| CN105464812B true CN105464812B (en) | 2017-06-16 |
Family
ID=55602903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510707839.3A Expired - Fee Related CN105464812B (en) | 2015-10-27 | 2015-10-27 | A kind of aero-engine fuel control system starting exhaust apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105464812B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762901B (en) * | 2016-11-30 | 2018-05-22 | 北京航科发动机控制系统科技有限公司 | A kind of pressure difference values dynamic regulation device adjustable etc. online |
| CN108035806A (en) * | 2017-11-08 | 2018-05-15 | 中国航发北京航科发动机控制系统科技有限责任公司 | A kind of parking jettison gear of aero-engine fuel dispenser |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4041695A (en) * | 1975-11-21 | 1977-08-16 | The Garrett Corporation | Fuel system pneumatic purge apparatus and method |
| EP0240541B1 (en) * | 1985-09-25 | 1992-04-29 | Rosemount Inc. | Pneumatic amplifier with negative feedback for current to pressure transducer |
| GB2390020A (en) * | 2002-06-27 | 2003-12-31 | Alec Melvin | Extinguishing oil and gas well blow-out fires |
| CN201901307U (en) * | 2010-10-08 | 2011-07-20 | 姜法宏 | Automatic exhaust steam valve for liquid flexible package |
| CN202731839U (en) * | 2012-06-13 | 2013-02-13 | 中国石油天然气股份有限公司 | Pressure difference type antifreezing constant pressure air release valve |
-
2015
- 2015-10-27 CN CN201510707839.3A patent/CN105464812B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4041695A (en) * | 1975-11-21 | 1977-08-16 | The Garrett Corporation | Fuel system pneumatic purge apparatus and method |
| EP0240541B1 (en) * | 1985-09-25 | 1992-04-29 | Rosemount Inc. | Pneumatic amplifier with negative feedback for current to pressure transducer |
| GB2390020A (en) * | 2002-06-27 | 2003-12-31 | Alec Melvin | Extinguishing oil and gas well blow-out fires |
| CN201901307U (en) * | 2010-10-08 | 2011-07-20 | 姜法宏 | Automatic exhaust steam valve for liquid flexible package |
| CN202731839U (en) * | 2012-06-13 | 2013-02-13 | 中国石油天然气股份有限公司 | Pressure difference type antifreezing constant pressure air release valve |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105464812A (en) | 2016-04-06 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 102200 No. 1 Li Xiang Road, Changping District science and Technology Park, Beijing Patentee after: CHINA AEROSPACE BEIJING HANGKE ENGINE CONTROL SYSTEM TECHNOLOGY Co.,Ltd. Address before: 102200 No. 1 Li Xiang Road, Changping District science and Technology Park, Beijing Patentee before: BEIJING HANGKE ENGINE CONTROL SYSTEM SCIENCE & TECHNOLOGY Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170616 Termination date: 20211027 |
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| CF01 | Termination of patent right due to non-payment of annual fee |