CN109404135B - Oil return type oil transportation control system - Google Patents
Oil return type oil transportation control system Download PDFInfo
- Publication number
- CN109404135B CN109404135B CN201811497078.3A CN201811497078A CN109404135B CN 109404135 B CN109404135 B CN 109404135B CN 201811497078 A CN201811497078 A CN 201811497078A CN 109404135 B CN109404135 B CN 109404135B
- Authority
- CN
- China
- Prior art keywords
- oil
- tank
- fuel
- main
- oil tank
- 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
Links
- 239000000446 fuel Substances 0.000 claims abstract description 54
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 230000005484 gravity Effects 0.000 abstract description 5
- 239000003921 oil Substances 0.000 description 159
- 239000000295 fuel oil Substances 0.000 description 7
- 239000002828 fuel tank Substances 0.000 description 7
- 238000000034 method Methods 0.000 description 3
- 239000010763 heavy fuel oil Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/236—Fuel delivery systems comprising two or more pumps
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention discloses an oil return type oil transportation control system which comprises a main oil tank, an oil transportation tank, a fuel pump, an ejector pump and an oil exhaustion annunciator, wherein the main oil tank is communicated with the oil transportation tank through an oil return pipe, the ejector pump and the oil exhaustion annunciator are arranged in the oil transportation tank, the fuel pump is arranged in the main oil tank, the fuel pump is connected with the ejector pump through a first oil transportation pipeline, and the ejector pump is communicated with the main oil tank through a second oil transportation pipeline. Under the condition of limited space layout and cost limitation, the invention realizes the automatic control of the oil delivery sequence meeting the requirement of the gravity center change of the aircraft, simplifies the oil delivery system, reduces the cost and failure rate of the system and improves the reliability of the system.
Description
Technical Field
The invention relates to the technical field of aviation machinery control, in particular to an oil return type oil transportation control system.
Background
When the aircraft is designed, the automatic control of the oil transportation sequence is realized under the condition that the gravity center change requirement in the oil transportation process is met, and under the ground and various flight conditions and attitudes, the system for transferring the fuel of the fuel transportation tank to the fuel supply tank is called as an oil transportation system according to a certain sequence, and meanwhile, the requirement of the gravity center change of the aircraft in the oil transportation process can be met. The traditional oil delivery system generally comprises an oil delivery box, an oil delivery pump, an ejector pump, an oil level signal device, an oil delivery control valve and an oil delivery conduit. The traditional aircraft fuel oil transportation sequence control system is realized by means of the joint work of a fuel level signal device and an oil transportation control valve, and accessories such as the fuel level signal device, the oil transportation control valve and the like are respectively arranged for the fuel tank. However, for aircraft, this design increases the pipeline and finished products of the oil delivery system, increases the weight, cost and failure rate of the system, and reduces the reliability of the system. In addition, often due to the compact overall layout and complex structure of the aircraft, there is insufficient space to provide each tank with a separate set of oil control systems that work in combination with oil level annunciators and oil control valves.
Disclosure of Invention
In order to solve the problems, the invention provides an oil return type oil transportation control system, which realizes automatic control of oil transportation sequence meeting the gravity center change requirement of an airplane under the condition of limited space layout and cost limitation, simplifies the oil transportation system, reduces the cost and failure rate of the system and improves the reliability of the system.
The technical scheme adopted by the invention is as follows: the utility model provides an oil return formula oil transportation control system, includes main oil tank, fuel pump, ejector pump and oil annunciator, through back oil pipe intercommunication between main oil tank and the oil tank, be equipped with ejector pump and oil annunciator in the fuel tank, be equipped with the fuel pump in the main oil tank, the fuel pump is connected with the ejector pump through first oil pipeline, the ejector pump passes through second oil pipeline and communicates with main oil tank.
The main oil tank is divided into a front main oil tank and a rear main oil tank which are communicated through oil return holes, the front main oil tank is communicated with the oil delivery tank through an oil return pipe, one end of the oil return pipe extends into the front main oil tank, the position of the oil return hole is higher than a nozzle of the oil return pipe, the fuel pump is arranged in the rear main oil tank, and the rear main oil tank is connected with the injection pump through a second oil delivery pipeline.
A first one-way valve is further arranged between the front main oil tank and the rear main oil tank, and the bottom surface of the front main oil tank is higher than the bottom surface of the rear main oil tank. The first one-way valve is positioned below the oil return hole and close to the bottom of the front main oil tank, so that when the oil level of the rear main oil tank is lower than that of the first one-way valve, fuel in the front main oil tank can flow into the rear main oil tank for an engine.
The inlet of the second oil conveying pipeline into the rear main oil tank is provided with a second one-way valve, so that fuel in the rear main oil tank is prevented from flowing backwards into the oil conveying tank when the ejector pump does not work.
The fuel pump is connected with the engine through a third oil pipeline and is used for conveying fuel oil to the engine.
The beneficial effects of the invention are as follows: according to the invention, the oil return type oil transportation control system is adopted, so that the oil transportation sequence control is realized through the oil return hole in the main oil tank and the oil return pipe between the main oil tank and the oil transportation tank when the fuel oil of the oil transportation tank is conveyed to the main oil tank, the automatic oil transportation sequence control meeting the gravity center change requirement of an aircraft is realized under the condition of limited space layout and cost limitation, the oil transportation system is simplified, the cost and the failure rate of the system are reduced, and the reliability of the system is improved.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
in the figure, 1, an oil return pipe, 2, a front main oil tank, 3, an oil return hole, 4, a first one-way valve, 5, a fuel pump, 6, a rear main oil tank, 7, a second one-way valve, 8, an ejector pump, 9, an oil-out annunciator, 10, an oil tank, 11, a first oil pipeline, 12, a second oil pipeline, 13 and a third oil pipeline.
Detailed Description
The present invention will be further described in detail with reference to the following examples and drawings for the purpose of enhancing the understanding of the present invention, which examples are provided for the purpose of illustrating the present invention only and are not to be construed as limiting the scope of the present invention.
Example 1
The utility model provides an oil return formula oil transportation control system, including main oil tank, oil delivery case 10, fuel pump 5, ejector pump 8 and oil are done annunciator 9, main oil tank divide into preceding main oil tank 2 and back main oil tank 6 through the oil return hole 3 intercommunication, pass through the oil return pipe 1 intercommunication between preceding main oil tank 2 and the oil delivery case 10, in the one end of oil return pipe 1 extends to preceding main oil tank 2, the position of oil return hole 3 is higher than the nozzle of oil return pipe 1, be equipped with ejector pump 8 and oil in the oil delivery case 10 and done annunciator 9, be equipped with fuel pump 5 in the back main oil tank 6, fuel pump 5 is connected with ejector pump 8 through first oil pipeline 11, ejector pump 8 communicates with back main oil tank 6 through second oil pipeline 12.
The bottom surface of preceding main oil tank 2 is higher than the bottom surface of back main oil tank 6, still be equipped with first check valve 4 between preceding main oil tank 2 and the back main oil tank 6, first check valve 4 is located the below of oil gallery 3, be close to the bottom position of preceding main oil tank 2, design like this makes the fuel inflow of preceding main oil tank 2 back main oil tank 6 when the aircraft makes the dive motor fly, prevent back main oil tank 6 fuel refluence to preceding main oil tank 2 simultaneously, when guaranteeing that the oil level of back main oil tank is less than first check valve promptly, the fuel in the preceding main oil tank can all flow into in the back main oil tank and supply the engine to use.
The second check valve 7 is arranged at the inlet of the second oil delivery pipeline 12 into the rear main oil tank 6, so that the internal combustion oil in the rear main oil tank 6 is prevented from flowing backwards into the oil delivery tank 10 when the ejector pump does not work.
The fuel pump 5 is connected to the engine via a third fuel line 13 for supplying fuel to the engine.
The working principle is as follows:
the main oil tank is divided into a front main oil tank 2 and a rear main oil tank 6, and the fuel pump 5 is connected to start oil transportation.
(1) When the oil level of the front main oil tank 2 is higher than that of the nozzle of the oil return pipe 1, the fuel oil after the pressurization of the fuel pump 5 enters the injection pump 8 in the oil conveying tank 10, high-pressure jet flow is generated at the nozzle, so that a low-pressure area is formed in the nozzle cavity, the fuel oil in the oil conveying tank 10 is sucked into the nozzle cavity by the oil suction port, is injected to the rear main oil tank 6 through the jet pipe under the driving of the high-pressure jet flow, flows into the front main oil tank 2 through the oil return hole 3 between the rear main oil tank 6 and the front main oil tank 2, flows back to the oil conveying tank 10 through the oil return pipe 1, and at the moment, the fuel oil consumed by the engine is still the fuel oil in the main oil tank.
(2) When the oil surface of the front main oil tank 2 is flush with the orifice of the oil return pipe 1, the fuel in the fuel delivery tank 10 is ejected into the rear main oil tank 6 under the drive of high-pressure oil introduced from the fuel pump 5. At this time, the fuel consumed by the engine is the fuel in the fuel delivery box 10, until the fuel is exhausted, the fuel exhaustion annunciator 9 sends out a fuel exhaustion signal, and the second check valve 7 is further arranged at the inlet of the rear main fuel tank 6 where the second fuel delivery pipeline of the fuel delivery box 10 enters, so that the fuel in the rear main fuel tank 6 is prevented from flowing back into the fuel delivery box 10 when the ejector pump 8 does not work.
(3) When the fuel in the fuel delivery tank 10 is used up, the fuel in the main fuel tank is lower than the fuel return pipe 1, and the engine consumes the residual fuel in the main fuel tank until the fuel in the main fuel tank is used up, so that the automatic control of the aircraft fuel delivery sequence is realized.
In the oil return type oil transportation control system, in the oil transportation process of an aircraft, firstly, part of fuel in the main oil tank is transported, secondly, the fuel in the wing oil tank is transported through the jet pump and the oil return pipe, and the residual fuel in the main oil tank is transported again, so that the oil transportation sequence automatic control of the fuel in the oil tank in the aircraft is realized. And the oil transportation system is simplified, the cost and failure rate of the system are reduced, and the reliability of the system is improved.
Claims (4)
1. The oil return type oil transportation control system is characterized by comprising a main oil tank, an oil transportation tank, a fuel pump, an ejector pump and an oil exhaustion annunciator, wherein the main oil tank is communicated with the oil transportation tank through an oil return pipe, the ejector pump and the oil exhaustion annunciator are arranged in the oil transportation tank, the fuel pump is arranged in the main oil tank, the fuel pump is connected with the ejector pump through a first oil transportation pipeline, and the ejector pump is communicated with the main oil tank through a second oil transportation pipeline;
the main oil tank is divided into a front main oil tank and a rear main oil tank which are communicated through oil return holes, the front main oil tank is communicated with the oil delivery tank through an oil return pipe, one end of the oil return pipe extends into the front main oil tank, the position of the oil return hole is higher than a nozzle of the oil return pipe, the fuel pump is arranged in the rear main oil tank, and the rear main oil tank is connected with the injection pump through a second oil delivery pipeline;
the fuel pump is connected with the engine through a third oil pipeline.
2. The oil return type oil transportation control system according to claim 1, wherein a first check valve is further arranged between the front main oil tank and the rear main oil tank, and the first check valve is located below the oil return hole.
3. The oil return type oil transportation control system according to claim 1, wherein the inlet of the second oil transportation pipeline into the rear main oil tank is provided with a second one-way valve.
4. An oil return type oil delivery control system according to claim 1, wherein the bottom surface of the front main tank is higher than the bottom surface of the rear main tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811497078.3A CN109404135B (en) | 2018-12-07 | 2018-12-07 | Oil return type oil transportation control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811497078.3A CN109404135B (en) | 2018-12-07 | 2018-12-07 | Oil return type oil transportation control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109404135A CN109404135A (en) | 2019-03-01 |
| CN109404135B true CN109404135B (en) | 2023-12-26 |
Family
ID=65457943
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811497078.3A Active CN109404135B (en) | 2018-12-07 | 2018-12-07 | Oil return type oil transportation control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109404135B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123560A (en) * | 2021-03-25 | 2022-09-30 | 海鹰航空通用装备有限责任公司 | Anti-negative-overload oil tank of aircraft |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB735874A (en) * | 1952-05-20 | 1955-08-31 | Rolls Royce | Improvements relating to gas-turbine engine fuel systems |
| GB851428A (en) * | 1957-08-28 | 1960-10-19 | United Aircraft Corp | Fuel supply system for use in aircraft |
| SU927645A2 (en) * | 1976-04-05 | 1982-05-15 | Предприятие П/Я В-2481 | System for control of fuel consumption in aircraft |
| JP2009151987A (en) * | 2007-12-19 | 2009-07-09 | Toyota Motor Corp | Fluid distribution system and fuel cell system |
| CN101580130A (en) * | 2009-06-18 | 2009-11-18 | 北京航空航天大学 | Aircraft anti-icing fuel system suitable for high-altitude low temperature environment |
| CN101761394A (en) * | 2008-12-23 | 2010-06-30 | 江西洪都航空工业集团有限责任公司 | Negative overload resistant double-chamber oil supply device and method thereof |
| CN104627376A (en) * | 2014-12-04 | 2015-05-20 | 江西洪都航空工业集团有限责任公司 | Aircraft fuel oil conveying sequence control system |
| CN105000189A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Spilled oil recovery system for ventilation tank of large aircraft inverted dihedral wing fuel system |
| CN105092192A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Vibratory test method of airplane fuel tank |
| CN107128496A (en) * | 2017-04-19 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | One kind four sends out whirlpool oar aircraft fuel delivery system |
| CN209261679U (en) * | 2018-12-07 | 2019-08-16 | 江西洪都航空工业集团有限责任公司 | A kind of oil-return type oil transportation control system |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009137942A1 (en) * | 2008-05-16 | 2009-11-19 | Elisen Technologies Inc. | Auxiliary fuel tank system |
| JP6029421B2 (en) * | 2012-11-09 | 2016-11-24 | 三菱航空機株式会社 | Nitrogen-enriched gas supply system, aircraft |
| US20150151845A1 (en) * | 2013-12-02 | 2015-06-04 | Aero Systems Consultants LLC | Aircraft fuel systems |
| CN105620771A (en) * | 2014-10-28 | 2016-06-01 | 中国航空工业集团公司西安飞机设计研究所 | Fuel supply and delivery system for double-engine turboprop airplane |
| CN104943869B (en) * | 2015-06-23 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Ventilation tank residual fuel drainage system of reversed wing fuel system of large aircraft |
-
2018
- 2018-12-07 CN CN201811497078.3A patent/CN109404135B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB735874A (en) * | 1952-05-20 | 1955-08-31 | Rolls Royce | Improvements relating to gas-turbine engine fuel systems |
| GB851428A (en) * | 1957-08-28 | 1960-10-19 | United Aircraft Corp | Fuel supply system for use in aircraft |
| SU927645A2 (en) * | 1976-04-05 | 1982-05-15 | Предприятие П/Я В-2481 | System for control of fuel consumption in aircraft |
| JP2009151987A (en) * | 2007-12-19 | 2009-07-09 | Toyota Motor Corp | Fluid distribution system and fuel cell system |
| CN101761394A (en) * | 2008-12-23 | 2010-06-30 | 江西洪都航空工业集团有限责任公司 | Negative overload resistant double-chamber oil supply device and method thereof |
| CN101580130A (en) * | 2009-06-18 | 2009-11-18 | 北京航空航天大学 | Aircraft anti-icing fuel system suitable for high-altitude low temperature environment |
| CN105092192A (en) * | 2014-05-07 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Vibratory test method of airplane fuel tank |
| CN104627376A (en) * | 2014-12-04 | 2015-05-20 | 江西洪都航空工业集团有限责任公司 | Aircraft fuel oil conveying sequence control system |
| CN105000189A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Spilled oil recovery system for ventilation tank of large aircraft inverted dihedral wing fuel system |
| CN107128496A (en) * | 2017-04-19 | 2017-09-05 | 中国航空工业集团公司西安飞机设计研究所 | One kind four sends out whirlpool oar aircraft fuel delivery system |
| CN209261679U (en) * | 2018-12-07 | 2019-08-16 | 江西洪都航空工业集团有限责任公司 | A kind of oil-return type oil transportation control system |
Non-Patent Citations (5)
| Title |
|---|
| 先进飞机中燃油系统的综合化控制与管理;张娟;;航空计算技术(第02期);全文 * |
| 外热源作用下机翼油箱边界温度变化规律研究;童升华;邵垒;古远康;冯诗愚;刘卫华;;航空兵器(第01期);第48-52页 * |
| 飞机液动离心泵对燃油系统耗油顺序影响的研究分析;赵鲁宁;孙颖;王伟龙;;飞机设计(第01期);全文 * |
| 飞机燃油引射供输油系统动流源研制;闫炜;马柯;;液压与气动(第06期);第14-16页 * |
| 飞机燃油系统仿真方法;廖凌燕;;系统仿真学报(第S1期);第56-59页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109404135A (en) | 2019-03-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6907899B2 (en) | Saddle tank fuel delivery system | |
| US2332007A (en) | Sump selector valve for fuel tanks | |
| CN100381691C (en) | Common rail type fuel injection system | |
| CN109404135B (en) | Oil return type oil transportation control system | |
| CN104648681B (en) | High-reliability fuel supplying and conveying system with gravity center adjusting capability | |
| CN1914416B (en) | Coupling valve structure for fuel supply module | |
| CN207018120U (en) | The low tension loop of fuel feed system and fuel feed system | |
| KR20130121024A (en) | A fuel feed network for a rotorcraft engine, the network including means for priming a pump for sucking fuel from a feeder tank | |
| CN207178075U (en) | A kind of oil pump oil circuit and diesel car | |
| CN209261679U (en) | A kind of oil-return type oil transportation control system | |
| CN107128496B (en) | Four-engine turboprop aircraft oil supply and delivery system | |
| KR100957010B1 (en) | Fuel feed module system of the saddle type fuel tank | |
| CN218703931U (en) | Pressure oiling system and aircraft | |
| EP3077290B1 (en) | Bubble collector for suction fuel system | |
| KR100916950B1 (en) | Dual jet nozzle of fuel pump module made up combinational structure | |
| CN207033628U (en) | Single cylinder diesel electronic controlled fuel pump enters oil outlet one-way valve | |
| JPS63227949A (en) | Fuel supply device for vehicle | |
| CN109653874A (en) | A kind of motor oil oil supply system | |
| CN219257689U (en) | Unmanned aerial vehicle high reliability oil transportation system | |
| CN104986343A (en) | Oil supplying and conveying system in oil tank | |
| CN204750577U (en) | Aircraft bellytank draws penetrates oil transportation device | |
| CN104712473B (en) | Fuel service system and corresponding automobile | |
| CN105000189A (en) | Spilled oil recovery system for ventilation tank of large aircraft inverted dihedral wing fuel system | |
| EP0934449B1 (en) | Aircraft fuel transfer pump with auxiliary fuel line scavenge pump | |
| CN116331499A (en) | Unmanned aerial vehicle high reliability oil transportation system |
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 |