CN104564699A - Aviation fuel pump with ejecting supercharging device - Google Patents
Aviation fuel pump with ejecting supercharging device Download PDFInfo
- Publication number
- CN104564699A CN104564699A CN201410737562.4A CN201410737562A CN104564699A CN 104564699 A CN104564699 A CN 104564699A CN 201410737562 A CN201410737562 A CN 201410737562A CN 104564699 A CN104564699 A CN 104564699A
- Authority
- CN
- China
- Prior art keywords
- fuel pump
- fuel
- inducer
- spiral case
- supercharging device
- 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.)
- Pending
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D13/00—Pumping installations or systems
- F04D13/02—Units comprising pumps and their driving means
- F04D13/06—Units comprising pumps and their driving means the pump being electrically driven
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/669—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for liquid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/02—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being liquid
- F04F5/10—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being liquid displacing liquids, e.g. containing solids, or liquids and elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04F—PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BY USING INERTIA OF FLUID TO BE PUMPED; SIPHONS
- F04F5/00—Jet pumps, i.e. devices in which flow is induced by pressure drop caused by velocity of another fluid flow
- F04F5/54—Installations characterised by use of jet pumps, e.g. combinations of two or more jet pumps of different type
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides an aviation fuel pump with high cavitation resistance, and in particular provides a fuel pump with a novel structure. The aviation fuel pump comprises an inducer, an impeller, a volute, a motor, an inlet pipeline and an ejecting supercharging device. When the product works, the motor drives the inducer and the impeller to rotate by a transmission shaft, under the action of a centrifugal force of the blade, the fuel is supercharged and accelerated by the inducer and the impeller from an inlet and then flows into the volute, a part of high pressure fuel flows through an ejecting pipeline through drainage holes in the volute and then flows out from a nozzle in order to supercharge the fuel in the inlet pipeline, and therefore the fuel pump has high cavitation resistance.
Description
Technical field
The invention belongs to Aviation Fuel system, relate to a kind of aero fuel pump with injection supercharging device.
Background technique
Aero fuel pump with injection supercharging device is mainly used in aircraft fuel system, for oily to carrying out transmission after fuel pressurization.The domestic fuel pump product being arranged on fuel tank sidewall at present, because there is the longer device such as fuel oil suction port pipeline, the self-styled valve of entrance, flow resistance is comparatively large, so fuel pump anti-cavitation performance is poor.The maximum use height of general such fuel pump is about 8 kms, and general military aircraft ceiling altitude is many at 16 ~ 20 kms.Under fuel tank system adopts boost conditions (supercharging value is generally 20kPa), the maximum use of fuel pump is highly also about 14 kms.
Summary of the invention
The object of this national defence patent: this aero fuel pump is provided with injection supercharging device, maximum use height can reach about 16 kms, under fuel tank system adopts boost conditions (supercharging value is generally 20kPa), the maximum use of fuel pump highly can reach more than 20 kms.The requirement of army's civil aircraft oil-fired system for oil transportation can be met, expand the using scope of the type fuel pump.
Technological scheme of the present invention: a kind of aero fuel pump with injection supercharging device, motor 8 is fixed by fastening piece and spiral case end flanges, and electric coupler 7 is arranged on the right-hand member top of motor 8; Be provided with inducer 10, impeller 9 in spiral case 6, the outlet end of spiral case 6 is provided with conduction hole 5; Injection pipeline 3 is communicated with the conduction hole 5 of spiral case 6 by fastening piece; Nozzle 2 is welded on injection pipeline 3 end, and nozzle 2 is arranged on mixing section 4 center line; Mixing section 4 is connected with spiral case 6 by fastening piece; The interference of entrance self-styled valve 1 is connected on mixing section 4, and is arranged on inducer 10 front end.
Beneficial effect of the present invention: a kind of aero fuel pump with injection supercharging device of the present invention's design.Product electric coupler 7 is energized, and motor 8 drives inducer 10, impeller 9 rotates, to fuel pressurization; Most of fuel medium wherein after supercharging is delivered to oil-fired system pipeline by spiral case 6; Part fuel medium is flowed out at a high speed from nozzle 2 by conduction hole 5, the fuel oil in suction mixing section 4, and mixes supercharging in mixing section 4, improves the fuel pressure before fuel pump inducer 10, thus improves the anti-cavitation ability of fuel pump.
The maximum use height of a kind of aero fuel pump with injection supercharging device of the present invention's design can reach about 16 kms, under fuel tank system adopts boost conditions (supercharging value is generally 20kPa), the maximum use of fuel pump highly can reach more than 20 kms.And the maximum use height of the fuel pump of same kind is about 8 kms, under fuel tank system adopts boost conditions (supercharging value is generally 20kPa), the maximum use height of fuel pump is about 14 kms.
This invention expands the use height restriction scope of the type fuel pump.
Accompanying drawing illustrates:
Fig. 1 is structural representation of the present invention.
Fig. 2 is fundamental diagram of the present invention.Arrow represents that fuel medium flows through route.
Fuel pump is by the self-styled valve of 1-entrance, 2-nozzle, 3-injection pipeline, 4-mixing section, 5-draining hole, 6-spiral case, 7-electric coupler, 8-motor, 9-impeller, 10-inducer.
Embodiment
Below by embodiment, the present invention is described in further detail.Refer to Fig. 1 and Fig. 2.
As shown in Figure 1, a kind of aero fuel pump with injection supercharging device, motor 8 is fixed by fastening piece and spiral case end flanges, and electric coupler 7 is arranged on the right-hand member top of motor 8; Be provided with inducer 10, impeller 9 in spiral case 6, the outlet end of spiral case 6 is provided with conduction hole 5; Injection pipeline 3 is communicated with the conduction hole 5 of spiral case 6 by fastening piece; Nozzle 2 is welded on injection pipeline 3 end, and nozzle 2 is arranged on mixing section 4 center line; Mixing section 4 is connected with spiral case 6 by fastening piece; The interference of entrance self-styled valve 1 is connected on mixing section 4, and is arranged on inducer 10 front end.
As shown in Figure 2 (arrow represents that fuel medium flows through route), during work, electric coupler 7 is energized, and motor 8 drives inducer 10, impeller 9 rotates, to fuel pressurization; Most of fuel medium wherein after supercharging is delivered to oil-fired system pipeline by spiral case 6; Part fuel medium is flowed out at a high speed from nozzle 2 by conduction hole 5, the fuel oil in suction mixing section 4, and mixes supercharging in mixing section 4, improves the fuel pressure before fuel pump inducer 10, thus improves the anti-cavitation ability of fuel pump.
Claims (1)
1. the aero fuel pump with injection supercharging device, described injection supercharging device comprises conduction hole (5), injection pipeline (3), nozzle (2), mixing section (4); It is characterized in that, motor (8) is fixed by fastening piece and spiral case end flanges, and electric coupler (7) is arranged on the right-hand member top of motor (8); Be provided with inducer (10), impeller (9) in spiral case (6), the outlet end of spiral case (6) is provided with conduction hole (5); Injection pipeline (3) is communicated with the conduction hole (5) of spiral case (6) by fastening piece; Nozzle (2) is welded on injection pipeline (3) end, and nozzle (2) is arranged on the center line in mixing section (4); Mixing section (4) is connected with spiral case (6) by fastening piece; The self-styled valve of entrance (1) interference is connected on mixing section (4), and is arranged on inducer (10) front end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410737562.4A CN104564699A (en) | 2014-12-05 | 2014-12-05 | Aviation fuel pump with ejecting supercharging device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410737562.4A CN104564699A (en) | 2014-12-05 | 2014-12-05 | Aviation fuel pump with ejecting supercharging device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104564699A true CN104564699A (en) | 2015-04-29 |
Family
ID=53081551
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410737562.4A Pending CN104564699A (en) | 2014-12-05 | 2014-12-05 | Aviation fuel pump with ejecting supercharging device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104564699A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567866A (en) * | 2016-11-04 | 2017-04-19 | 西安航空动力控制科技有限公司 | Fuel oil thrust augmentation centrifugal pump resistant to caviation |
| CN109596302A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flow control ejection system of dummy vehicle low-speed wind tunnel experiment |
| CN110469542A (en) * | 2019-08-16 | 2019-11-19 | 中国航发北京航科发动机控制系统科技有限公司 | A kind of fuel inlet device improving centrifugal pump suction capacity |
| CN112610536A (en) * | 2020-12-11 | 2021-04-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Anti cavitation structure of fuel pump |
| CN113107731A (en) * | 2021-04-27 | 2021-07-13 | 中国舰船研究设计中心 | Fuel oil and lubricating oil dual-fuel lightering pump set device for ship |
| CN114278612A (en) * | 2021-12-28 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Skin installation fuel pump with dismouting is from seal structure |
| CN114483602A (en) * | 2021-12-28 | 2022-05-13 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Braking structure of rotary plate valve of fuel pump |
| CN114962282A (en) * | 2022-03-29 | 2022-08-30 | 哈尔滨工程大学 | Multifunctional centrifugal pump suction inlet pressurization test device and test method |
-
2014
- 2014-12-05 CN CN201410737562.4A patent/CN104564699A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567866A (en) * | 2016-11-04 | 2017-04-19 | 西安航空动力控制科技有限公司 | Fuel oil thrust augmentation centrifugal pump resistant to caviation |
| CN106567866B (en) * | 2016-11-04 | 2018-11-16 | 西安航空动力控制科技有限公司 | A kind of fuel oil reinforcing centrifugal pump of anti-cavitation |
| CN109596302A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flow control ejection system of dummy vehicle low-speed wind tunnel experiment |
| CN109596302B (en) * | 2018-11-02 | 2021-08-03 | 中国航空工业集团公司西安飞机设计研究所 | Flow control injection system for low-speed wind tunnel experiment of aircraft model |
| CN110469542A (en) * | 2019-08-16 | 2019-11-19 | 中国航发北京航科发动机控制系统科技有限公司 | A kind of fuel inlet device improving centrifugal pump suction capacity |
| CN112610536A (en) * | 2020-12-11 | 2021-04-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Anti cavitation structure of fuel pump |
| CN112610536B (en) * | 2020-12-11 | 2023-05-30 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Anti cavitation structure of fuel pump |
| CN113107731A (en) * | 2021-04-27 | 2021-07-13 | 中国舰船研究设计中心 | Fuel oil and lubricating oil dual-fuel lightering pump set device for ship |
| CN114278612A (en) * | 2021-12-28 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Skin installation fuel pump with dismouting is from seal structure |
| CN114483602A (en) * | 2021-12-28 | 2022-05-13 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Braking structure of rotary plate valve of fuel pump |
| CN114483602B (en) * | 2021-12-28 | 2023-12-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Braking structure of fuel pump rotary plate valve |
| CN114962282A (en) * | 2022-03-29 | 2022-08-30 | 哈尔滨工程大学 | Multifunctional centrifugal pump suction inlet pressurization test device and test method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150429 |
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| WD01 | Invention patent application deemed withdrawn after publication |