CN105620771A - Fuel supply and delivery system for double-engine turboprop airplane - Google Patents
Fuel supply and delivery system for double-engine turboprop airplane Download PDFInfo
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- CN105620771A CN105620771A CN201410587394.5A CN201410587394A CN105620771A CN 105620771 A CN105620771 A CN 105620771A CN 201410587394 A CN201410587394 A CN 201410587394A CN 105620771 A CN105620771 A CN 105620771A
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Abstract
The invention relates to an airplane fuel supply and delivery system, in particular to a fuel supply and delivery system suitable for a double-engine turboprop airplane. A fuel tank is of a left-right symmetric integrated structure. Fuel delivery pumps (2) are arranged in a left transfer fuel tank (5) and a right transfer fuel tank (5), so that dynamic flow is provided for jet pumps (3), and fuel transfer is achieved. Meanwhile, the fuel delivery pumps on the two sides are connected through a pipeline and isolated through a fuel delivery isolating valve (8). When the fuel delivery pump on one side fails, the isolating valve is opened so that the fuel delivery pump on the single side can provide the dynamic flow to the jet pumps of the fuel tanks on the two sides, fuel transfer of the fuel tanks on the two sides can be achieved, and fuel supply of engines is guaranteed. In addition, a fuel tank communicating pipeline (9) is arranged and used for balancing fuel unbalance caused by single-pump fuel delivery. The independence of the fuel tanks on the two sides can be guaranteed by closing a balancing isolating valve (7) on the fuel tank communicating pipeline. By the adoption of the scheme, on the basis that the fuel supply and delivery requirement of the double-engine turboprop airplane is met, the fuel supply and delivery system has the beneficial effects of being high in reliability, low in weight and cost and the like.
Description
Technical field
The present invention relates to a kind of aircraft fuel delivery system, particularly to a kind of being applicable to double; two send out whirlpool oar aircrafts, fuel tank be the fuel delivery system of symmetrical overall structure fuel tank.
Background technology
The topmost function of fuel system is under all service conditions of aircraft, by the parameter of engine calls constantly to its fuel feeding. In order to ensure oil supply performance, it is necessary to fuel oil transfers subsystem and constantly from transferring fuel tank, fuel oil transported to oil sump tank. The current commonly used oil feed pump of airplane in transportation category fuel delivery system provides the dynamic stream of injection thus realizing fuel oil and transferring for jet pump, for double; two whirlpool oar aircrafts, owing to engine inlet pressure is relatively low, cause that oil feed pump cannot provide enough pressure to jet pump, it is impossible to adopt this kind of fuel delivery system scheme. Transferred and the function that dewaters accordingly, it would be desirable to one both can meet fuel oil, there is the fuel delivery system scheme of high reliability, lighter weight, lower cost simultaneously.
Summary of the invention
A kind of double; two fuel delivery system sending out whirlpool oar aircrafts, fuel tank, based on the commonly used integral tank of airplane in transportation category, is carried out fuel tank division according to typical fuel system design scheme by the design of this fuel delivery system. Including oil feed pump 1, oil transfer pump 2, jet pump 3, oil sump tank 4, transfer fuel tank 5, the fuel feeding defeated valve 6 of friendship, oil feed pump 1 is arranged in oil sump tank 4, oil transfer pump 2 and jet pump 3 are arranged on and transfer in fuel tank 5, it is characterized by: described aircraft fuel delivery system also includes balance isolating valve 7, oil transportation isolating valve 8, balance connecting pipeline 9 and oil transportation connecting pipeline 10;
Oil feed pump 1 in oil sump tank 4 is connected with respective electromotor by pipeline, is linked together by the oil feed line of both sides, is provided with fuel feeding and hands over defeated valve 6 between the oil feed line of both sides;
The entrance of oil transfer pump 2 and jet pump 3 is linked together by pipeline road, and both sides oil transfer pump 2 is connected by oil transportation connecting pipeline 10, is provided with oil transportation isolating valve 8 on oil transportation connecting pipeline 10;
Both sides are transferred fuel tank 5 and are connected by balancing connecting pipeline 9, are provided with balance isolating valve 7 on balance connecting pipeline 9.
The advantageous effect of this invention:
This invention can meet double; two whirlpool oar aircraft of sending out for oil transportation and the requirement that dewaters, the program is ensureing that achieving fuel transfer system on the basis for oil transportation reliability simplifies simultaneously, effectively reduce fuel system weight and cost, be suitable on the whirlpool oar aircraft of weight sensitive and cost sensitivity and apply.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present invention. Wherein: oil feed pump 1; Oil transfer pump 2; Jet pump 3; Oil sump tank 4; Transfer fuel tank 5; Fuel feeding hands over defeated valve 6; Balance isolating valve 7; Oil transportation isolating valve 8; Balance connecting pipeline 9; Oil transportation connecting pipeline 10.
Detailed description of the invention
The detailed description of the invention that should invent is described in conjunction with invention diagram. Such as Fig. 1, this invention is to be respectively provided with oil transfer pump 2 in fuel tank 5 provide dynamic stream to realize fuel oil for jet pump 3 to transfer left and right transferring, simultaneously, the oil transfer pump of both sides is connected by pipeline and isolates with oil transportation isolating valve 8, when side oil transfer pump lost efficacy, open isolating valve to realize unilateral oil transfer pump and provide dynamic stream to realize bilateral oil tank fuel to both sides fuel tank jet pump to transfer, make oil sump tank 4 intermediate fuel oil keep high pasta, it is ensured that engine oil. In addition, arrange one and transfer the fuel oil imbalance that fuel tank connecting pipeline 9 causes for balancing single pump oil transportation, this pipeline can pass through to close balance isolating valve 7 ensure the independence of both sides fuel tank, and only carries out fuel balance to transferring fuel tank, it is to avoid the generation of full machine fuel leakage. This fuel delivery system has the feature that
Oil feed pump 1 in oil sump tank 4 is connected with respective electromotor by pipeline, is linked together by the oil feed line of both sides, is provided with fuel feeding and hands over defeated valve 6 between the oil feed line of both sides; Under normal circumstances, both sides oil sump tank 4 to corresponding engine oil by respective oil feed pump 1, when side oil feed pump 1 or engine failure, can be opened fuel feeding and hand over defeated valve 6 to realize unilateral oil sump tank 4 to double; two fuel feeding or both sides oil sump tank 4 to single-shot fuel feeding;
The entrance of oil transfer pump and jet pump 3 is linked together by pipeline road, and both sides oil transfer pump 2 is connected by oil transportation connecting pipeline 10, is provided with oil transportation isolating valve 8 on oil transportation connecting pipeline 10; Under normal circumstances, the oil transfer pump 2 that both sides are transferred in fuel tank 5 provides injection dynamic stream to respective jet pump 3, thus fuel oil is delivered to oil sump tank 4 by transferring fuel tank 5; When side oil transfer pump 2 fault, open the oil transportation isolating valve 8 on oil transportation connecting pipeline 10, the oil transfer pump 2 of opposite side providing injection dynamic stream for both sides jet pump 3, transferring thus realizing fuel oil;
Both sides are transferred fuel tank 5 and are connected by balancing connecting pipeline 9, are provided with balance isolating valve 7 on balance connecting pipeline 9. There is provided injection to move in the process of stream at unilateral oil transfer pump 2 for both sides jet pump 3, both sides can be caused to transfer fuel tank 5 fuel oil uneven, it is possible to by opening balance isolating valve 7, it is achieved the fuel balance of fuel tank 5 is transferred in both sides.
The detailed description of the invention that should invent is described in conjunction with invention diagram. Such as Fig. 1, this invention is to be respectively provided with oil transfer pump 2 in fuel tank 5 provide dynamic stream to realize fuel oil for jet pump 3 to transfer left and right transferring, simultaneously, the oil transfer pump of both sides is connected by pipeline and isolates with oil transportation isolating valve 8, when side oil transfer pump lost efficacy, open isolating valve to realize unilateral oil transfer pump and provide dynamic stream to realize bilateral oil tank fuel to both sides fuel tank jet pump to transfer, make oil sump tank 4 intermediate fuel oil keep high pasta, it is ensured that engine oil. In addition, arrange one and transfer the fuel oil imbalance that fuel tank connecting pipeline 9 causes for balancing single pump oil transportation, this pipeline can pass through to close balance isolating valve 7 ensure the independence of both sides fuel tank, and only carries out fuel balance to transferring fuel tank, it is to avoid the generation of full machine fuel leakage.
The program, meeting on the whirlpool oar aircraft engine basis for oil transportation requirement, has the advantages such as high reliability, lighter weight and relatively low cost simultaneously.
Claims (2)
1. double; two whirlpool oar aircraft fuel delivery systems, including oil feed pump (1), oil transfer pump (2), jet pump (3), oil sump tank (4), transfer fuel tank (5), the fuel feeding defeated valve of friendship (6), oil feed pump (1) is arranged in oil sump tank (4), oil transfer pump (2) and jet pump (3) are arranged on and transfer in fuel tank (5), it is characterized by: described aircraft fuel delivery system also includes balance isolating valve (7), oil transportation isolating valve (8), balance connecting pipeline (9) and oil transportation connecting pipeline (10);
Oil feed pump (1) in oil sump tank (4) is connected with respective electromotor by pipeline, is linked together by the oil feed line of both sides, is provided with fuel feeding and hands over defeated valve (6) between the oil feed line of both sides;
The entrance of oil transfer pump (2) and jet pump (3) is linked together by pipeline road, both sides oil transfer pump (2) is connected by oil transportation connecting pipeline (10), is provided with oil transportation isolating valve (8) on oil transportation connecting pipeline (10).
2. double; two whirlpool oar aircraft fuel delivery systems according to claim 1, it is characterized by: fuel tank (5) is transferred by balancing connecting pipeline (9) connection in both sides, is provided with balance isolating valve (7) in balance connecting pipeline (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410587394.5A CN105620771A (en) | 2014-10-28 | 2014-10-28 | Fuel supply and delivery system for double-engine turboprop airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410587394.5A CN105620771A (en) | 2014-10-28 | 2014-10-28 | Fuel supply and delivery system for double-engine turboprop airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620771A true CN105620771A (en) | 2016-06-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410587394.5A Pending CN105620771A (en) | 2014-10-28 | 2014-10-28 | Fuel supply and delivery system for double-engine turboprop airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN105620771A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697308A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Fuel oil transferring method for large airplane |
| 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 |
| CN107963227A (en) * | 2017-11-08 | 2018-04-27 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of double hair helicopter fuel system display control panels |
| CN109404135A (en) * | 2018-12-07 | 2019-03-01 | 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2086184A1 (en) * | 1970-04-20 | 1971-12-31 | Gen Electric | |
| US3669136A (en) * | 1969-03-25 | 1972-06-13 | Siai Marchetti Spa | Fuel delivery system for a plurality of aircraft engines |
| US4913380A (en) * | 1988-10-13 | 1990-04-03 | Omac, Inc. | Fuel system for Canard aircraft |
| CN203889073U (en) * | 2014-05-07 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Aircraft auxiliary fuel tank device transmitting fuel by virtue of injection |
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2014
- 2014-10-28 CN CN201410587394.5A patent/CN105620771A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3669136A (en) * | 1969-03-25 | 1972-06-13 | Siai Marchetti Spa | Fuel delivery system for a plurality of aircraft engines |
| FR2086184A1 (en) * | 1970-04-20 | 1971-12-31 | Gen Electric | |
| US4913380A (en) * | 1988-10-13 | 1990-04-03 | Omac, Inc. | Fuel system for Canard aircraft |
| CN203889073U (en) * | 2014-05-07 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Aircraft auxiliary fuel tank device transmitting fuel by virtue of injection |
Non-Patent Citations (1)
| Title |
|---|
| 曹连华等: "战斗机燃油系统流体网络的数值计算", 《飞机设计》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106697308A (en) * | 2016-12-15 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Fuel oil transferring method for large airplane |
| 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 |
| CN107128496B (en) * | 2017-04-19 | 2021-07-09 | 中国航空工业集团公司西安飞机设计研究所 | Four-engine turboprop aircraft oil supply and delivery system |
| CN107963227A (en) * | 2017-11-08 | 2018-04-27 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of double hair helicopter fuel system display control panels |
| CN109404135A (en) * | 2018-12-07 | 2019-03-01 | 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 |
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Application publication date: 20160601 |