CN206398761U - Improve the fuel nozzle of fuel feeding scope - Google Patents
Improve the fuel nozzle of fuel feeding scope Download PDFInfo
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- CN206398761U CN206398761U CN201621375928.9U CN201621375928U CN206398761U CN 206398761 U CN206398761 U CN 206398761U CN 201621375928 U CN201621375928 U CN 201621375928U CN 206398761 U CN206398761 U CN 206398761U
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- bicyclic
- spinning disk
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Abstract
The utility model is to be related to a kind of fuel nozzle for improving fuel feeding scope, including center nozzle, for bicyclic chamber multi-port centrifuging temperature form of nozzle, including fuel inlet fitting, spinning disk, bicyclic chamber shower nozzle, fuel inlet fitting (1), spinning disk (2), bicyclic chamber shower nozzle (3) assembled in series constitutes fuel nozzle, it is characterized in that, there is an oil duct (5) inside fuel inlet fitting (1), aperture (9) is disposed with spinning disk (2), tangential small-hole (15) and tangential slot (14), bicyclic chamber shower nozzle (3) is divided into ring cavity (7) and (8) two chambers of cavity, cavity (10) is formed between spinning disk (2) and bicyclic chamber shower nozzle (3), oil duct (5) is connected by aperture (9) with cavity (10), oil duct (5) is connected by tangential small-hole (15) with cavity (8), there is a passage (11) to communicate between ring cavity (7) and cavity (8), cavity (8) is connected with center nozzle (13), ring cavity (7) has multiple spouts (12).
Description
Technical field
The utility model belongs to aero-engine field, is related to a kind of fuel nozzle for improving fuel feeding scope.
Background technology
Fuel nozzle is the important component in aero-engine main chamber, and its major function is, by fuel-oil atmozation, to spray into
Blend and burn with air in combustion chamber.With the expansion of aero-engine flight envelope, fuel flow scope is also increasingly broader,
Therefore modern aeroengine main chamber fuel nozzle is typically designed as double oil circuits to meet the fuel flow scope of broadness.At present
Aero-engine typically uses the double spout centrifuging temperature nozzle arrangements forms of two-way, but double oil way fuel spray nozzles are generally required
Major and minor two fuel inlet fittings, and two-way fuel manifold is equipped with, not only bring weight and cost increase, and fuel control
It is very cumbersome.Therefore, the structure of nozzle tape side valve is employed in some aero-engines, to reduce fuel manifold all the way,
The design that a fuel inlet fitting is divided into two strands of oil circuits is realized by side valve, but side valve also brings valve processing, adjusted
Examination is difficult, the shortcomings of manufacturing cycle is long, and valve job stability is poor, therefore more aero-engine still employs double oil
Road fuel nozzle structure type.
The content of the invention
The purpose of this utility model：A kind of fuel nozzle for improving fuel feeding scope is provided, while atomization quality is ensured
Improve the fuel feeding scope of fuel nozzle.
The technical solution of the utility model is：
On the basis of traditional single oil circuit rotarytype injector structure, the scheme of bicyclic chamber is used in nozzle head, by fuel oil
Naturally two strands of oil circuits are split into.When aero-engine is operated in small operating mode, fuel feed pressure is smaller, due to the second road runner
Loss is much larger than the first via, and most of fuel oil will flow through from the first via, and is sprayed from center nozzle, forms good atomization.When
When aero-engine is operated in big operating mode, fuel feed pressure is larger, and two oil circuits have great amount of fuel oil.Due to there is two-way combustion
Oil is sprayed, and the more traditional single oil circuit swirl atomizer of its range of flow is greatly improved.
Technical scheme：A kind of fuel nozzle for improving fuel feeding scope, including center nozzle, are that bicyclic chamber multi-port is centrifugal
Fuel nozzle form, including fuel inlet fitting, spinning disk, bicyclic chamber shower nozzle, fuel inlet fitting, spinning disk, bicyclic chamber shower nozzle series connection dress
With composition fuel nozzle, have inside fuel inlet fitting and aperture, tangential small-hole and tangential slot are disposed with an oil duct, spinning disk, it is bicyclic
Chamber shower nozzle is divided into ring cavity and two chambers of cavity, forms cavity between spinning disk and bicyclic chamber shower nozzle, oil duct passes through aperture and cavity
Connection, oil duct is connected by tangential small-hole with cavity, has a passage to communicate between ring cavity and cavity, cavity and center nozzle phase
Even, ring cavity has multiple spouts.
Further, the angle of multiple tangential small-holes, tangential small-hole and nozzle centerline is disposed with spinning disk intermediate region
Spend for 20 ° -- 70 °.
Further, channel width is 0.1mm--0.3mm.
Further, spout is circumferentially evenly arranged on ring cavity, and quantity is 4--12.
Spin chamber in shower nozzle divide into inside and outside two ring cavities by the structure type, at low pressures, and fuel oil is mainly therefrom
Heart spout sprays, at elevated pressures, and fuel oil sprays from the multiple apertures of center nozzle and outside simultaneously, is improving fuel feed scope
While, take into account the atomization quality that ensure that under low-pressure.
Beneficial effect：The burner scheme only one of which fuel inlet fitting, it is simple in construction, in traditional single oil circuit rotarytype injector knot
On the basis of structure, using the design of bicyclic chamber rotarytype injector, fuel nozzle is divided into Liang Ge spin chambers, fuel oil is split into two strands
Fuel oil, improves fuel supply flow rate scope.Predominantly center oil circuit work under low-pressure simultaneously, due to centrifugal action ensure that it is low
Good atomization under pressure.
Brief description of the drawings
Fig. 1 is the fuel nozzle schematic diagram that the utility model improves fuel feeding scope
Fig. 2 is spinning disk structural representation
1- fuel inlet fittings, 2- spinning disks, the bicyclic chamber shower nozzles of 3-, 4- nozzle oil inlets, 5- oil ducts, 7- ring cavities, 8- cavitys, 9-
Aperture, 10- cavities, 11- passages, 12- spouts, 13- center nozzles, 14- tangential slots, 15- tangential small-holes, 16- walls, 17- spiral shells
Line, 18- nozzle centerlines
Embodiment
Below in conjunction with the accompanying drawings and the utility model is discussed in detail in specific embodiment.
It is a kind of fuel nozzle for improving fuel feeding scope, it is characterised in that including center nozzle 13, be refering to Fig. 1, Fig. 2
Bicyclic chamber multi-port centrifuging temperature form of nozzle, including fuel inlet fitting 1, spinning disk 2, bicyclic chamber shower nozzle 3, fuel inlet fitting 1, rotation
Have inside flow 2, the bicyclic assembled in series of chamber shower nozzle 3 composition fuel nozzle, fuel inlet fitting 1 and be disposed with an oil duct 5, spinning disk 2
Aperture 9, tangential small-hole 15 and tangential slot 14, bicyclic 3 points of chamber shower nozzle is ring cavity 7 and 8 two chambers of cavity, spinning disk 2 and bicyclic chamber
Cavity 10 is formed between shower nozzle 3, oil duct 5 is connected by aperture 9 with cavity 10, and oil duct 5 is connected by tangential small-hole 15 with cavity 8
It is logical, there is a passage 11 to communicate between ring cavity 7 and cavity 8, cavity 8 is connected with center nozzle 13, ring cavity 7 there are multiple spouts 12.
Further, multiple tangential small-holes 15, tangential small-hole 15 and nozzle centerline are disposed with the intermediate region of spinning disk 2
18 angle is 20 ° -- 70 °.
Further, the width of passage 11 is 0.1mm--0.3mm.
Further, spout 12 is circumferentially evenly arranged on ring cavity 7, and quantity is 4--12.
When fuel nozzle works, fuel oil flows into oil duct 5 from nozzle oil inlet 4.Then two oil circuits are split into.The first via
Cavity 8 is flowed into by tangential small-hole 15, secondary route aperture 9 flows into cavity 10, then flows into ring cavity 7 by tangential slot 14.
When aero-engine is operated in small operating mode, fuel feed pressure is smaller, because the second road passages losses are much larger than
The first via, most of fuel oil will be flowed through from the first via, and cavity 8 is flowed into from tangential small-hole 15, because the effect of centrifugal force forms rotation
Shape is flowed, and with velocity component forward, is sprayed from center nozzle 13, good atomization is formed.Fraction fuel oil is from the second tunnel
Flow through, when by tangential slot 14, the loss of its oil circuit is larger, and charge oil pressure is relatively low, and the centrifugal force of generation is weaker, it is impossible to be close to wall
Face 16 forms eddy flow, mainly will flow into cavity 8 from passage 11, and converges with first via fuel oil, and is sprayed from center nozzle 13.By
Spray, its actual orifice size is smaller, also ensure that at low pressures good from center nozzle 13 in most of fuel oil
Atomization.
When aero-engine is operated in big operating mode, fuel feed pressure is larger, and two oil circuits have great amount of fuel oil, the
Fuel oil flows into cavity 8 from tangential small-hole 15 all the way, because the effect of centrifugal force forms eddy flow shape, and is sprayed from center nozzle 13,
Form good atomization.Second road fuel oil flows through from the second tunnel, by tangential slot 14, produces larger centrifugal force, is close to wall 16
Eddy flow is formed, ring cavity 7 is flowed through and is sprayed from multiple spouts 12.Due to having the ejection of two-way fuel oil, the more traditional single oil of its range of flow
Road swirl atomizer is greatly improved.
Claims (4)
1. a kind of fuel nozzle for improving fuel feeding scope, including center nozzle (13), are bicyclic chamber multi-port centrifuging temperature spray
Mouth form, including fuel inlet fitting (1), spinning disk (2), bicyclic chamber shower nozzle (3), fuel inlet fitting (1), spinning disk (2), the spray of bicyclic chamber
Head (3) assembled in series composition fuel nozzle, it is characterised in that have cloth on an oil duct (5), spinning disk (2) inside fuel inlet fitting (1)
Aperture (9), tangential small-hole (15) and tangential slot (14) are equipped with, bicyclic chamber shower nozzle (3) is divided into ring cavity (7) and (8) two chambers of cavity,
Cavity (10) is formed between spinning disk (2) and bicyclic chamber shower nozzle (3), oil duct (5) is connected by aperture (9) with cavity (10), oil
Road (5) is connected by tangential small-hole (15) with cavity (8), has a passage (11) to communicate between ring cavity (7) and cavity (8), cavity
(8) it is connected with center nozzle (13), ring cavity (7) there are multiple spouts (12).
2. the fuel nozzle according to claim 1 for improving fuel feeding scope, it is characterised in that in spinning disk (2) middle area
Domain is disposed with multiple tangential small-holes (15), and the angle of tangential small-hole (15) and nozzle centerline (18) is 20 ° -- and 70 °.
3. the fuel nozzle according to claim 1 for improving fuel feeding scope, it is characterised in that passage (11) width is
0.1mm--0.3mm。
4. the fuel nozzle according to claim 1 for improving fuel feeding scope, it is characterised in that spout (12) is in ring cavity (7)
On be circumferentially evenly arranged, quantity is 4--12.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621375928.9U CN206398761U (en) | 2016-12-14 | 2016-12-14 | Improve the fuel nozzle of fuel feeding scope |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621375928.9U CN206398761U (en) | 2016-12-14 | 2016-12-14 | Improve the fuel nozzle of fuel feeding scope |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206398761U true CN206398761U (en) | 2017-08-11 |
Family
ID=59510513
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621375928.9U Active CN206398761U (en) | 2016-12-14 | 2016-12-14 | Improve the fuel nozzle of fuel feeding scope |
Country Status (1)
| Country | Link |
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| CN (1) | CN206398761U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108426710A (en) * | 2018-05-22 | 2018-08-21 | 广州飞机维修工程有限公司 | Civil aircraft accessory power system Fuel Flow Regulator test device and method |
| CN110594065A (en) * | 2019-09-05 | 2019-12-20 | 北京工业大学 | Centrifugal nozzle device capable of being disassembled and assembled in sections |
| CN110849629A (en) * | 2019-10-14 | 2020-02-28 | 中国北方发动机研究所(天津) | Adjustable nozzle of turbocharger test bed combustion chamber and combustion chamber |
| CN113357047A (en) * | 2021-06-04 | 2021-09-07 | 中国人民解放军国防科技大学 | Ramjet nozzle suitable for wide Mach number range |
| CN114278964A (en) * | 2021-12-27 | 2022-04-05 | 中国人民解放军国防科技大学 | Fuel nozzle suitable for wide-range ramjet |
-
2016
- 2016-12-14 CN CN201621375928.9U patent/CN206398761U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108426710A (en) * | 2018-05-22 | 2018-08-21 | 广州飞机维修工程有限公司 | Civil aircraft accessory power system Fuel Flow Regulator test device and method |
| CN108426710B (en) * | 2018-05-22 | 2024-04-30 | 广州飞机维修工程有限公司 | Testing device and method for fuel flow regulator of auxiliary power system of civil aircraft |
| CN110594065A (en) * | 2019-09-05 | 2019-12-20 | 北京工业大学 | Centrifugal nozzle device capable of being disassembled and assembled in sections |
| CN110849629A (en) * | 2019-10-14 | 2020-02-28 | 中国北方发动机研究所(天津) | Adjustable nozzle of turbocharger test bed combustion chamber and combustion chamber |
| CN113357047A (en) * | 2021-06-04 | 2021-09-07 | 中国人民解放军国防科技大学 | Ramjet nozzle suitable for wide Mach number range |
| CN113357047B (en) * | 2021-06-04 | 2022-07-29 | 中国人民解放军国防科技大学 | Ramjet nozzle suitable for wide Mach number range |
| CN114278964A (en) * | 2021-12-27 | 2022-04-05 | 中国人民解放军国防科技大学 | Fuel nozzle suitable for wide-range ramjet |
| CN114278964B (en) * | 2021-12-27 | 2022-12-13 | 中国人民解放军国防科技大学 | Fuel nozzle suitable for wide-range ramjet |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 P.O. Box 305, Mianyang City, Sichuan Province Patentee before: CHINA GAS TURBINE EST |