CN114543118B - Centrifugal starting nozzle - Google Patents
Centrifugal starting nozzle Download PDFInfo
- Publication number
- CN114543118B CN114543118B CN202210158169.4A CN202210158169A CN114543118B CN 114543118 B CN114543118 B CN 114543118B CN 202210158169 A CN202210158169 A CN 202210158169A CN 114543118 B CN114543118 B CN 114543118B
- Authority
- CN
- China
- Prior art keywords
- nozzle
- cyclone
- core rod
- lining
- bushing
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention provides a centrifugal starting nozzle, which comprises a nozzle shell, wherein a communicated channel and an inner cavity are arranged in the nozzle shell, and a bushing and a nozzle are sequentially and cooperatively arranged in the inner cavity; the diameter of one end of the nozzle, which is far away from the lining, is smaller than that of the lining, a plug screw is sleeved on the nozzle, the plug screw is in threaded connection with the nozzle shell, and the plug screw axially compresses the nozzle and the lining; a spring, a core rod and a cyclone are sequentially arranged in a cavity formed by the nozzle and the bushing, a cyclone groove is arranged on the end face of the cyclone, and the cyclone groove is attached to the outlet of the nozzle; the end face of the bushing is provided with a hole communicated with the channel, and the core rod is provided with a transverse flow hole along the radial direction. The invention realizes good atomization and reliable sealing of fuel, has compact structure and easy disassembly, and can avoid the condition of reduced fuel atomization performance caused by the influence of the pulsation pressure of the fuel supply system and the high-pressure air flow in the combustion chamber on the nozzle.
Description
Technical Field
The invention relates to the technical field of aircraft engine starting nozzles, in particular to a centrifugal starting nozzle.
Background
The ignition modes of the combustion chamber include a direct ignition mode and an indirect ignition mode, wherein the indirect ignition generally ignites the fuel oil sprayed by the starting nozzle and the air mixture in the igniter through the electric nozzle, and then the generated flame ignites the oil-gas mixture in the combustion chamber. The atomization stability of the starting nozzle, the tightness of the fuel in the starting nozzle and the reliability and safety of the ignition device are greatly affected.
The general starting nozzle realizes the filtration and swirl atomization of fuel oil through oil filtration and small holes machined on parts, and the reliability of the structure and the nozzle performance are general: since the primer nozzle generally operates in a high temperature environment, sealing of the fuel within the nozzle is difficult; when influenced by the pulsating pressure of the fuel supply system or the high-pressure air flow in the combustion chamber, the fuel atomization performance is lowered.
Disclosure of Invention
In order to solve the technical problems, the invention provides a centrifugal starting nozzle.
The invention is realized by the following technical scheme.
The centrifugal starting nozzle comprises a nozzle shell, wherein a communicated channel and an inner cavity are arranged in the nozzle shell, and a bushing and a nozzle are sequentially arranged in the inner cavity in a matched manner; the diameter of one end of the nozzle, which is far away from the lining, is smaller than that of the lining, a plug screw is sleeved on the nozzle, the plug screw is in threaded connection with the nozzle shell, and the plug screw axially compresses the nozzle and the lining; a spring, a core rod and a cyclone are sequentially arranged in a cavity formed by the nozzle and the bushing, a cyclone groove is arranged on the end face of the cyclone, and the cyclone groove is attached to the outlet of the nozzle; the end face of the bushing is provided with a hole communicated with the channel, and the core rod is provided with a transverse flow hole along the radial direction.
One end of the screw plug, which faces the bushing, is provided with an adjusting washer and a compression ring, the compression ring is made of pure copper material, and the adjusting washer is tightly pressed at the large end of the nozzle.
The inner end of the core rod is in clearance fit with the bushing, the diameter of the core rod towards one end of the cyclone is reduced, the core rod extends into the nozzle, and the spherical surface of the end face of the core rod.
The diameter of one end of the nozzle, which faces the lining, is the same as that of the lining, and a conical transition section is arranged at the position of the nozzle, which corresponds to the smaller diameter of the core rod.
The core rod is axially provided with four cylindrical sections with gradually smaller diameters, the cross flow holes are formed in the second cylindrical section, and the adjacent cylindrical sections are in transition through the conical sections.
The cross flow holes are uniformly distributed along the circumferential direction of the core rod. Preferably an even number, for example four, six, eight.
The flow area of the cross flow holes is smaller than the flow area of the holes on the end face of the bushing. The cross flow orifice diameter is preferably 0.32mm.
Two opposite sides of the side surface of the cyclone are provided with planes, a gap is formed between the planes and the side wall of the nozzle, one end of the cyclone is provided with a boss, the middle of the boss is provided with a circular groove, the circular groove is attached to the outlet of the nozzle, grooves are formed in the two opposite sides of the boss to the planes, and the grooves and the circular groove are spirally shaped.
And a cone angle is arranged at one end of the outlet of the nozzle, which faces the cyclone groove.
The tail part of the nozzle shell is of a thin-wall structure, two closing-in grooves are symmetrically formed in the circumferential direction of the tail part of the screw plug, and a closing-in structure is arranged in the corresponding closing-in groove at the tail part of the nozzle shell.
The invention has the beneficial effects that:
the invention realizes good atomization and reliable sealing of fuel, has compact structure and easy disassembly, and can avoid the condition of reduced fuel atomization performance caused by the influence of the pulsation pressure of the fuel supply system and the high-pressure air flow in the combustion chamber on the nozzle. The spring ensures the close contact of all parts in the nozzle shell, and a certain propping force is arranged between the end face of the cyclone and the nozzle, so that the performance of the nozzle is prevented from being reduced due to the position change in the working process.
Drawings
Fig. 1 is a schematic structural view of the present invention.
In the figure: 1-a nozzle housing; 2-a bushing; 3-nozzle; 4-a screw plug; 5-adjusting the gasket; 6-a compression ring; 7-a core rod; 8-a cyclone; 9-a spring; 10-a transverse flow hole; 11-plane; 12-boss.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the above.
The structure of the invention is schematically shown in fig. 1:
the invention provides a centrifugal starting nozzle, which comprises a nozzle shell 1, wherein a communicated channel and an inner cavity are arranged in the nozzle shell 1, and a lining 2 and a nozzle 3 are sequentially arranged in the inner cavity in a matched manner; the diameter of one end of the nozzle 3 far away from the lining 2 is smaller than that of the lining 2, a plug screw 4 is sleeved on the nozzle 3, the plug screw 4 is in threaded connection with the nozzle shell 1, and the plug screw 4 axially compresses the nozzle 3 and the lining 2; a spring 9, a core rod 7 and a cyclone 8 are sequentially arranged in a cavity formed by the nozzle 3 and the bushing 2, a cyclone groove is arranged on the end surface of the cyclone 8, and the cyclone groove is attached to the outlet of the nozzle 3; the end face of the lining 2 is provided with a hole communicated with the channel, and the core rod 7 is provided with a transverse flow hole 10 along the radial direction.
Principle of: the centrifugal start nozzle is connected to the oil supply line by means of a screw thread on the nozzle housing 1 and is mounted on the igniter. The fuel oil sequentially passes through the channel on the nozzle shell 1 and the hole on the end surface of the lining 2 to enter the core rod 7, and then enters the gap between the outer side of the core rod 7 and the lining 2 and the nozzle 3 through the cross flow hole 10 on the core rod 7, and the fuel oil flow direction is changed because the axis of the cross flow hole 10 is arranged along the radial direction of the core rod 7; the inner and outer side pressures of the core rod 7 are balanced, and the spring 9 is preloaded, so that the influence of the pulsation pressure of the oil supply system can be resisted. Then the fuel oil flows into a swirl groove on the end face of the swirler 8 through a gap between the swirler 8 and the nozzle 3, a hollow oil film is formed through the centrifugal action of the swirl groove, and then under the action of the surface wave and aerodynamic force of the oil film, the oil film is destabilized to form oil mist to be sprayed out through an outlet on the end face of the nozzle 3. The angle of the swirl groove can be designed to control the spray cone angle after fuel atomization. Due to the fact that the spring 9 is arranged between the bushing 2 and the core rod 7, tight contact of all parts in the nozzle shell 1 is guaranteed through the elastic force of the spring 9 in the screwing process of the screw plug 4, meanwhile, certain jacking force is guaranteed between the end face of the cyclone 8 and the nozzle 3, and the phenomenon that the nozzle performance is reduced due to position change in the working process is prevented.
The invention realizes good atomization and reliable sealing of fuel, has compact structure and easy disassembly, and can avoid the condition of reduced fuel atomization performance caused by the influence of the pulsation pressure of the fuel supply system and the high-pressure air flow in the combustion chamber on the nozzle. The spring 9 ensures the close contact of all parts in the nozzle shell 1, and a certain propping force exists between the end face of the cyclone 8 and the nozzle 3, so that the reduction of the nozzle performance caused by the position change in the working process is prevented.
One end of the screw plug 4 facing the bushing 2 is provided with an adjusting washer 5 and a pressing ring 6, the pressing ring 6 is made of pure copper, and the adjusting washer 5 is tightly pressed at the large end of the nozzle 3. The structure of the contact position of the compression ring 6 and the screw plug 4 is deformed during the screwing process of the screw plug 4, so that the sealing between the ring and the nozzle housing 1 is ensured.
The inner end of the core rod 7 is in clearance fit with the bushing 2, the diameter of the core rod 7 towards one end of the cyclone 8 is reduced, and the core rod 7 extends into the nozzle 3, and the spherical surface of the end surface of the core rod 7 is provided. The clearance fit prevents the core rod 7 from jamming in the floating process; the spherical surface reduces the contact area between the core rod 7 and the cyclone 8, and avoids the influence on the atomization performance of the nozzle caused by the separation of the cyclone 8 and the nozzle 3.
The diameter of one end of the nozzle 3 facing the lining 2 is the same as that of the lining 2, and a conical transition section is arranged at the position of the nozzle 3, which corresponds to the position of the core rod 7 and is smaller in diameter. The contact positions of the lining 2 and the nozzle 3 are all thin-wall structures, and the structures of the contact positions of the lining 2 and the nozzle 3 are deformed in the screwing process of the screw plug 4 so as to ensure the sealing among the lining 2, the nozzle 3 and the nozzle shell 1.
The core rod 7 is a cylindrical section with four sections of gradually smaller diameters along the axial direction, the cross flow hole 10 is arranged on the second section of cylindrical section, and the adjacent cylindrical sections are in transition through the conical sections. By this arrangement, the gap between the outside of the mandrel 7 and the liner 2 and the nozzle 3 is nearly tapered, the oil flow is stable, and the influence of the pulsating pressure is avoided.
The cross flow holes 10 are uniformly distributed along the circumferential direction of the mandrel 7. Preferably an even number, for example four, six, eight.
The flow area of the cross flow holes 10 is smaller than the flow area of the holes in the end face of the liner 2. The diameter of the transverse flow hole 10 is preferably 0.32mm.
By this arrangement, smooth flow of fuel into the gap between the core rod 7 and the liner 2 and the spout 3 is achieved.
Two opposite sides of the side surface of the cyclone 8 are provided with planes 11, a gap is formed between the planes 11 and the side wall of the nozzle 3, one end of the cyclone 8 is provided with a boss 12, the middle part of the boss 12 is provided with a circular groove, the circular groove is attached to the outlet of the nozzle, the boss 12 is provided with grooves opposite to the two sides of the planes 11, and the grooves and the circular grooves are spirally formed. The spiral groove is a swirl groove, fuel flows into the swirl groove through a gap between the plane 11 and the side wall of the nozzle 3, forms a hollow oil film under the centrifugal action through spiral flow, and then forms oil mist to be sprayed out through the outlet of the nozzle 3 under the action of oil film surface wave and aerodynamic force due to oil film instability, so that the pressure loss is small, and the high-pressure airflow in the combustion chamber can be resisted.
The outlet of the nozzle 3 is provided with a cone angle towards one end of the swirl groove, so as to play a role in further adjusting the cone angle of the fuel spray.
The tail of the nozzle shell 1 is of a thin-wall structure, two closing-in grooves are symmetrically formed in the circumferential direction of the tail of the screw plug 4, and a closing-in structure is arranged in the corresponding closing-in groove at the tail of the nozzle shell 1. The screw plug 4 is convenient to close and fix in the groove of the screw plug 4 after the screw plug 4 is installed, and the screw plug 4 is prevented from loosening.
Claims (9)
1. A centrifugal start-up nozzle, characterized by: the spray nozzle comprises a spray nozzle shell (1), wherein a communicated channel and an inner cavity are arranged in the spray nozzle shell (1), and a lining (2) and a spray nozzle (3) are sequentially arranged in the inner cavity in a matched manner; the diameter of one end, far away from the lining (2), of the spout (3) is smaller than that of the lining (2), a screw plug (4) is sleeved on the spout (3), the screw plug (4) is in screw connection with the nozzle shell (1), and the screw plug (4) axially compresses the spout (3) and the lining (2); a spring (9), a core rod (7) and a cyclone (8) are sequentially arranged in a cavity formed by the nozzle (3) and the bushing (2), a cyclone groove is arranged on the end face of the cyclone (8), and the cyclone groove is attached to the outlet of the nozzle (3); the end face of the bushing (2) is provided with a hole communicated with the channel, and the core rod (7) is provided with a transverse flow hole (10) along the radial direction;
an adjusting washer (5) and a compression ring (6) are arranged at one end of the screw plug (4) facing the bushing (2), and the adjusting washer (5) is tightly pressed at the large end of the nozzle (3);
two opposite sides of the side surface of the cyclone (8) are provided with planes (11), a gap is formed between the planes (11) and the side wall of the nozzle (3), one end of the cyclone (8) is provided with a boss (12), the middle part of the boss (12) is provided with a circular groove, the circular groove is attached to the outlet of the nozzle, the boss (12) is opposite to the two sides of the planes (11), and the groove and the circular groove form a spiral shape;
the fuel oil flow path is as follows: the fuel flows into the lining (2) from the upper channel of the nozzle shell (1) through the hole on the lining (2), then flows into a gap formed between the core rod (7) and the nozzle (3) from the middle cavity of the core rod (7) through the transverse flow hole (10) on the core rod (7), then flows into a circular groove in the middle of the boss (12) from grooves on two sides of the boss (12) opposite to the plane through a gap formed between the plane (11) on the side surface of the cyclone (8) and the nozzle (3), and then sprays the fuel from the nozzle outlet corresponding to the circular groove.
2. The centrifugal start-up nozzle of claim 1, wherein: the compression ring (6) is made of pure copper material.
3. The centrifugal start-up nozzle of claim 1, wherein: the inner end of the core rod (7) is in clearance fit with the bushing (2), the diameter of the core rod (7) is reduced towards one end of the cyclone (8) and extends into the nozzle (3), and the spherical surface of the end face of the core rod (7) is provided.
4. A centrifugal start-up nozzle as set forth in claim 3 wherein: the diameter of one end of the nozzle (3) facing the bushing (2) is the same as that of the bushing (2), and a conical transition section is arranged at the position of the nozzle (3) corresponding to the diameter of the core rod (7) and is reduced.
5. A centrifugal start-up nozzle as set forth in claim 3 wherein: the mandrel (7) is a cylindrical section with four sections of gradually smaller diameters along the axial direction, the transverse flow hole (10) is arranged on the cylindrical section of the second section, and the adjacent cylindrical sections are in transition through the conical sections.
6. A centrifugal start-up nozzle as set forth in claim 1 or 5, wherein: the cross flow holes (10) are uniformly distributed along the circumferential direction of the core rod (7).
7. The centrifugal start-up nozzle of claim 6, wherein: the flow area of the cross flow holes (10) is smaller than the flow area of the holes on the end face of the lining (2).
8. The centrifugal start-up nozzle of claim 1, wherein: and a cone angle is arranged at one end of the outlet of the nozzle (3) facing the cyclone groove.
9. The centrifugal start-up nozzle of claim 1, wherein: the tail of the nozzle shell (1) is of a thin-wall structure, two closing-in grooves are symmetrically formed in the circumferential direction of the tail of the screw plug (4), and a closing-in structure is arranged in the corresponding closing-in groove in the tail of the nozzle shell (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210158169.4A CN114543118B (en) | 2022-02-21 | 2022-02-21 | Centrifugal starting nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210158169.4A CN114543118B (en) | 2022-02-21 | 2022-02-21 | Centrifugal starting nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114543118A CN114543118A (en) | 2022-05-27 |
| CN114543118B true CN114543118B (en) | 2023-04-25 |
Family
ID=81676383
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210158169.4A Active CN114543118B (en) | 2022-02-21 | 2022-02-21 | Centrifugal starting nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114543118B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1211337A (en) * | 1967-08-28 | 1970-11-04 | Parker Hannifin Corp | Fuel and air nozzle and manifold assemblies for gas turbine engines |
| GB1394856A (en) * | 1972-07-13 | 1975-05-21 | Teledyne Ind | Fuel flow control unit for a gas turbine engine |
| CN201593807U (en) * | 2010-01-11 | 2010-09-29 | 中国航空动力机械研究所 | Fuel oil nozzle |
| CN109140502A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | A kind of built-in fuel manifold for conveying and being atomized for double oil circuits fuel oil |
| CN111981512A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel air atomization device |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103134079B (en) * | 2011-11-30 | 2014-12-17 | 贵州航空发动机研究所 | Double-oil-circuit fuel nozzle |
| WO2015024139A1 (en) * | 2013-08-19 | 2015-02-26 | Wang Kangmei | Centrifugal conical-spray fuel spray nozzle |
| EP3221642B1 (en) * | 2014-11-21 | 2018-09-05 | Ansaldo Energia S.p.A. | Lance injector for injecting fuel into a combustion chamber of a gas turbine |
| CN105180214B (en) * | 2015-09-23 | 2017-10-03 | 哈尔滨工程大学 | A kind of dual fuel nozzle of incendivity low-BTU gas and cyclone integral structure |
| US11585452B2 (en) * | 2019-12-03 | 2023-02-21 | Woodward, Inc. | Fuel nozzle with reduced flow tolerance |
| CN113108313B (en) * | 2021-04-01 | 2022-09-13 | 中国科学院工程热物理研究所 | Single-way oil supply and pressure self-adaptive double-membrane fuel oil atomization device |
| CN113432148B (en) * | 2021-06-28 | 2022-09-27 | 中科航星科技有限公司 | Fuel oil atomizing nozzle structure of turbojet engine and atomizing method thereof |
| CN113739204B (en) * | 2021-08-23 | 2023-02-03 | 四川航天中天动力装备有限责任公司 | Pneumatic centrifugal backflow type fuel nozzle for backflow combustion chamber |
-
2022
- 2022-02-21 CN CN202210158169.4A patent/CN114543118B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1211337A (en) * | 1967-08-28 | 1970-11-04 | Parker Hannifin Corp | Fuel and air nozzle and manifold assemblies for gas turbine engines |
| GB1394856A (en) * | 1972-07-13 | 1975-05-21 | Teledyne Ind | Fuel flow control unit for a gas turbine engine |
| CN201593807U (en) * | 2010-01-11 | 2010-09-29 | 中国航空动力机械研究所 | Fuel oil nozzle |
| CN109140502A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | A kind of built-in fuel manifold for conveying and being atomized for double oil circuits fuel oil |
| CN111981512A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel air atomization device |
Non-Patent Citations (1)
| Title |
|---|
| 华小峰.TB15车发动机喷油器喷嘴结构的改进.矿业快报.2001,(第14期),全文. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114543118A (en) | 2022-05-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2701164A (en) | Duplex fuel nozzle | |
| CN113108313B (en) | Single-way oil supply and pressure self-adaptive double-membrane fuel oil atomization device | |
| GB616300A (en) | Burner | |
| EP3803208B1 (en) | Pre-swirl pressure atomizing tip | |
| CN106499559B (en) | The double oil circuits swirl atomizer structure of major-minor oil circuit integrated design | |
| CN110374761B (en) | Reverse multi-nozzle solid rocket engine | |
| US4311277A (en) | Fuel injector | |
| CN111412086A (en) | Weldless injector for liquid rocket engine | |
| CN114543118B (en) | Centrifugal starting nozzle | |
| CN110410822B (en) | Centrifugal nozzle with variable nozzle opening area | |
| CN86100946A (en) | The high reliability fuel oil nozzle of gas turbine | |
| CN111502860B (en) | Pressure swirl injector with modular design | |
| RU2298729C1 (en) | Jet nozzle | |
| CN113719860A (en) | Fuel atomizing nozzle for class | |
| CN111306322A (en) | Jet valve | |
| US5269495A (en) | High-pressure atomizing nozzle | |
| CN201909311U (en) | Two-stage rotary mixing type air atomizing oil gun | |
| KR20030053435A (en) | Improved liquid fuel injector for burners of gas turbines | |
| US4585173A (en) | Pressure activated conical spray nozzle | |
| RU2670830C9 (en) | Pneumatic spray nozzle for spraying liquids | |
| CN112691801A (en) | Simple adjustable atomizing nozzle and adjusting method | |
| CN112833422A (en) | Spark ignition type igniter for gas fuel and ignition method | |
| CN114985138B (en) | Noise reduction nozzle convenient for adjusting nozzle core | |
| CN116045307B (en) | Dual-centrifugal air alcohol torch igniter | |
| CN111520757B (en) | Direct injection type concave cavity swirl nozzle |
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 |