CN108194205B - It is a kind of for improving the ignition electric nozzle of aero-engine ignition stability - Google Patents
It is a kind of for improving the ignition electric nozzle of aero-engine ignition stability Download PDFInfo
- Publication number
- CN108194205B CN108194205B CN201711457152.4A CN201711457152A CN108194205B CN 108194205 B CN108194205 B CN 108194205B CN 201711457152 A CN201711457152 A CN 201711457152A CN 108194205 B CN108194205 B CN 108194205B
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- China
- Prior art keywords
- ignition
- ignitron
- nozzle
- intake duct
- air intake
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Classifications
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- 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
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
一种用于提高航空发动机点火稳定性的点火电嘴，包括点火管、点火电极、进气道及转接座；点火管为圆柱筒形结构，点火管尾端密封固接在转接座上，点火管首端为锥形喷口结构；点火电极位于点火管轴向中心；进气道为矩形管结构，进气道连接在点火管上，进气道与点火管具有夹角，进气道内至少分布有两处挡块，挡块间交错布置；转接座密封固连在机匣上，机匣上开设有点火电嘴安装孔，点火电嘴安装孔孔径大于点火管直径，点火电嘴安装孔孔径小于转接座直径；在进气道管口上设有转接板，转接板平行于火焰筒轴向中心线，进气道通过转接板与火焰筒相固连；点火管锥形喷口及进气道管口均朝向火焰筒内侧，点火管轴向中心线与火焰筒轴向中心线相垂直。
An ignition nozzle for improving the ignition stability of an aero-engine, comprising an ignition tube, an ignition electrode, an air inlet and an adapter seat; the ignition tube is a cylindrical structure, and the tail end of the ignition tube is sealed and fixed on the adapter seat , the head end of the ignition tube is a conical nozzle structure; the ignition electrode is located in the axial center of the ignition tube; the intake port is a rectangular tube structure, the intake port is connected to the ignition tube, and the intake port and the ignition tube have an included angle. At least two blocks are distributed, and the blocks are staggered; the adapter seat is sealed and fixed on the casing, and the casing is provided with an ignition nozzle installation hole. The diameter of the ignition nozzle installation hole is larger than the diameter of the ignition pipe, and the ignition nozzle is installed. The hole diameter is smaller than the diameter of the adapter seat; an adapter plate is arranged on the nozzle of the intake duct, the adapter plate is parallel to the axial centerline of the flame tube, and the intake duct is fixedly connected with the flame tube through the adapter plate; the ignition tube is tapered The nozzle and the inlet pipe are all facing the inner side of the flame tube, and the axial centerline of the ignition tube is perpendicular to the axial centerline of the flame tube.
Description
Technical field
The invention belongs to aero-engine technology fields, stablize more particularly to one kind for improving aero-engine ignition
The ignition electric nozzle of property.
Background technique
With the fast development that the aerospaces such as hypersonic aircraft and sky and space plane are equipped, for the following world back and forth with
And national defence provides effective guarantee.Due to the main activities range of hypersonic aircraft and sky and space plane be in atmosphere and across
Endoatmosphere, while there is very high flight Mach number, and air will be entered in the combustion chamber of engine with high flow rate, air with
The incorporation time of fuel is extremely short, this can bring very big influence to mixed gas quality, and higher gaseous mixture flow velocity is easy to put out
, to reduce the Ignition Stability of engine chamber, or even there is the risk of flame-out in flight in the fiery core of igniting.
Summary of the invention
In view of the problems of the existing technology, the present invention provides a kind of for improving the point of aero-engine ignition stability
Thermoelectricity mouth can reduce the induction air flow ratio of gaseous mixture, and can form stable flow field in ignition location, ensure that igniting is stablized
Property.
To achieve the goals above, the present invention adopts the following technical scheme: it is a kind of steady for improving aero-engine ignition
Qualitative ignition electric nozzle, including ignitron, ignitor, air intake duct and adapter；The ignitron is cylinder barrel shaped structure, point
Fire tube tail end sealing is fixed on adapter, and ignitron head end is conical nozzle structure；The ignitor is located at ignitron
Axial centre；The air intake duct is rectangular tube structure, and air intake duct is connected on ignitron, and air intake duct and ignitron have folder
Block at two, and interlaced arrangement between block is at least distributed in angle in air intake duct.
The adapter is connected on casing by bolt seal, and ignition electric nozzle mounting hole is offered on casing, switching
The diameter of seat is greater than the aperture of ignition electric nozzle mounting hole, and the aperture of ignition electric nozzle mounting hole is greater than the diameter of ignitron.
Pinboard is provided on the nozzle of the air intake duct, pinboard is parallel to the longitudinal center line of burner inner liner, air inlet
Road is fixedly connected with by pinboard and burner inner liner.
The nozzle of the conical nozzle of the ignitron and air intake duct is towards on the inside of burner inner liner, and the axial centre of ignitron
The longitudinal center line of line and burner inner liner is perpendicular.
Beneficial effects of the present invention:
The ignition electric nozzle for being used to improve aero-engine ignition stability of the invention, can reduce the inlet air flow of gaseous mixture
Speed, and stable flow field can be formed in ignition location, it ensure that Ignition Stability.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the ignition electric nozzle for improving aero-engine ignition stability of the invention；
Fig. 2 is the scheme of installation of the ignition electric nozzle for improving aero-engine ignition stability of the invention；
Fig. 3 is the air-suction state figure of the ignition electric nozzle for improving aero-engine ignition stability of the invention；
Fig. 4 is the fired state figure of the ignition electric nozzle for improving aero-engine ignition stability of the invention；
In figure, 1-ignitron, 2-ignitors, 3-air intake ducts, 4-adapters, 5-blocks, 6-casings, 7-points
Thermoelectricity mouth mounting hole, 8-pinboards, 9-burner inner liners, 10-gaseous mixtures, 11-flames.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments.
As shown in Figure 1, 2, a kind of for improving the ignition electric nozzle of aero-engine ignition stability, including ignitron 1, point
Thermoelectricity pole 2, air intake duct 3 and adapter 4；The ignitron 1 is cylinder barrel shaped structure, and 1 tail end sealing of ignitron is fixed in switching
On seat 4,1 head end of ignitron is conical nozzle structure；The ignitor 2 is located at the axial centre of ignitron 1；The air intake duct
3 be rectangular tube structure, and air intake duct 3 is connected on ignitron 1, and air intake duct 3 and ignitron 1 are in 60 ° of angles, in air intake duct 3
Block 5 at two, and 5 interlaced arrangements of block are at least distributed with.
The adapter 4 is connected on casing 6 by bolt seal, and ignition electric nozzle mounting hole 7 is offered on casing 6,
The diameter of adapter 4 is greater than the aperture of ignition electric nozzle mounting hole 7, and the aperture of ignition electric nozzle mounting hole 7 is greater than the straight of ignitron 1
Diameter.
Pinboard 8 is provided on the nozzle of the air intake duct 3, pinboard 8 is parallel to the longitudinal center line of burner inner liner 9,
Air intake duct 3 is fixedly connected with by pinboard 8 with burner inner liner 9.
The nozzle of the conical nozzle of the ignitron 1 and air intake duct 3 is towards 9 inside of burner inner liner, and the axial direction of ignitron 1
The longitudinal center line of center line and burner inner liner 9 is perpendicular.
As shown in figure 3, the gaseous mixture 10 of high flow rate initially enters in air intake duct 3, and successively pass through the blocking of three blocks 5
And deceleration, then entered in ignitron 1 with slow flow state, then gaseous mixture 10 can form standing vortex in 1 inner cavity of ignitron, so that
Gaseous mixture 10 forms stable flow field.Next, being discharged by ignitor 2, and between ignitor 2 and ignitron 1
High voltage flash is formed, to form high-intensitive spark, the gaseous mixture 10 of 1 inner cavity of ignitron will be lighted by spark, and then be formed
Stablize burned flame 11, flame 11 will be sprayed into burner inner liner 9 by the conical nozzle of ignitron 1, as shown in Figure 4；Finally, point
The flame 11 that fire tube 1 sprays will pilot flame cylinder 9 burn indoor high flow rate gaseous mixture, so that realizes engine stablizes combustion
It burns.
The scope of patent protection that scheme in embodiment is not intended to limit the invention, it is all without departing from carried out by the present invention etc.
Effect implements or change, is both contained in the scope of the patents of this case.
Claims (4)
1. a kind of for improving the ignition electric nozzle of aero-engine ignition stability, it is characterised in that: including ignitron, ignition power
Pole, air intake duct and adapter；The ignitron is cylinder barrel shaped structure, and ignitron tail end sealing is fixed on adapter, is lighted a fire
Pipe head end is conical nozzle structure；The ignitor is located at the axial centre of ignitron；The air intake duct is rectangular tube structure,
Air intake duct is connected on ignitron, and is in 60 ° of angles between air intake duct and the head end of ignitron, is at least distributed in air intake duct
Block at two, and interlaced arrangement between block.
2. according to claim 1 a kind of for improving the ignition electric nozzle of aero-engine ignition stability, feature exists
In: the adapter is connected on casing by bolt seal, offers ignition electric nozzle mounting hole on casing, adapter it is straight
Diameter is greater than the aperture of ignition electric nozzle mounting hole, and the aperture of ignition electric nozzle mounting hole is greater than the diameter of ignitron.
3. according to claim 1 a kind of for improving the ignition electric nozzle of aero-engine ignition stability, feature exists
In: pinboard is provided on the nozzle of the air intake duct, pinboard is parallel to the longitudinal center line of burner inner liner, and air intake duct passes through
Pinboard is fixedly connected with burner inner liner.
4. according to claim 1 a kind of for improving the ignition electric nozzle of aero-engine ignition stability, feature exists
In the conical nozzle of: the ignitron and the nozzle of air intake duct towards on the inside of burner inner liner, and the longitudinal center line of ignitron with
The longitudinal center line of burner inner liner is perpendicular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711457152.4A CN108194205B (en) | 2017-12-28 | 2017-12-28 | It is a kind of for improving the ignition electric nozzle of aero-engine ignition stability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711457152.4A CN108194205B (en) | 2017-12-28 | 2017-12-28 | It is a kind of for improving the ignition electric nozzle of aero-engine ignition stability |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108194205A CN108194205A (en) | 2018-06-22 |
| CN108194205B true CN108194205B (en) | 2019-05-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711457152.4A Active CN108194205B (en) | 2017-12-28 | 2017-12-28 | It is a kind of for improving the ignition electric nozzle of aero-engine ignition stability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108194205B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109441643B (en) * | 2018-09-27 | 2020-12-01 | 北京航空航天大学 | Micro-turbojet and gas turbine combustor ignition devices |
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| CN101144430A (en) * | 2007-10-19 | 2008-03-19 | 北京航空航天大学 | Tower Flame Stabilizers for Rotary Engines |
| CN201908766U (en) * | 2010-10-29 | 2011-07-27 | 四川泛华航空仪表电器厂 | Low-pressure high-energy electric ignition semiconductor spark plug |
| CN102400789A (en) * | 2011-08-26 | 2012-04-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Igniter shell capable of stabilizing flame |
| CN103277231A (en) * | 2013-03-18 | 2013-09-04 | 中国人民解放军空军工程大学 | Aero-engine air rotational flow plasma igniter |
| CN104454290A (en) * | 2014-10-23 | 2015-03-25 | 中国人民解放军空军工程大学 | Elongating arc plasma jet ignition device |
| CN204984608U (en) * | 2015-09-16 | 2016-01-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Ignition electric nozzle mounting structure |
| CN205119053U (en) * | 2015-11-16 | 2016-03-30 | 陕西航空电气有限责任公司 | Nozzle and have its torch electric nozzle and engine ignition |
| WO2016139696A1 (en) * | 2015-03-03 | 2016-09-09 | 株式会社 東芝 | Ignition device and gas turbine burner |
| CN106677905A (en) * | 2016-11-04 | 2017-05-17 | 天津航空机电有限公司 | Platinum-iridium alloy type ignition electric nozzle for aero-engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9140193B2 (en) * | 2011-05-03 | 2015-09-22 | Siemens Energy, Inc. | Gas turbine igniter with structure to reduce radial movement of igniter rod |
-
2017
- 2017-12-28 CN CN201711457152.4A patent/CN108194205B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101144430A (en) * | 2007-10-19 | 2008-03-19 | 北京航空航天大学 | Tower Flame Stabilizers for Rotary Engines |
| CN201908766U (en) * | 2010-10-29 | 2011-07-27 | 四川泛华航空仪表电器厂 | Low-pressure high-energy electric ignition semiconductor spark plug |
| CN102400789A (en) * | 2011-08-26 | 2012-04-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Igniter shell capable of stabilizing flame |
| CN103277231A (en) * | 2013-03-18 | 2013-09-04 | 中国人民解放军空军工程大学 | Aero-engine air rotational flow plasma igniter |
| CN104454290A (en) * | 2014-10-23 | 2015-03-25 | 中国人民解放军空军工程大学 | Elongating arc plasma jet ignition device |
| WO2016139696A1 (en) * | 2015-03-03 | 2016-09-09 | 株式会社 東芝 | Ignition device and gas turbine burner |
| CN204984608U (en) * | 2015-09-16 | 2016-01-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Ignition electric nozzle mounting structure |
| CN205119053U (en) * | 2015-11-16 | 2016-03-30 | 陕西航空电气有限责任公司 | Nozzle and have its torch electric nozzle and engine ignition |
| CN106677905A (en) * | 2016-11-04 | 2017-05-17 | 天津航空机电有限公司 | Platinum-iridium alloy type ignition electric nozzle for aero-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108194205A (en) | 2018-06-22 |
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Effective date of registration: 20240423 Address after: Runyayuan Street Store, No. 65 Qixiang Road, Hanjiang District, Yangzhou City, Jiangsu Province, 225000 Patentee after: Jiangsu Hangyuan New Technology Co.,Ltd. Country or region after: China Address before: 110136, Liaoning, Shenyang moral and Economic Development Zone, No. 37 South Avenue moral Patentee before: SHENYANG AEROSPACE University Country or region before: China |
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Effective date of registration: 20241108 Address after: 225000 Jiangwang Street and Yuexiyuan 303, Hanjiang District, Yangzhou City, Jiangsu Province Patentee after: Yangzhou Starry Sky Technology Co.,Ltd. Country or region after: China Address before: Runyayuan Street Store, No. 65 Qixiang Road, Hanjiang District, Yangzhou City, Jiangsu Province, 225000 Patentee before: Jiangsu Hangyuan New Technology Co.,Ltd. Country or region before: China |