CN104005853A - Ignition device for aircraft engine ground test - Google Patents
Ignition device for aircraft engine ground test Download PDFInfo
- Publication number
- CN104005853A CN104005853A CN201410225087.2A CN201410225087A CN104005853A CN 104005853 A CN104005853 A CN 104005853A CN 201410225087 A CN201410225087 A CN 201410225087A CN 104005853 A CN104005853 A CN 104005853A
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- CN
- China
- Prior art keywords
- lower shell
- upper shell
- aeroengine
- shell body
- air inlet
- 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
- 238000002347 injection Methods 0.000 claims abstract description 11
- 239000007924 injection Substances 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 6
- 238000010304 firing Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 230000003134 recirculating effect Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
The invention relates to an ignition device for an aircraft engine ground test. The ignition device comprises an upper shell, a lower shell and a flame ejector cone, wherein one end of the upper shell is in a spherical closed shape, and the other end of the upper shell is fixedly connected with the lower shell; an injection nozzle and an ignition plug are arranged on the upper shell; an air inlet groove is formed in the lower shell; a baffle is arranged in the lower shell; the flame ejector cone is connected with the lower shell and extends into a flame tube of an aircraft engine. A continuous ignition function can be generated, the requirement on the aircraft engine ground test is met, and the device can be continuously used and has a good ignition effect.
Description
Technical field
The present invention relates to a kind of ignition mechanism, especially a kind of aeroengine ground run ignition mechanism.
Background technique
Aeroengine is different with performance requirement according to purposes, and its firing mode is not identical yet, at disposable bullet, with in aeroengine, generally adopts the firing mode of pyrophoric ignition, and this firing mode has that energy is large, success rate advantages of higher; If certain bullet is with in motor, adopted built-in disposable, the solid gunpowder igniter reliable, torch energy is large of lighting a fire, this firing mode is also referred to as indirect firing mode.But as disposable igniter, in reseach of engine process, can not adapt to the needs of a large amount of test runs, subject matter is that disposable cartridge cost is high, the problems such as dismounting complexity, and engine performance and body structure are had to impact, make in process of scientific research, to be difficult to obtain fast and effectively firing test data.
Summary of the invention
The object of this invention is to provide a kind of aeroengine ground run ignition mechanism, can realize continuous ignition function, guarantee the needs of aeroengine ground run, cost-saving, easy accessibility, and can not affect performance and the body structure of aeroengine ground run.
Technological scheme of the present invention is, aeroengine ground run is arranged on the casing of aeroengine by ignition mechanism, comprise upper shell, lower shell body, flame injection cylinder, described upper shell and lower shell body are cylindrical, upper shell one end is spheroidal sealing, the other end is fixedly connected with lower shell body, on upper shell, be provided with oil nozzle and ignition electric nozzle, on lower shell body, be provided with air inlet duct and plate washer, the airintake direction of described air inlet duct is towards the direction of upper shell, baffle plate is circular arc, be arranged on lower shell body inside, one end is fixed on bottom the air inlet duct parallel to an axis of air inlet duct, opposite side extend to upper shell inner and with upper shell parallel sidewalls, flame injection cylinder is connected with lower shell body, and extend in the burner inner liner of aeroengine.
Described flame injection cylinder is connected by sphere with lower shell body, and the position contacting with the burner inner liner of aeroengine is sphere.
Working procedure of the present invention is, air enters ignition mechanism inside by the air inlet duct of lower shell body, under the effect of baffle plate, change airflow direction, make air-flow moving along upper housing wall surface current, under the effect of spherical shell, form recirculating zone, meanwhile, this air-flow mixes with the fuel oil of pilot jet ejection, gas mixture flows near ignition electric nozzle together, under the effect of electrical spark, light gas mixture, and form stable burning things which may cause a fire disaster in position, recirculating zone, constantly light new gas mixture, and make flame blow-off point firearm.This ignition mechanism is equivalent to a small combustion chamber in fact, adopts the gas mixture in the spark ignition small combustion chamber that inductance sparking system forms to form flame, and flame is lighted the gas mixture of main combustion chamber from small combustion chamber ejection, complete the igniting of motor.
Volume of the present invention is little, its volume only has Φ 24 * 50, and simple in structure, be arranged on aero-engine casing, be positioned at the outside of aeroengine, be convenient to assembling and the decomposition of ignition system and oil supply system, guarantee can directly carry out oil sealing and payment work after engine test, shortened the manufacturing cycle.In addition, flame injection cylinder of the present invention is that sphere is connected with lower shell body, when work, when displacement appears in the burner inner liner of aeroengine, can relatively rotate, and avoids occurring ignition mechanism itself and the damage to engine structure; Adopt the intake method of oblique air inlet duct, in limited space, increased air inflow, thus the energy of guarantee point firearm torch; The setting of arc-shaped baffle, has increased the airspeed of igniter inside, thereby can cause stronger eddy flow effect, is conducive to the formation of recirculating zone.The present invention can produce continuous ignition function, guarantees the demand of aeroengine ground run, can use continuously, has good igniting effect.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
The side view of Fig. 2 Fig. 1;
The partial enlarged drawing of Fig. 3 Fig. 1;
Fig. 4 is the structural representation of baffle plate.
Embodiment
As shown in the figure, the concrete technological scheme of the ignition mechanism that aeroengine ground run is used is: aeroengine ground run is arranged on the casing 9 of aeroengine by ignition mechanism, comprise upper shell 1, lower shell body 2, flame injection cylinder 3, described upper shell 1 is cylindrical with lower shell body 2, upper shell 1 one end is spheroidal sealing, the other end is fixedly connected with lower shell body 2, on upper shell 1, be provided with oil nozzle 4 and ignition electric nozzle 5, on lower shell body 2, be provided with air inlet duct 7 and plate washer 6, the airintake direction of described air inlet duct 7 is towards the direction of upper shell 1, baffle plate 6 is circular arc, be arranged on lower shell body 2 inside, one end is fixed on bottom air inlet duct 7 parallel to an axiss of air inlet duct 7, opposite side extend to upper shell 1 inner and with upper shell 1 parallel sidewalls, flame injection cylinder 3 is connected with lower shell body 2, and extend in the burner inner liner 8 of aeroengine.Described flame injection cylinder 3 is connected by sphere with lower shell body 2, and the position contacting with the burner inner liner 8 of aeroengine is sphere.
Claims (2)
1. an aeroengine ground run ignition mechanism, it is characterized in that, described device is arranged on the casing [9] of aeroengine, comprise upper shell [1], lower shell body [2], flame injection cylinder [3], described upper shell [1] is cylindrical with lower shell body [2], upper shell [1] one end is spheroidal sealing, the other end is fixedly connected with lower shell body [2], on upper shell [1], be provided with oil nozzle [4] and ignition electric nozzle [5], on lower shell body [2], be provided with air inlet duct [7] and plate washer [6], the airintake direction of described air inlet duct [7] is towards the direction of upper shell [1], baffle plate [6] is circular arc, be arranged on lower shell body [2] inside, one end is fixed on bottom air inlet duct [7] parallel to an axis of air inlet duct [7], opposite side extend to upper shell [1] inner and with upper shell [1] parallel sidewalls, flame injection cylinder [3] is connected with lower shell body [2], and extend in the burner inner liner [8] of aeroengine.
2. aeroengine ground run ignition mechanism as claimed in claim 1, is characterized in that, described flame injection cylinder [3] is connected by sphere with lower shell body [2], and the position contacting with the burner inner liner [8] of aeroengine is sphere.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410225087.2A CN104005853A (en) | 2014-05-26 | 2014-05-26 | Ignition device for aircraft engine ground test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410225087.2A CN104005853A (en) | 2014-05-26 | 2014-05-26 | Ignition device for aircraft engine ground test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104005853A true CN104005853A (en) | 2014-08-27 |
Family
ID=51366710
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410225087.2A Pending CN104005853A (en) | 2014-05-26 | 2014-05-26 | Ignition device for aircraft engine ground test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104005853A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240847A (en) * | 2015-11-19 | 2016-01-13 | 哈尔滨东安发动机（集团）有限公司 | Anti-backfire structure of combustion chamber |
| CN105781747A (en) * | 2016-03-22 | 2016-07-20 | 南京理工大学 | Ignition device for liquid refuel ramjet engine |
| CN106050471A (en) * | 2016-06-13 | 2016-10-26 | 南京理工大学 | Pre-atomization ignition device used for liquid fuel ramjet engine |
| US20180003388A1 (en) * | 2016-07-01 | 2018-01-04 | Hanwha Techwin Co., Ltd. | Slinger combustor and gas turbine engine system having the same |
| CN114151200A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Igniter |
| CN114294676A (en) * | 2021-12-16 | 2022-04-08 | 北京动力机械研究所 | Precombustion chamber structure with wide ignition boundary |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4141213A (en) * | 1977-06-23 | 1979-02-27 | General Motors Corporation | Pilot flame tube |
| CN87204751U (en) * | 1987-11-09 | 1988-07-27 | 株洲市东区节能燃油器厂 | Continuous flame oil burner for industrial furnace |
| CN2030285U (en) * | 1988-04-22 | 1989-01-04 | 汤民生 | Counterflow burner for industrial furnace |
| CN2172406Y (en) * | 1993-04-24 | 1994-07-20 | 航空航天工业部第六○八研究所 | Ignitor for industrial furnace burner |
| CN202852885U (en) * | 2012-10-24 | 2013-04-03 | 哈尔滨东安发动机（集团）有限公司 | Baffling type annular combustion chamber |
| CN203925752U (en) * | 2014-05-26 | 2014-11-05 | 哈尔滨东安发动机（集团）有限公司 | Aeroengine ground run ignition mechanism |
-
2014
- 2014-05-26 CN CN201410225087.2A patent/CN104005853A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4141213A (en) * | 1977-06-23 | 1979-02-27 | General Motors Corporation | Pilot flame tube |
| CN87204751U (en) * | 1987-11-09 | 1988-07-27 | 株洲市东区节能燃油器厂 | Continuous flame oil burner for industrial furnace |
| CN2030285U (en) * | 1988-04-22 | 1989-01-04 | 汤民生 | Counterflow burner for industrial furnace |
| CN2172406Y (en) * | 1993-04-24 | 1994-07-20 | 航空航天工业部第六○八研究所 | Ignitor for industrial furnace burner |
| CN202852885U (en) * | 2012-10-24 | 2013-04-03 | 哈尔滨东安发动机（集团）有限公司 | Baffling type annular combustion chamber |
| CN203925752U (en) * | 2014-05-26 | 2014-11-05 | 哈尔滨东安发动机（集团）有限公司 | Aeroengine ground run ignition mechanism |
Non-Patent Citations (2)
| Title |
|---|
| 彭拾义: "燃烧室的浮动连接技术", 《燃气轮机技术》 * |
| 邓明: "《航空燃气涡轮发动机原理与构造》", 30 March 2008, 国防工业出版社 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240847A (en) * | 2015-11-19 | 2016-01-13 | 哈尔滨东安发动机（集团）有限公司 | Anti-backfire structure of combustion chamber |
| CN105781747A (en) * | 2016-03-22 | 2016-07-20 | 南京理工大学 | Ignition device for liquid refuel ramjet engine |
| CN106050471A (en) * | 2016-06-13 | 2016-10-26 | 南京理工大学 | Pre-atomization ignition device used for liquid fuel ramjet engine |
| US20180003388A1 (en) * | 2016-07-01 | 2018-01-04 | Hanwha Techwin Co., Ltd. | Slinger combustor and gas turbine engine system having the same |
| KR20180003856A (en) * | 2016-07-01 | 2018-01-10 | 한화테크윈 주식회사 | Slinger combustor and gas turbine engine system |
| US10907834B2 (en) * | 2016-07-01 | 2021-02-02 | Hanwha Aerospace Co., Ltd. | Slinger combustor having main combustion chamber and sub-combustion chamber, and gas turbine engine system having the same |
| CN114151200A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Igniter |
| CN114294676A (en) * | 2021-12-16 | 2022-04-08 | 北京动力机械研究所 | Precombustion chamber structure with wide ignition boundary |
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| PB01 | Publication | ||
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Application publication date: 20140827 |