CN108019292A - A kind of oscillation damping method for nozzles with injector guide rib - Google Patents
A kind of oscillation damping method for nozzles with injector guide rib Download PDFInfo
- Publication number
- CN108019292A CN108019292A CN201610961275.0A CN201610961275A CN108019292A CN 108019292 A CN108019292 A CN 108019292A CN 201610961275 A CN201610961275 A CN 201610961275A CN 108019292 A CN108019292 A CN 108019292A
- Authority
- CN
- China
- Prior art keywords
- nozzles
- guide rib
- injector
- vibration
- oscillation damping
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Nozzles (AREA)
Abstract
The invention discloses a kind of oscillation damping method for nozzles with injector guide rib, belong to aero propulsion technical field.The present invention adds a series of vibration damping holes on original nozzles with injector guide rib, to balance the stream pressure of guide rib both sides, can effectively reduce the vibration of nozzles with injector during use.The present invention it is easy to operate, only need to be punched according to certain rules on guide rib without increase supernumerary structure, do not reduce guide rib intensity, do not influence nozzles with injector normal work, the vibration of nozzles with injector during use can effectively be reduced, ensure its normal work, there is preferable practical value and wide application prospect in aero propulsion technical field.
Description
Technical field
This technology invention is related to a kind of oscillation damping method for nozzles with injector guide rib, belongs to aero propulsion technology neck
Domain.
Background technology
Nozzles with injector guide rib is typically mounted on the annular channel between nozzles with injector main jet pipe and outer tube, makes reflux
Can only be according to certain specific flow path, to reduce return flow, and the influence to draught jet capacity is smaller；Thus can be to prevent
The only tail gas of engine suction reflux, ensures normal work of the engine in starting process.In the case of reflux：The knot
Structure reduces the circulation area of reflux, and forms an expanding channel to reduce the flow velocity of reflux, makes reflux stagnation in ejection
Near tube inlet, to ensure the normal work of engine and accessory system.In the case of normal injection：The structure makes injection air-flow
Blended with a kind of inclined angle with mainstream combustion gas, be sufficiently mixed the two, reduce the delivery temperature of nozzles with injector.But
Since the air-flow velocity at nozzles with injector is higher, high-speed flow can produce guide rib and shake along this specific flow path
Move and influence the main jet pipe and outer tube of nozzles with injector, influence it and work normally and reduce its service life.
The content of the invention
1st, purpose：In view of the above-mentioned problems, the purpose of the present invention is provide a kind of vibration damping for the guide rib of nozzles with injector
Method, this method is in the feelings for not increasing supernumerary structure, ensureing certain guide rib intensity, not influencing nozzles with injector normal work
Under condition, the vibration during nozzles with injector use can be effectively reduced, ensure the normal of engine normal starting and accessory system
Work.
2nd, technical solution：The technical solution adopted by the present invention is：Added on original nozzles with injector guide rib a series of
Vibration damping hole, can effectively reduce the vibration of nozzles with injector during use.
3rd, advantage and effect：Beneficial effects of the present invention are：It is easy to operate, only need to be on guide rib according to certain rules
Punch without the certain guide rib intensity of increase supernumerary structure, guarantee, do not influence nozzles with injector normal work, you can effectively
The vibration of nozzles with injector, ensures its normal work during reduction use.
Brief description of the drawings
Fig. 1 is a kind of typically nozzles with injector structure with guide rib.
Fig. 2 is the guide rib after main jet pipe and punching.
Fig. 3 is the top view of Fig. 2.
1. outer tube in figure, 2. main jet pipes, 3. guide ribs (first row), 4. guide ribs (second row), after 5. punchings
Guide rib (first row), 6. punching after guide rib (second row).
Embodiment
This technology is invented with reference to the accompanying drawings and detailed description and is further illustrated.
As shown in Figure 1, the figure is a kind of typical nozzles with injector structure.The present invention does not change the basic structure of nozzles with injector
And size, but improve on this basis.
As shown in Figure 2,3, which is improved nozzles with injector structure (in order to preferably show the position in hole on guide rib
Put, outer tube is saved).The present invention with the addition of a series of vibration damping holes on the basis of Fig. 1 on guide rib, ensure rib
On the premise of piece intensity, the pressure of two sidewind of fin can be balanced, the fin vibration that air-flow excitation produces is reduced, ensures injection
The normal work of jet pipe.
First row fin it is anterior due to parallel with airflow direction and fin is larger herein, more hole can be opened herein,
Aperture also can be larger the pressure of two sidewind of fin is better balanced, and may also function as the effect of certain loss of weight.First row rib
The middle part of piece is almost vertical with airflow direction and is not formed with second row fin and blocks mutually, and punching herein more can increase back
Flow is flowed, influences the normal work of guide rib, therefore should try one's best herein and not punch or beat the less hole in a small amount of aperture to balance
The stream pressure of fin both sides.First row fin rear portion and second row fin are being in axial direction mutual occlusion state, therefore
This position punched at two should be mutually coordinated, in axial direction see this at two on fin hole row should be in staggeredly arrangement form to reduce
Return flow, the aperture of punching should be smaller, and the quantity punched in the case where ensureing fin intensity can be adjusted suitably with preferably
Balance fin both sides stream pressure.
Hole on fin can process after the completion of fin manufacture, and the quantity in hole can be according to the Vibration Condition of nozzles with injector
Adjustment, but must ensure certain fin intensity.
Claims (4)
1. a kind of oscillation damping method for nozzles with injector guide rib, one is added on original nozzles with injector guide rib (3,4)
Serial vibration damping hole, to reduce the vibration of nozzles with injector during use.It is characterized in that：Pressed on original nozzles with injector guide rib
Certain rule adds a series of vibration damping holes, to balance the stream pressure of guide rib both sides, reduces ejection during use
The vibration of pipe.
2. a kind of oscillation damping method for nozzles with injector guide rib according to claim 1, it is characterized in that：Nozzles with injector
A diameter of 0.01~80mm in hole on guide rib.
3. a kind of oscillation damping method for nozzles with injector guide rib according to claim 1, it is characterized in that：Nozzles with injector
The number of rows in hole is 1~100 row on guide rib.
4. a kind of oscillation damping method for nozzles with injector guide rib according to claim 1, it is characterized in that：Nozzles with injector
Number on guide rib per round is 1~100.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610961275.0A CN108019292B (en) | 2016-11-04 | 2016-11-04 | Vibration reduction method for jet nozzle flow guide fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610961275.0A CN108019292B (en) | 2016-11-04 | 2016-11-04 | Vibration reduction method for jet nozzle flow guide fin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108019292A true CN108019292A (en) | 2018-05-11 |
| CN108019292B CN108019292B (en) | 2020-04-28 |
Family
ID=62084121
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610961275.0A Active CN108019292B (en) | 2016-11-04 | 2016-11-04 | Vibration reduction method for jet nozzle flow guide fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108019292B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115432175A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow rectification structure, jet flow control valve, jet flow control system and flight equipment |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2713138Y (en) * | 2004-06-25 | 2005-07-27 | 王本准 | Engine muffler |
| CN202730145U (en) * | 2012-06-08 | 2013-02-13 | 宝钢不锈钢有限公司 | Rectangular gas elbow pipe with vibration-reducing guide plates |
| CN205207262U (en) * | 2015-11-22 | 2016-05-04 | 象山巨鹰科技发展有限公司 | Fan wheel for air purifier |
-
2016
- 2016-11-04 CN CN201610961275.0A patent/CN108019292B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2713138Y (en) * | 2004-06-25 | 2005-07-27 | 王本准 | Engine muffler |
| CN202730145U (en) * | 2012-06-08 | 2013-02-13 | 宝钢不锈钢有限公司 | Rectangular gas elbow pipe with vibration-reducing guide plates |
| CN205207262U (en) * | 2015-11-22 | 2016-05-04 | 象山巨鹰科技发展有限公司 | Fan wheel for air purifier |
Non-Patent Citations (1)
| Title |
|---|
| 张铎等: "辅助动力发动机起动过程中回流问题的研究", 《探索 创新 交流（第7集）——第七届中国航空学会青年科技论坛文集（下册）》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115432175A (en) * | 2022-11-08 | 2022-12-06 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow rectification structure, jet flow control valve, jet flow control system and flight equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108019292B (en) | 2020-04-28 |
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