CN201740050U - Engine flame tube - Google Patents
Engine flame tube Download PDFInfo
- Publication number
- CN201740050U CN201740050U CN2010205015320U CN201020501532U CN201740050U CN 201740050 U CN201740050 U CN 201740050U CN 2010205015320 U CN2010205015320 U CN 2010205015320U CN 201020501532 U CN201020501532 U CN 201020501532U CN 201740050 U CN201740050 U CN 201740050U
- Authority
- CN
- China
- Prior art keywords
- flame tube
- head
- engine
- nozzle
- outlet temperature
- 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.)
- Expired - Lifetime
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- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The utility model relates to an engine flame tube, comprising a flame tube body and a nozzle, wherein a reverse Z-shaped guide plate with a thickness of 0.5 to 1mm is arranged on an inner wall at the head of the flame tube body. The engine flame tube forms a recirculation region through the guide plate and also forms rows of air films tightly attached to the walls of the head to cool and protect the head. The outlet temperature field of a combustion chamber is improved and the distribution coefficient of an outlet temperature can be less than 0.2. A ring vortex head is matched with tangential oil injection. Fuel oil moves in the flame tube according to a helical line path, has long retention time, full combustion, improved combustion efficiency and a small amount of exhaust and smoke.
Description
Technical field
The utility model relates to a kind of engine flame tube.
Background technology
Aeroengine combustor liner is to adopt the version of swirler to realize flameholding mostly, but in the small-power aero-engine, when particularly the small-power aero-engine adopts reverse flow type combustor's version, the engine external diameter is relatively large, burner inner liner adopts traditional swirler structure, and each swirler all produces an independently head recirculating zone, joins flame in addition, cause the number of swirler many, nozzle is many.Because the low-powered engine fuel delivery is little, under nozzle quantity can not situation very little, the fuel flow of single-nozzle was inevitable very little, and this bring very big difficulty can for the processing of nozzle.
Summary of the invention
The purpose of this utility model is to overcome the deficiency of said structure, provides a kind of simple in structure, easy to process, and fuel oil time of staying in burner inner liner is long, and engine flame tube completely burns.
The utility model comprises burner inner liner body, nozzle, it is characterized in that: it is the Z-shaped deflector of falling of 0.5-1 millimeter that described burner inner liner body head inwall is provided with thickness.
Adopt burner inner liner of the present utility model, its recirculating zone is whole ring whirlpool, and flame connection flame is good, therefore can reduce the quantity of nozzle, and it is too little also to have solved little aeroengine combustor buring flow, the difficult problem that nozzle quantity can not be too much.
The utility model air communication is crossed when deflector forms the recirculating zone and has also been formed the several rows of air film of being close to the head wall, has played the effect of cooling protection head; Improve the outlet temperature field of combustion chamber, outlet temperature breadth coefficient (OTDF) can be less than 0.2; Ring whirlpool head and tangential oil spout coupling, by the spiral trajectory motion, the time of staying of fuel oil in burner inner liner is long in burner inner liner for fuel oil, burns fully, and efficiency of combustion is improved, and smoking of the exhaust is few.
Description of drawings
Fig. 1 is the utility model structural representation.
Fig. 2 is that the K of Fig. 1 is to view.
Fig. 3 is the A-A view of Fig. 2.
Among the figure: 1, deflector, 2, burner inner liner body, 3, nozzle, 4, airflow hole.
The specific embodiment
The utility model comprises burner inner liner body 2, nozzle 3.Burner inner liner body 2 head inwalls are provided with down Z-shaped deflector 1, and the thickness of deflector 1 is 0.7 millimeter.
During work, air-flow enters from the airflow hole 4 of burner inner liner body 2 heads, and Z-shaped deflector 1 back of flowing through down forms the ring whirlpool of a large scale, with the tangential oil spout coupling of nozzle 3, thereby realizes that combustion chambers burn is stable.
Claims (1)
1. an engine flame tube comprises burner inner liner body (2), nozzle (3), it is characterized in that: it is the Z-shaped deflector of falling of 0.5-1 millimeter (1) that described burner inner liner body (2) head inwall is provided with thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205015320U CN201740050U (en) | 2010-08-23 | 2010-08-23 | Engine flame tube |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010205015320U CN201740050U (en) | 2010-08-23 | 2010-08-23 | Engine flame tube |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201740050U true CN201740050U (en) | 2011-02-09 |
Family
ID=43555325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010205015320U Expired - Lifetime CN201740050U (en) | 2010-08-23 | 2010-08-23 | Engine flame tube |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201740050U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102818291A (en) * | 2012-09-03 | 2012-12-12 | 中国航空动力机械研究所 | Flame tube |
| CN113154453A (en) * | 2021-05-06 | 2021-07-23 | 中国航发湖南动力机械研究所 | Tangential inclined annular membrane diverging and cooling structure |
-
2010
- 2010-08-23 CN CN2010205015320U patent/CN201740050U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102818291A (en) * | 2012-09-03 | 2012-12-12 | 中国航空动力机械研究所 | Flame tube |
| CN102818291B (en) * | 2012-09-03 | 2015-07-15 | 中国航空动力机械研究所 | Flame tube |
| CN113154453A (en) * | 2021-05-06 | 2021-07-23 | 中国航发湖南动力机械研究所 | Tangential inclined annular membrane diverging and cooling structure |
| CN113154453B (en) * | 2021-05-06 | 2022-07-08 | 中国航发湖南动力机械研究所 | Tangential tilting type annular membrane diverging and cooling structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110209 |