CN204460285U - A kind of annular return combustion chamber flame drum - Google Patents
A kind of annular return combustion chamber flame drum Download PDFInfo
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- CN204460285U CN204460285U CN201420752874.8U CN201420752874U CN204460285U CN 204460285 U CN204460285 U CN 204460285U CN 201420752874 U CN201420752874 U CN 201420752874U CN 204460285 U CN204460285 U CN 204460285U
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- inner liner
- hole
- burner inner
- combustion chamber
- nozzle
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Abstract
The utility model is a kind of annular return combustion chamber flame drum, this burner inner liner and outer casing form combustion chamber, be mainly used in small turbine engine, function makes compressor compressed air out in a combustion chamber and fuel mix, forms combustion mixture and burn.Make the converts chemical energy of burning become the heat energy of gas, improve the temperature of gas, to do work in turbine.The structure of this burner inner liner, compared with general combustion chamber flame drum, has the advantages that volume is little, structure is simple and compact, has larger actual application value.
Description
Technical field
The invention belongs to turbogenerator technical field, relate to a kind of annular return combustion chamber flame drum.
Background technology
Combustion chamber flame drum is one of critical component of small turbine engine, and major function makes compressor compressed air out in a combustion chamber and fuel mix, forms combustion mixture and burns.Make the converts chemical energy of burning become the heat energy of gas, improve the temperature of gas, to do work in turbine.
Major part reflowed combustion indoor employing list cyclone stabilizes the flame.The mode that the present invention takes another kind to stabilize the flame, namely the primary holes be distributed in outside burner inner liner becomes 30 ° of oblique heads in angle with axis, the existence of this angle can make the air-flow generation backflow entering primary zone stabilize the flame, owing to the present invention is directed to put-put (engine diameters is at about 200mm), so adopt this simple method also can reach the effect stabilized the flame.
Summary of the invention
Object of the present invention: the small turbine engine annular return combustion chamber flame drum providing a kind of structure simpler, compact.
Technical scheme of the present invention: a kind of annular return combustion chamber flame drum, is characterized in that: burner inner liner and casing are fixed by locating hole (6), and casing and the concentricity axle of burner inner liner.Air-flow out enters the gap area of casing and burner inner liner from turbine, then burner inner liner inside is entered by primary holes (1), afterburning hole (2) and blending hole (3), the nozzle installing hole (5) of burner inner liner head is provided with fuel nozzle, fuel oil feeds in burner inner liner by nozzle, igniter installing hole (4) is provided with igniter, lights the fuel air mixture in burner inner liner.
Compared with common toroidal combustion chamber, the gas after burning is through the backflow of 180 ° in burner inner liner, and outer ring cavity flowing is flowed contrary with the main flow in burner inner liner, and the flowing of interior ring cavity is identical with main flow.In interior ring cavity, because air-flow is turned back from head, cause the outer ring cavity of its pressure ratio low, it is especially careful that the flowing therefore in burner inner liner controls needs.Based on this reason, the primary holes be distributed in outside burner inner liner is become 30 ° of oblique heads in angle with axis by the present invention, and the existence of this angle can make the air-flow generation backflow entering primary zone stabilize the flame
Beneficial effect of the present invention: the engine shaft of this annular return combustion chamber layout, apart from can significantly shorten, effectively can utilize the volume of combustion chamber, and make the structure of combustion chamber compacter.Meanwhile, avoid adopting cyclone to be used as the device stabilized the flame, the structure of combustion chamber is simplified.
Accompanying drawing illustrates:
Fig. 1 is structural representation of the present invention;
Fig. 2 is the air flow direction schematic diagram of the present invention when working.
Wherein, 1-primary holes, 2-afterburning hole, 3-blending hole, 4-igniter installation site, 5-nozzle mounting position, 6-locating hole, 7-exhaust outlet.
Detailed description of the invention
Below by detailed description of the invention, the present invention is described in further detail.
Head in combustion chamber is circumferentially axially uniformly distributed 8 larger holes, 8 apertures are uniformly distributed in the circumference in each hole in 8 holes, 8 flood nozzle are equipped with in 8 larger holes, it is physically the swirl atomizer of depended on pressure atomization, be used for supply combustion chamber atomized fuel, 8 apertures are around used for cooling jet and blow down carbon deposit.
In combustion chamber axially, from head, outer shroud has 5 rounds, first row and second row are primary holes, this two round is staggered and has the oblique head of the angle of 30 ° with axial, produces eddy flow, form recirculating zone at head when this angle makes air-flow enter combustion chamber, can stabilize the flame during burning, maintain combustion chamber and successively burn.The air entered by this two round forms the primary zone of combustion chamber.3rd row and the 4th row are afterburning hole, and are staggered, and this some holes supplements to combustion chamber the afterburning district that corresponding air forms combustion chamber, plays cooling wall simultaneously.Last row is blending hole, enters air and the high-temperature hot gas mixing of combustion chamber, reduces the temperature of combustor exit air-flow.
Meanwhile, combustion chamber inner ring has 4 rounds, and role is identical with the effect in hole on outer shroud respectively, and the air after dilution zone, not only temperature is down to the temperature that turbine can bear, and temperature distribution uniform.Combustion chamber radial direction also has 3 locating holes, the radial hole also having a dress ignition electric nozzle.
The form of combustion chamber is annular return combustion chamber, casing forms the lateral wall of chamber cavity, chamber cavity is formed by casing and axle sleeve, the air-flow of blower outlet is first through the rear portion of combustion chamber, then head of combustion chamber is flowed to, and the air-flow of combustion chamber flows from head to rear portion, combustion chamber, be therefore backflow, air flow direction is shown in Fig. 2.For small-sized reverse flow type combustor, the existence of air admission hole makes the air-flow entered in burner inner liner produce eddy flow, thus plays the effect stabilized the flame.
The more general chamber structure of this annular return combustion chamber flame drum is simple, compact, lightweight, has important meaning to the development of small-sized engine combustion chamber, and has certain versatility and good practical value.
Claims (1)
1. an annular return combustion chamber flame drum, entirety is annular tubular structure, it is distributed with primary holes (1), afterburning hole (2), blending hole (3), igniter installing hole (4), nozzle installing hole (5), locating hole (6), it is characterized in that: burner inner liner inner ring divides circumferential cloth one to arrange primary holes (1) totally 48 near nozzle installing hole (5) position, outer shroud circumference distribution two row's primary holes (1), often arrange 32, outer shroud primary holes and burner inner liner are axially in 30 ° of angles, outer shroud and inner ring circumference distribution simultaneously two row afterburning hole (2), outer shroud often arranges 32, and inner ring often arranges each 24, front portion, outer shroud afterburning hole (2) is blending hole (3), and circumference 16 is uniform, by locating hole (6), burner inner liner and casing are fixed, and casing and the concentricity axle of burner inner liner, air-flow out enters the gap area of casing and burner inner liner from compressor, then by primary holes (1), afterburning hole (2) and blending hole (3) enter burner inner liner inside, the nozzle installing hole (5) of burner inner liner head is provided with fuel nozzle, fuel oil feeds in burner inner liner by nozzle, igniter installing hole (4) is provided with igniter, light the fuel air mixture in burner inner liner, gas after burning in burner inner liner through the backflow of 180 °, discharge from exhaust outlet (7) and enter nozzle ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420752874.8U CN204460285U (en) | 2014-12-03 | 2014-12-03 | A kind of annular return combustion chamber flame drum |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420752874.8U CN204460285U (en) | 2014-12-03 | 2014-12-03 | A kind of annular return combustion chamber flame drum |
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| Publication Number | Publication Date |
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| CN204460285U true CN204460285U (en) | 2015-07-08 |
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| CN201420752874.8U Active CN204460285U (en) | 2014-12-03 | 2014-12-03 | A kind of annular return combustion chamber flame drum |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108139077A (en) * | 2015-10-06 | 2018-06-08 | 赛峰直升机发动机公司 | For the annular combustion chamber of turbogenerator |
| CN108561896A (en) * | 2018-03-15 | 2018-09-21 | 西北工业大学 | A kind of tiny engine burner inner liner with twin-stage guide vane |
| CN108825380A (en) * | 2018-05-28 | 2018-11-16 | 华中科技大学 | A kind of high efficiency turboshaft engine |
| CN108954387A (en) * | 2018-08-08 | 2018-12-07 | 北京航空航天大学 | A kind of micro gas turbine engine and its chamber assembly that burns |
| CN110186069A (en) * | 2019-05-31 | 2019-08-30 | 中国航发湖南动力机械研究所 | Burning heater |
| CN112815357A (en) * | 2020-12-24 | 2021-05-18 | 北航（四川）西部国际创新港科技有限公司 | Flame tube structure of combustion chamber and combustion chamber |
-
2014
- 2014-12-03 CN CN201420752874.8U patent/CN204460285U/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108139077A (en) * | 2015-10-06 | 2018-06-08 | 赛峰直升机发动机公司 | For the annular combustion chamber of turbogenerator |
| CN108139077B (en) * | 2015-10-06 | 2020-09-15 | 赛峰直升机发动机公司 | Annular combustion chamber for a turbine engine |
| US10895383B2 (en) | 2015-10-06 | 2021-01-19 | Safran Helicopter Engines | Ring-shaped combustion chamber for a turbine engine |
| CN108561896A (en) * | 2018-03-15 | 2018-09-21 | 西北工业大学 | A kind of tiny engine burner inner liner with twin-stage guide vane |
| CN108561896B (en) * | 2018-03-15 | 2020-04-10 | 西北工业大学 | Take doublestage guide vane's miniature engine flame tube |
| CN108825380A (en) * | 2018-05-28 | 2018-11-16 | 华中科技大学 | A kind of high efficiency turboshaft engine |
| CN108825380B (en) * | 2018-05-28 | 2020-05-19 | 华中科技大学 | Turboshaft engine |
| CN108954387A (en) * | 2018-08-08 | 2018-12-07 | 北京航空航天大学 | A kind of micro gas turbine engine and its chamber assembly that burns |
| CN110186069A (en) * | 2019-05-31 | 2019-08-30 | 中国航发湖南动力机械研究所 | Burning heater |
| CN112815357A (en) * | 2020-12-24 | 2021-05-18 | 北航（四川）西部国际创新港科技有限公司 | Flame tube structure of combustion chamber and combustion chamber |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |