CN204176685U - The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner - Google Patents
The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner Download PDFInfo
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- CN204176685U CN204176685U CN201420562238.9U CN201420562238U CN204176685U CN 204176685 U CN204176685 U CN 204176685U CN 201420562238 U CN201420562238 U CN 201420562238U CN 204176685 U CN204176685 U CN 204176685U
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Abstract
The utility model belongs to gas turbine field, disclose the double-deck gaseous film control structure of a kind of gas-turbine combustion chamber burner inner liner, burner inner liner wall is formed by connecting by multistage gaseous film control wall, gaseous film control wall is provided with film cooling holes, the inner side of gaseous film control wall is connected with outside air film ring, and the inner side of outside air film ring is connected with inner side air film ring; Described outside air film ring is provided with outer shroud Cooling Holes, and described inner side air film ring is provided with inner ring Cooling Holes.The utility model, by arranging double-deck gaseous film control structure, enhances the cooling effectiveness of burner inner liner internal face, reduces the temperature of burner inner liner local, reduces thermal stress; Multistage gaseous film control wall is arranged continuously, takes full advantage of cooling-air, can cover more large-area burner inner liner wall, enhance cooling effect; Refrigerating gas is divided into multiply to flow into, and improves mixing rate and the mixed effect of fuel, improves efficiency of combustion, reduce ignition temperature, is conducive to reducing to pollute.
Description
Technical field
The utility model relates to gas turbine technology field, particularly the double-deck gaseous film control structure of a kind of gas-turbine combustion chamber burner inner liner.
Background technology
Gas turbine comprises compressor, combustion chamber, the large parts of turbine three.Wherein, the highest temperature zone of gas turbine is present in combustion chamber, and chemical energy, as the fuel gas buring parts connecting compressor and turbine, is heat energy by combustion chamber, hot-air is passed into turbine acting.At chamber front end, fuel nozzle is housed, the fuel of nozzle ejection is with the air entered in combustion chamber combustion, and ignition temperature can reach more than 2000 degrees Celsius, and pressure can reach 20 atmospheric pressure.Combustion chamber outer shell is at high temperature difficult to bear such high pressure.For reducing the temperature of combustion chamber casing wall, to ensure its intensity, usually in combustion chamber, establishing burner inner liner, reducing outer shell and being heated, making its main pressure-bearing.
Burner inner liner generally adopts high-temperature alloy to make, the normal working temperature of current burner inner liner metal material is all below 1000 degrees Celsius, but the ignition temperature of combustion chamber can reach more than 2000 degrees Celsius, therefore must cool burner inner liner, and whether cooling structure setting is reasonable, very large on the working life impact of burner inner liner.Mode at present for the basic cylinder cooling of gas turbine flame mainly contains: gaseous film control, disperse cooling, impact to disperse and combine cooling, laminate cooling etc., general principle is be introduced in burner inner liner by a part of cold air from ring cavity combustion chamber mostly, air film is formed at burner inner liner inwall, cooling flame cylinder inwall, can isolate hot combustion gas and burner inner liner on the other hand on the one hand.Good cooling structure should be able to be formed inside burner inner liner be evenly distributed, turbulivity is low, adherent good air film, and air film can be avoided to superpose blocked up and affect burning tissues simultaneously.
In real work, due to the impact by film cooling holes cooling effectiveness, air film often cannot cover whole burner inner liner inwall; At the tail end of air film, i.e. air film ring region, the easy ablation air film ring of the high-temperature gas in burner inner liner and flame tube wall, cause burner inner liner wall burn or crack.
Existing publication number is the patent of CN101675227A, have employed double-deck wall cooling structure, burner inner liner is made double-decker, expand the cooling-air circulation area of burner inner liner upper wall surface, improve cooling effectiveness, but for the gentle zona in region itself that air film ring and burner inner liner wall join, still there is the problem of hot-spot, the defect such as easily to crack.
Utility model content
(1) technical problem that will solve
The technical problems to be solved in the utility model is: for the air film tail end solving existing combustion barrel easily forms air film ring, high-temperature gas ablation in easy burned cylinder, the effect cooling and isolate high-temperature gas cannot be realized, cause combustion barrel to be burnt or occur the problem of crackle.
(2) technical scheme
In order to solve the problems of the technologies described above, the utility model provides the double-deck gaseous film control structure of a kind of gas-turbine combustion chamber burner inner liner, burner inner liner wall is formed by connecting by multistage gaseous film control wall, gaseous film control wall is provided with film cooling holes, the inner side of gaseous film control wall is connected with outside air film ring, the inner side of outside air film ring is connected with inner side air film ring, described gaseous film control wall and outside air film ring, all leaves space between outside air film ring and inner side air film ring; The rear end of described outside air film ring is connected with gaseous film control wall, on the air film ring of described outside, and is positioned at the rear side of film cooling holes, is provided with outer shroud Cooling Holes; The front end of described inner side air film ring is connected with the front end of outside air film ring, on the air film ring of described inner side, and is positioned at the front side of outer shroud Cooling Holes, is provided with inner ring Cooling Holes.
Wherein, described outside air film ring and inner side air film ring are all tangent with the circumference at burner inner liner wall place.
Wherein, the center line of described outer shroud Cooling Holes and the angle of outside air film ring are first-class to angle, and the described first-class angular range to angle is 30 ~ 60 degree.
Wherein, the center line of described inner ring Cooling Holes and the angle of inner side air film ring be second to angle, described second is 30 ~ 60 degree to the angular range of angle.
Wherein, gas outside burner inner liner wall enters inside burner inner liner wall through inner ring Cooling Holes, the direction of rotation of incline direction air-flow inside burner inner liner wall of described inner ring Cooling Holes, makes the gas flowed into by inner ring Cooling Holes can continue flowing by the gas inside burner inner liner wall.
Wherein, described gaseous film control wall is corrugated, and in it, recess and outside air film ring are welded to connect.
Wherein, the front end of described inner side air film ring is provided with bending segment, and end and the outside air film ring of described bending segment are welded to connect.
(3) beneficial effect
The double-deck gaseous film control structure of the utility model gas-turbine combustion chamber burner inner liner, compared with prior art, has the following advantages and high-lighting effect:
(1) by arranging double-deck air film ring and arranging Cooling Holes thereon, effectively enhance the cooling effectiveness of air film ring and burner inner liner internal face, reduce the temperature of burner inner liner local, reduce thermal stress;
(2) multistage gaseous film control wall is arranged continuously, every section of gaseous film control wall is equipped with double-deck gaseous film control structure, and refrigerating gas flows respectively to front and back, takes full advantage of cooling-air, more large-area burner inner liner wall can be covered, enhance cooling effect;
(3) refrigerating gas is divided into multiply to flow rapidly into, and multiply refrigerating gas, from multiple directions and inner contacts combustion gases, improves mixing rate and the mixed effect of fuel, improves efficiency of combustion, reduce ignition temperature, is conducive to reducing to pollute.
Accompanying drawing explanation
Fig. 1 is one of structural representation of the double-deck gaseous film control structure of the utility model gas-turbine combustion chamber burner inner liner;
Fig. 2 is the close-up schematic view of A in Fig. 1;
Fig. 3 is many structural representations two of the double-deck gaseous film control structure of the utility model gas-turbine combustion chamber burner inner liner;
Fig. 4 is the global sections schematic diagram of the utility model Flame cylinder.
Wherein, 11, burner inner liner wall; 12, gaseous film control wall; 13, film cooling holes; 14, outside air film ring; 15, outer shroud Cooling Holes; 16, inner side air film ring; 17, pad; 18, inner ring Cooling Holes; α, first-class to angle; β, the first circumferential inclination angle; γ, second are to angle; θ, second week are to inclination angle.
Detailed description of the invention
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
For ease of describing, before the direction of arrow in Fig. 1 is defined as.
The chamber temperature of gas turbine is higher, for reducing the temperature of combustion chamber outer shell, generally can arrange burner inner liner in combustion chamber, and outside burner inner liner, logical refrigerating gas, is burning gases inside burner inner liner.As shown in Figure 1-2, the double-deck gaseous film control structure of a kind of gas-turbine combustion chamber burner inner liner of the utility model, it mainly comprises burner inner liner wall 11, viewed from the cross-wise direction figure, burner inner liner wall 11 is the cirque structures be formed by connecting by multiple gaseous film control wall 12, the inner side of every section of gaseous film control wall 12 is all connected with outside air film ring 14, and be connected with inner side air film ring 16 inside outside air film ring 14, the portion other than connected portion between three all leaves space; Gaseous film control wall 12 is waveform, the rear end of outside air film ring 14 is welded on trough place, the i.e. inwardly protruded part of gaseous film control wall 12, front end and gaseous film control wall 12 time of outside air film ring 14 leave gap, gas is facilitated to circulate, the part of gaseous film control wall 12 corresponding outside air film ring 14 is provided with film cooling holes 13, and outside air film ring 14 is provided with outer shroud Cooling Holes 15, and outer shroud Cooling Holes 15 is positioned at the rear side of film cooling holes 13; The front end of inner side air film ring 16 is provided with bending segment, and the front end of this bending segment and outside air film ring 14 is welded to connect, and both left ends open wide, and inner side air film ring 16 is provided with inner ring Cooling Holes 18, and inner ring Cooling Holes 18 is positioned at the front side of outer shroud Cooling Holes 15.Outside air film ring 14 is all tangent with its place circumference with inner side air film ring 16 or overlap, an angle is had between the internal face of outer shroud Cooling Holes 15 and outside air film ring 14, the i.e. angle of sidewind in the center line of outer shroud Cooling Holes 15 and burner inner liner wall 11, be called first-class to angle α, the first-class scope to angle α is 30 ~ 60 degree; According to process requirements, outer shroud Cooling Holes 15 can be designed to turn forward or tilt backwards, to improve cooling effect during design.Also have an angle between the internal face of inner ring Cooling Holes 18 and inner side air film ring 16, i.e. the angle of sidewind in the center line of inner ring Cooling Holes 18 and burner inner liner wall 11, be called that second is to angle γ, second is 30 ~ 60 degree to the scope of angle γ.
During work, the refrigerating gas outside burner inner liner rotates along a direction, and the burning gases of burner inner liner inside flow in opposite direction inside burner inner liner wall 11.First refrigerating gas enters gaseous film control wall 12 by film cooling holes 13, wherein part refrigerating gas is along gaseous film control wall 12 flow forward, flow out eventually through air film ring 14 front end, outside, by the air film making to be formed between burning gases and gaseous film control wall 12 one deck and flow, realize object that is heat insulation and cooling.The other a part of refrigerating gas entering film cooling holes 13 enters the gap between outside air film ring 14 and inner side air film ring 16 by outer shroud Cooling Holes 15, wherein part refrigerating gas flows backward along the internal face of outside air film ring 14, realizes the object of the gaseous film control wall 12 at cooling outside air film ring 14 and air film ring 14 rear portion, outside; Residual gas through outer shroud Cooling Holes 15 is flowed out by inner ring Cooling Holes 18, wherein a part flows backward, realize the object of cooling inner side air film ring 16, a part of flow forward in addition, realizes the object of the pad 17 of cooling outside air film ring 14 and outside air film ring 14 and inner side air film ring 16.Owing to there being refrigerating gas to pass through in outer shroud Cooling Holes 15 always, hole wall temperature is lower, and the temperature of peripheral wall surface can be made to reduce; Because outer shroud Cooling Holes 15 is arranged on the weakest region of gaseous film control, effectively can reduce the temperature in this region, reduce thermal stress.
As shown in Figure 4, the angle of outer shroud Cooling Holes 15 and inner ring Cooling Holes 18 also can be controlled by circumferential inclination angle, the point at inner ring Cooling Holes 18 or circumference place, outer shroud Cooling Holes 15 place is connected with the center of circle of burner inner liner, the angle of connecting line and outer shroud Cooling Holes 15 center line is called the first circumferential angle of inclination beta, the angle of connecting line and inner ring Cooling Holes 18 center line is called that second week is to inclination angle theta, and the scope of two angles is 30 ~ 60 degree.
Wherein, the incline direction of inner ring Cooling Holes 18 is consistent with the flow direction of burner inner liner combustion gas, namely the refrigerating gas flowed into by inner ring Cooling Holes 18 is made can to continue flow forward along the flowing of burning gases, extend the flow distance of refrigerating gas, realize the object of cooling inner side air film ring 16; Namely the incline direction of inner ring Cooling Holes 18 is along the flow direction of burner inner liner combustion gas, and this arranges when refrigerating gas and burning gases can also be avoided to meet and forms whirlpool, is conducive to the cooling of burner inner liner.
As shown in Figure 3, described outer shroud Cooling Holes 15 can be one, also several holes evenly can be arranged on outside air film ring 14, to increase the flow of refrigerating gas, improve cooling effect; Inner ring Cooling Holes 18 also can be set to multiple, and the refrigerating gas flow flowing to inner side air film ring 16 inner surface is increased, and avoids occurring that inner side air film ring 16 cools the problem of timeliness, ensures the cooling effect of inner side air film ring 16.
As can be seen from the above embodiments, the double-deck gaseous film control structure of a kind of gas-turbine combustion chamber burner inner liner of the utility model, by arranging inner side air film ring 16, outside air film ring 14 double-decker, achieve the object of cooling flame tube wall surface 11, due to refrigerating gas enter burner inner liner wall 11 after flow respectively to front and back, increase cooling range and film-cooled heat, reduce the temperature of burner inner liner local, reduce thermal stress; The cooling structure of multiple gaseous film control wall 12 interacts, cooling blast is made to cover whole burner inner liner wall 11, avoid the phenomenon occurring that part burner inner liner wall 11 cannot cool, thoroughly eliminate burner inner liner wall 11 and burnt crackle even by the appearance of situations such as burning, ensure that the cooling effect of burner inner liner, extend the service life of burner inner liner; Outer shroud Cooling Holes 15 is arranged on the place that air film is the weakest, the wall surface temperature around outer shroud Cooling Holes 15 reduces by the refrigerating gas flowing through outer shroud Cooling Holes 15, reduces local stress; The refrigerating gas flowed rapidly into, makes the flowing velocity of burner inner liner fuel gas faster, improves the mixed effect of fuel gas, improve efficiency of combustion, reduce ignition temperature, reduce pollution.Meanwhile, the surface of medial and lateral air film ring 14 all has refrigerating gas to flow through, and makes it come with the burning gases of heat are isolated, also ensure that the cooling effect of cooling structure self, not easily damaged, extends the service life of burner inner liner further.
The above is only preferred embodiment of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvement and replacement, these improve and replace and also should be considered as protection domain of the present utility model.
Claims (7)
1. the double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner, burner inner liner wall (11) is formed by connecting by multistage gaseous film control wall (12), gaseous film control wall (12) is provided with film cooling holes (13), the inner side of gaseous film control wall (12) is connected with outside air film ring (14), the inner side in outside air film ring (14) is connected with inner side air film ring (16), it is characterized in that, described gaseous film control wall (12) and outside air film ring (14), all space is left between outside air film ring (14) and inner side air film ring (16), the rear end of described outside air film ring (14) is connected with gaseous film control wall (12), on described outside air film ring (14), and be positioned at the rear side of film cooling holes (13), be provided with outer shroud Cooling Holes (15), the front end of described inner side air film ring (16) is connected with the front end in outside air film ring (14), on described inner side air film ring (16), and be positioned at the front side of outer shroud Cooling Holes (15), be provided with inner ring Cooling Holes (18).
2. the double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner as claimed in claim 1, it is characterized in that, described outside air film ring (14) is all tangent with the circumference at burner inner liner wall (11) place with inner side air film ring (16).
3. the double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner as claimed in claim 2, it is characterized in that, the center line of described outer shroud Cooling Holes (15) and the angle in outside air film ring (14) are first-class to angle (α), and the described first-class angular range to angle (α) is 30 ~ 60 degree.
4. the double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner as claimed in claim 2, it is characterized in that, the center line of described inner ring Cooling Holes (18) and the angle of inner side air film ring (16) be second to angle (γ), described second is 30 ~ 60 degree to the angular range of angle (γ).
5. the double-deck gaseous film control structure of the gas-turbine combustion chamber burner inner liner as described in any one of claim 1,2,4, it is characterized in that, the gas in burner inner liner wall (11) outside enters burner inner liner wall (11) inner side through inner ring Cooling Holes (18), the direction of rotation of incline direction sidewind in burner inner liner wall (11) of described inner ring Cooling Holes (18), makes the gas flowed into by inner ring Cooling Holes (18) can continue flowing along the gas of burner inner liner wall (11) inner side.
6. the double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner as claimed in claim 1, it is characterized in that, described gaseous film control wall (12) is corrugated, and in it, recess and outside air film ring (14) are welded to connect.
7. the double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner as claimed in claim 1, it is characterized in that, the front end of described inner side air film ring (16) is provided with bending segment, and end and outside air film ring (14) of described bending segment are welded to connect.
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| CN201420562238.9U CN204176685U (en) | 2014-09-26 | 2014-09-26 | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner |
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| CN201420562238.9U CN204176685U (en) | 2014-09-26 | 2014-09-26 | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN108731030A (en) * | 2018-08-10 | 2018-11-02 | 宁波大艾激光科技有限公司 | A kind of combustion chamber with compound special-shaped groove gaseous film control structure |
| CN108775601A (en) * | 2018-07-04 | 2018-11-09 | 大连派思透平动力科技有限公司 | A kind of inner tube structure suitable for gas turbine reflux tube-type combustion chamber |
| CN109707532A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type active cooling structure |
| CN109707533A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type injection cooling structure |
| WO2021083338A1 (en) * | 2019-10-31 | 2021-05-06 | 芜湖美的厨卫电器制造有限公司 | Gas device |
| 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 |
| CN114110657A (en) * | 2021-11-11 | 2022-03-01 | 中国航发贵阳发动机设计研究所 | Cooling structure for head of flame tube of combustion chamber of middle-thrust aircraft engine |
| CN114151791A (en) * | 2020-09-08 | 2022-03-08 | 国家能源投资集团有限责任公司 | Power generation system and start-stop combustion device thereof |
| CN115111603A (en) * | 2022-05-31 | 2022-09-27 | 哈尔滨工程大学 | Double-wall structure combustion chamber flame tube of micro gas turbine with cooling structure |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN108775601A (en) * | 2018-07-04 | 2018-11-09 | 大连派思透平动力科技有限公司 | A kind of inner tube structure suitable for gas turbine reflux tube-type combustion chamber |
| CN108775601B (en) * | 2018-07-04 | 2024-05-10 | 大连欧谱纳透平动力科技有限公司 | Inner cylinder structure suitable for gas turbine backflow cylinder type combustion chamber |
| CN108731030A (en) * | 2018-08-10 | 2018-11-02 | 宁波大艾激光科技有限公司 | A kind of combustion chamber with compound special-shaped groove gaseous film control structure |
| CN108731030B (en) * | 2018-08-10 | 2024-02-13 | 宁波大艾激光科技有限公司 | Combustion chamber with composite special-shaped groove air film cooling structure |
| CN109707532A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type active cooling structure |
| CN109707533A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type injection cooling structure |
| WO2021083338A1 (en) * | 2019-10-31 | 2021-05-06 | 芜湖美的厨卫电器制造有限公司 | Gas device |
| CN114151791B (en) * | 2020-09-08 | 2023-11-03 | 国家能源投资集团有限责任公司 | Power generation system and start-stop combustion device thereof |
| CN114151791A (en) * | 2020-09-08 | 2022-03-08 | 国家能源投资集团有限责任公司 | Power generation system and start-stop combustion device thereof |
| 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 |
| CN114110657A (en) * | 2021-11-11 | 2022-03-01 | 中国航发贵阳发动机设计研究所 | Cooling structure for head of flame tube of combustion chamber of middle-thrust aircraft engine |
| CN115111603B (en) * | 2022-05-31 | 2023-09-29 | 哈尔滨工程大学 | Combustion chamber flame tube with cooling structure for miniature gas turbine and double-layer wall structure |
| CN115111603A (en) * | 2022-05-31 | 2022-09-27 | 哈尔滨工程大学 | Double-wall structure combustion chamber flame tube of micro gas turbine with cooling structure |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Double-layer gas film cooling structure of gas turbine combustor flame cylinder Effective date of registration: 20161104 Granted publication date: 20150225 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150225 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right |