CN202419699U - Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber - Google Patents
Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber Download PDFInfo
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- CN202419699U CN202419699U CN2011205583145U CN201120558314U CN202419699U CN 202419699 U CN202419699 U CN 202419699U CN 2011205583145 U CN2011205583145 U CN 2011205583145U CN 201120558314 U CN201120558314 U CN 201120558314U CN 202419699 U CN202419699 U CN 202419699U
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- inner liner
- burner inner
- flame tube
- tube wall
- inclined hole
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Abstract
The utility model provides a multi-inclined-hole flame tube wall plate. A plurality of inclined holes which are uniformly distributed and penetrate through the flame tube wall plate are arranged on the flame tube wall plate, and mixing angles of the inclined holes are gradually reduced along the length direction of the flame tube wall plate. The utility model also provides a flame tube formed by the multi-inclined-hole flame tube wall plates and a gas turbine combustion chamber including the flame tube. The problem of non-uniform wall surface cooling effect caused by non-uniform thickness of a gas film next to the flame tube wall surface is solved, and the temperature distribution of the flame tube wall surface is more uniform; and meanwhile, the heat stress of the flame tube wall surface is reduced, and the service life of the flame tube wall surface is prolonged.
Description
Technical field
The utility model relates to the gas turbine industrial circle, particularly a kind of many inclined holes burner inner liner wallboard and burner inner liner that is formed by this many inclined holes burner inner liner wallboard and the gas-turbine combustion chamber that comprises this burner inner liner.
Background technology
The highest temperature zone of gas turbine is the combustion chamber; The primary zone fuel gas temperature of combustion chamber can be up to 2400K; And flame tube wall metal material normal working temperature is no more than 1300K at present, and material can't bear in far away surpassing under the adverse circumstances of its normal working temperature and work long hours, and therefore must combustion chamber flame drum be cooled off; Reduce the combustion chamber life-span to prevent burner inner liner from being burnt out, and then reduce engine life.The basic type of cooling that is used for the combustion chamber flame drum cooling at present has air film cooling, the cooling of convection current air film, impacts the air film cooling, disperses cooling and laminate cooling etc.; Its basic cooling principle all is a cold air inside and outside the combustion chamber, and ring cavity gets in the burner inner liner; Form one deck air film in the burner inner liner inner wall surface; Air film is close to the burner inner liner internal face and is flowed, and air film plays cooling wall and isolates the effect that the burner inner liner wall is washed away in combustion gas.High-quality air film can effectively utilize cold gas, and obtains high gas film cooling efficiency, and wherein air film is that the adherent effect of air film is the leading indicator that characterizes the air film quality near the degree of two-dimensional flow.
Along with the development of aero engine technology, aero-engine compressor pressure ratio and combustion chamber out temperature all significantly improve.The operating pressure and the temperature of advanced combustion chamber constantly increase, and this must cause the suffered thermic load of combustion chamber flame drum sharply to increase.Along with the raising of design parameter, the blower outlet air themperature can be up to 800～900K.As cold gas, its potential cooling capacity descends with this high temperature compressed air, thereby required cooling gas flow increases.In order to make gas turbine obtain higher efficient, to improve the outlet temperature of combustion chamber as far as possible usually, now at the fuel gas temperature of combustor exit up to 1300K to 1800K.The raising of the outlet temperature of combustion chamber makes the consumption of turbo blade cold gas increase, and this part cold gas directly gets into turbine, not through burner inner liner, thereby has reduced the available air flow that the burner inner liner air film cools off.The available cooling tolerance of present high temperature rise combustor has only 20%～30% of total air, and advanced combustion chamber flame drum cools off between the minimizing of increase and available cooling tolerance of required cooling tolerance and has contradiction.For addressing this problem, except continuous development new material and new technology, one of deciding factor is exactly that burner inner liner is adopted advanced efficient cooling technology, utility model, the better air film cooling of application geometry.Through the improvement of geometry, when reaching the expection cooling effect, effectively reduce the flow of cold gas.The air film cooling structure should be made every effort to air film and is evenly distributed, and turbulence intensity is low, and is even along the axial cooling effect of burner inner liner, reduces thermal stress, and crackle and flexural deformation appear in burner inner liner under the condition of high temperature to avoid.
Fig. 1 a-1c shows the burner inner liner wallboard 100 that adopts the conventional film cooling structure; Air film hole 200 on the burner inner liner wallboard 100 is arranged and perpendicular to the burner inner liner wall in order; The air-flow that gets into burner inner liner from air film hole constantly superposes; Cause near the cooling air film burner inner liner internal face thickening that constantly superposes, influence the burning tissue in the burner inner liner, cause burner inner liner cooling effect inequality vertically simultaneously.Specifically, there is following several respects problem:
1. the flame tube wall consumption of conventional film cooling structure cooling tolerance is more relatively, and serious along the waste of burner inner liner axial downstream cold gas, it is bigger to cause overall efficiency to reduce;
2. the air-flow that gets into burner inner liner from air film hole constantly superposes, and causes near the cooling air film burner inner liner internal face thickening that constantly superposes, and air-film thickness increases vertically gradually, has taken the more combustion volume in combustion chamber, and the active combustion volume is diminished;
3. the flame tube wall perforate quantity of conventional film cooling structure is more, causes the flame tube wall structural strength to reduce, and causes processing cost higher simultaneously;
4. the flame tube wall wall temperature of conventional film cooling structure axially descends rapidly along burner inner liner; Cause higher burner inner liner wall temperature gradient, produce higher thermal stress, excessive thermal stress can cause faults such as warpage and the crackle of wall; Influence burner inner liner service life, reduce the reliability that burner inner liner uses.
In a word; In order to improve burner inner liner cooling effect and the service life that prolongs burner inner liner, also need develop the air film cooling structure of optimization, improve the efficient and the cooling uniformity of air film cooling; Improve the adherent effect of air film, reduce required cooling gas flow, reduce the burner inner liner pressure loss.
The utility model content
In order to address the above problem, the utility model provides a kind of novel flame barrel structure, and it has the air film cooling structure of optimization.
First aspect according to the utility model; A kind of many inclined holes burner inner liner wallboard is provided; Have even distribution on the said burner inner liner wallboard and run through a plurality of inclined holes of said burner inner liner wallboard, the blending angle of said inclined hole reduces along the length direction of said burner inner liner wallboard gradually.
Wherein, the blending angle of said inclined hole is between 0～90 °.
Wherein, the aperture of said inclined hole is between 0.1～2mm.
Second aspect according to the utility model provides a kind of burner inner liner, and said burner inner liner adopts foregoing burner inner liner wallboard to form, and the blending angle of said inclined hole flow direction of air-flow in the said burner inner liner reduces gradually.
Wherein, Said inclined hole said burner inner liner axially on be divided into first area, second area, the 3rd zone and the 4th zone; The length of said burner inner liner is L, and first area, second area, the 3rd zone and four-range length are respectively L1=0.2L, L2=0.2L, L3=0.1L, L4=0.5L.
In said first area, the blending angle of said inclined hole is decremented to 65 ° from 90 °;
In said second area, the blending angle of said inclined hole is decremented to 45 ° from 65 °;
In said the 3rd zone, the blending angle of said inclined hole is decremented to 5 ° from 45 °;
In said the 4th zone, the blending angle of said inclined hole is 0 °.
The 3rd aspect according to the utility model provides a kind of gas-turbine combustion chamber, is provided with according to foregoing burner inner liner in the said combustion chamber.
Adopt the said scheme of the utility model, can the application feature of burner inner liner improved in many aspects:
1. under the prerequisite that guarantees the flame tube wall cooling effect, reduce the cold gas consumption of burner inner liner, improved overall efficiency.Simultaneously, for further improving burner inner liner internal combustion temperature from now on, reserved more available cooling tolerance;
2. reduce air-film thickness growth gradually vertically, improved the capacity utilization of combustion chamber;
3. improve cooling effect, reduced the quantity of inclined hole indirectly, thereby avoided flame tube wall intensity to reduce too much, reduced processing cost;
4. improved the uneven problem of wall cooling effect that near the air-film thickness inequality of burner inner liner wall causes; Make flame tube wall surface temperature more even distribution; Reduced burner inner liner wall temperature gradient; Avoid too high thermal stress, avoided causing the fault such as warpage and crackle of wall, improved burner inner liner service life.
Description of drawings
Fig. 1 a is the stereogram of traditional burner inner liner wallboard;
Fig. 1 b is the vertical view of flame tube wall plate among Fig. 1 a;
Fig. 1 c be among Fig. 1 b the flame tube wall plate along the cutaway view of A-A;
Fig. 2 is the sketch map of typical gas-turbine combustion chamber;
Fig. 3 shows the blending angle β of the inclined hole on the burner inner liner wallboard;
Fig. 4 a is the stereogram according to the burner inner liner wallboard of the preferred embodiment of the utility model;
Fig. 4 b is the vertical view of flame tube wall plate among Fig. 4 a;
Fig. 4 c is the partial enlarged drawing of the C portion of flame tube wall plate among Fig. 4 b;
Fig. 5 is the operation principle sketch map of many inclined holes flame tube wall.
The specific embodiment
Describe the preferred embodiment according to the burner inner liner wallboard of the utility model in detail below in conjunction with accompanying drawing, the axis direction that axially is meant burner inner liner among the figure and in describing below circumferentially is meant the circumferencial direction of burner inner liner.
Fig. 2 is the sketch map of typical gas-turbine combustion chamber, shows typical gas-turbine combustion chamber 10.Combustion chamber 10 is through producing the required combustion gas of driving turbine rotation at confined space internal combustion air and fuel.Be in operation, burn in burner inner liner 20 from compressed air in the compressor and fuel, the fuel gas temperature that burning produces is greatly about 1800～2400K.These high-temperature fuel gas are reduced to 1400～1800K with mix the back temperature from the cold gas of flame tube wall, and then combustion gas flows into turbine and promotes turbine rotation with high speed from guider 30.Because the high-temperature fuel gas temperature that burning produces far above the normal working temperature of flame tube wall, therefore need be cooled off the burner inner liner wall.
Fig. 3 shows the blending angle β of the inclined hole on the burner inner liner wallboard.Fig. 4 a-4c shows a preferred embodiment according to the burner inner liner wallboard of the utility model.Have even distribution on the burner inner liner wallboard 1 and run through a plurality of inclined holes 2 of burner inner liner wallboard 1, the blending angle β of inclined hole 2 reduces along the length direction of burner inner liner wallboard 1 gradually.Here, blending angle β is meant the projection of axis on burner inner liner wallboard 1 and the angle of x direction (promptly axial) of inclined hole 2, and length direction is identical with the axis direction of the burner inner liner of formation.According to the utility model, inclined hole 2 can be cylindrical hole, and its aperture is between 0.1～2mm, and the blending angle β of inclined hole 2 is between 0～90 °.
In the embodiment shown in Fig. 4 a-4c, the size of blending angle β flow direction of air-flow in the burner inner liner reduces gradually, that is, and and β 1＞β 2＞β 3.Certainly, also can there be the identical situation of blending angle β in the subregion, but the trend that the flow direction of air-flow becomes to reduce in the burner inner liner substantially.In the present embodiment; Burner inner liner length overall vertically is L; Can be divided into 4 sections that L1, L2, L3, L4 are uneven in length vertically; The length of L1, L2, L3, each section of L4 is all between (0～0.5) L, and the blending angle that L1, L2, L3, each section of L4 are gone up inclined hole is respectively β 1, β 2, β 3, β 4, and β 1, β 2, β 3, β 4 angular dimensions can be between 0～80 °; Along being parallel to axial main flow direction, upstream orifice row's blending angle is greater than downstream aperture row's blending angle, and promptly β 1＞β 2＞β 3＞β 4.Preferably, the axial spacing of inclined hole is 3.5mm, and the circumferential spacing of inclined hole is 5.5mm, L1=0.2L, L2=0.2L, L3=0.1L, L4=0.5L.Wherein, in the L1 section, β 1 is reduced to 65 ° from 90 ° of linearities vertically; In the L2 section, β 2 is reduced to 45 ° from 65 ° of linearities; In the L3 section, β 3 is reduced to 5 ° from 45 ° of linearities, in the L4 section, and β 4=0 °.Adopt this arrangement can reduce the blending effect that gets into the cold gas of burner inner liner from air film hole vertically gradually, reduce the turbulence intensity that gets into the air-flow of burner inner liner from air film hole, reduce the cold gas film thickness, thereby reduce the thermal stress of flame tube wall.
Fig. 5 is the operation principle sketch map of many inclined holes flame tube wall.The wall both sides of the burner inner liner that is formed by burner inner liner wallboard 1 are respectively high-temperature fuel gas main flow and cooling blast, and cooling blast gets into the combustion gas main flows through the inclined hole on the flame tube wall 2.Air-flow forms the lower air film of one deck temperature near the flame tube wall of pressing close to the main flow zone, flame tube wall is not directly contacted with combustion gas, reduces the heats of combustion gas main flow to flame tube wall.For traditional cooling wall structure, the air-flow that gets into burner inner liner from air film hole constantly superposes, and causes near the cooling air film burner inner liner internal face thickening that constantly superposes; Air-film thickness increases vertically gradually; Cooling effect is uneven vertically, produces bigger thermal stress, influences the burner inner liner life-span.And the utility model has improved the uneven problem of wall cooling effect that near the air-film thickness inequality of burner inner liner wall causes; Make flame tube wall surface temperature more even distribution; Reduced burner inner liner wall temperature gradient; Avoid too high thermal stress, avoided causing the fault such as warpage and crackle of wall, improved burner inner liner service life.
Specific embodiment described in the utility model is merely the preferred embodiment of the utility model, is not the practical range that is used for limiting the utility model.Be that all equivalences of doing according to the content of the utility model claim change and modification, all belong to the protection domain of the utility model.
Claims (7)
1. the wallboard of inclined hole burner inner liner more than a kind is characterized in that, has even distribution on the said burner inner liner wallboard and runs through a plurality of inclined holes of said burner inner liner wallboard, and the blending angle of said inclined hole reduces along the length direction of said burner inner liner wallboard gradually.
2. burner inner liner wallboard according to claim 1 is characterized in that, the blending angle of said inclined hole is between 0～90 °.
3. burner inner liner wallboard according to claim 1 is characterized in that the aperture of said inclined hole is between 0.1～2mm.
4. a burner inner liner is characterized in that, said burner inner liner adopts that each described burner inner liner wallboard forms in the claim 1 to 3, and the blending angle of said inclined hole flow direction of air-flow in the said burner inner liner reduces gradually.
5. burner inner liner according to claim 4; It is characterized in that; Said inclined hole said burner inner liner axially on be divided into first area, second area, the 3rd zone and the 4th zone; The length of said burner inner liner is L, and first area, second area, the 3rd zone and four-range length are respectively L1=0.2L, L2=0.2L, L3=0.1L, L4=0.5L.
6. burner inner liner according to claim 5 is characterized in that,
In said first area, the blending angle of said inclined hole is decremented to 65 ° from 90 °;
In said second area, the blending angle of said inclined hole is decremented to 45 ° from 65 °;
In said the 3rd zone, the blending angle of said inclined hole is decremented to 5 ° from 45 °;
In said the 4th zone, the blending angle of said inclined hole is 0 °.
7. a gas-turbine combustion chamber is characterized in that, is provided with in the said combustion chamber according to each described burner inner liner in the claim 4 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205583145U CN202419699U (en) | 2011-12-28 | 2011-12-28 | Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205583145U CN202419699U (en) | 2011-12-28 | 2011-12-28 | Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber |
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| Publication Number | Publication Date |
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| CN202419699U true CN202419699U (en) | 2012-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205583145U Expired - Lifetime CN202419699U (en) | 2011-12-28 | 2011-12-28 | Multi-inclined-hole flame tube wall plate, flame tube and gas turbine combustion chamber |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| WO2016095157A1 (en) * | 2014-12-18 | 2016-06-23 | 深圳智慧能源技术有限公司 | Combustion chamber having porous flame tube |
| CN109340825A (en) * | 2018-09-20 | 2019-02-15 | 西北工业大学 | A kind of flame combustion chamber tube wall surface using novel convex wall inclined hole |
| CN112146127A (en) * | 2020-08-13 | 2020-12-29 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN112833424A (en) * | 2021-01-08 | 2021-05-25 | 西北工业大学 | Novel volute type combustion chamber flame tube wall surface structure |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
-
2011
- 2011-12-28 CN CN2011205583145U patent/CN202419699U/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| CN104197373B (en) * | 2014-08-26 | 2016-04-06 | 南京航空航天大学 | A kind of aeroengine combustor buring room adopting variable cross-section step type effusion wall cooling structure |
| WO2016095157A1 (en) * | 2014-12-18 | 2016-06-23 | 深圳智慧能源技术有限公司 | Combustion chamber having porous flame tube |
| CN109340825A (en) * | 2018-09-20 | 2019-02-15 | 西北工业大学 | A kind of flame combustion chamber tube wall surface using novel convex wall inclined hole |
| CN112146127A (en) * | 2020-08-13 | 2020-12-29 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN112146127B (en) * | 2020-08-13 | 2022-04-08 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN112833424A (en) * | 2021-01-08 | 2021-05-25 | 西北工业大学 | Novel volute type combustion chamber flame tube wall surface structure |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
| CN115493163B (en) * | 2022-09-06 | 2024-02-20 | 清华大学 | Combustion chamber flame tube and high-efficiency cooling method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120905 |