CN203464332U - Transition section of combustion chamber of combustion gas turbine - Google Patents
Transition section of combustion chamber of combustion gas turbine Download PDFInfo
- Publication number
- CN203464332U CN203464332U CN201320548244.4U CN201320548244U CN203464332U CN 203464332 U CN203464332 U CN 203464332U CN 201320548244 U CN201320548244 U CN 201320548244U CN 203464332 U CN203464332 U CN 203464332U
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- China
- Prior art keywords
- changeover portion
- transition section
- combustion chamber
- cooling holes
- gas
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- 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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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 24
- 230000007704 transition Effects 0.000 title abstract description 11
- 239000000567 combustion gas Substances 0.000 title abstract description 8
- 238000001816 cooling Methods 0.000 claims abstract description 71
- 238000002156 mixing Methods 0.000 claims abstract description 34
- 239000002737 fuel gas Substances 0.000 claims description 22
- 239000012528 membrane Substances 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 abstract description 16
- 230000000694 effects Effects 0.000 abstract description 8
- 230000008646 thermal stress Effects 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 abstract 1
- 239000002356 single layer Substances 0.000 abstract 1
- 238000005192 partition Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 230000007547 defect Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 208000037656 Respiratory Sounds Diseases 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000002679 ablation Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 239000003570 air Substances 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 239000003085 diluting agent Substances 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000877 morphologic effect Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a transition section of a combustion chamber of a combustion gas turbine and relates to structural design of the combustion chamber of the combustion gas turbine. The transition section comprises an inlet annulus shell, a transition section body and an outlet ring fan-shaped shell, wherein a plurality rows of gas film cooling holes which penetrate through a wall plate are formed in the wall plate of the transition section body; mixing angles alpha of the gas film cooling holes are within 30-90 degrees; the mixing angles alpha are gradually reduced in the gas flowing direction inside the transition section; the transition section body is divided into three unequal sections with different lengths in the horizontal direction; the mixing angle of each section is reduced in the gas flowing direction in a linear manner. Cooling flow enters the inclined gas film cooling holes from a cooling side to form gas film cover on a hot side, and cooling is provided for a single-layer transition section. By adopting the transmission section, the problems that the temperature of the wall surface of the transition section is too high and is not uniformly distributed are effectively solved, the thermal stress of the wall surface is reduced, and the cooling effect is improved, so that the number of the gas film cooling holes is reduced, and the structural strength of the wall surface of the transition section is improved.
Description
Technical field
The utility model relates to gas-turbine combustion chamber structure, particularly a kind of structural design of gas-turbine combustion chamber changeover portion.
Background technology
Typical gas turbine is comprised of compressor, combustion chamber, turbine and auxiliary system, and a plurality of combustion chambers are centered around peritrochanteric ringwise.Compressor compressed air, enters in combustion chamber and burns with fuel mix, and then combustion gas enters turbine acting.Changeover portion is accepted combustion chamber flame drum and turbine, and after burner inner liner blending is cooling, temperature is up to 1400～1800K in the combustion gas of passing through, and changeover portion has complicated unique three-D space structure.Its import cross sectional shape is consistent with burner inner liner, is circle; Outlet is connected with some combustion chambers, forms described turbine one-level stator blade annular entrance, and it is fan-shaped that single changeover portion outlet is ring.In spatial distribution, combustion chamber is arranged on the outside of gas turbine conventionally, causes changeover portion on radial direction, also to have certain variation, and two ends section type heart height differs, and need in limited axial length, complete by circle to the fan-shaped Morphological Transitions of ring.In the design process of changeover portion, must note Rational structure moulding, prevent from geometrically occurring violent variation, to avoid occurring larger aerodynamic loss; Meanwhile, for bearing the high temperature of combustion gas in combustion chamber, need to adopt air to carry out cooling, cooling technology comprises that laminate is cooling, it is cooling to impact and it is cooling to disperse, thereby reduces thermal stress load and concentrated area.
Along with the development of gas turbine technology, turbine inlet temperature improves gradually.And the metal material normal working temperature that changeover portion adopts is at present no more than 1300K, material cannot bear in far away surpassing under the adverse circumstances of its normal working temperature and work long hours, and therefore must take cooling provision.In disclosed changeover portion patent documentation, there is different advantage and defects in each cooling provision in the past.The amount of the cooling consumption cooling-air of laminated board type is little, has good heat transfer efficiency, and its major defect is: low, the easy oxide of mechanical strength and airborne impurity obstruction etc.Impact cooling major advantage and be mechanical load and thermal force to separate, impingement wall load, body holds heat, makes full use of and impacts the high feature of cooling heat transferring coefficient, but major defect is double wall, has increased the complexity of structure.Disperse cooling by film overcast at wooden partition inner surface, can effectively combustion gas and wooden partition be separated, play good cooling effect, but the conventional cooling thickness due to air film of dispersing can increase by streamwise, thereby produces uniform temperature gradient, cause stress to concentrate.In existing accident, exist changeover portion because serious fracture phenomena appears in unreasonable profile and inner air cooling duct, thereby cause firing machine component failure and shutdown.Need in this case repair and replacement changeover portion or other parts, just can make gas turbine reach duty.Therefore,, under limited cooling-air prerequisite, in order to solve cooling problem, except development new material and new technology, one of deciding factor adopts advanced high efficiency cooling technology to changeover portion exactly.For specific changeover portion structure, it is very necessary applying the cooling geometry of better air film, can make air film be evenly distributed, and turbulence intensity is low, reduces thermal stress, thereby avoids changeover portion under the condition of high temperature to occur crackle, distortion and ablation.
Utility model content
In order to address the above problem, the utility model adopts a kind of gas turbine combustion chamber changeover portion, makes it have good Film Cooling.
The technical solution of the utility model is as follows:
A kind of gas-turbine combustion chamber changeover portion, this changeover portion comprises entrance circular ring shell body and changeover portion body and the fan-shaped housing of discharge ring, described changeover portion body wallboard is provided with the many exhaust membranes Cooling Holes that runs through wallboard, it is characterized in that: the blending angle α of film cooling holes is between 30 °～90 °, and described blending angle α reduces gradually along the fuel gas flow direction in changeover portion.
Optimal technical scheme of the present utility model is that described changeover portion body along continuous straight runs is divided into first paragraph L successively
1, second segment L
2with the 3rd section of L
3, the length of three sections not etc., all between 0～0.5L, wherein: L
1=0.4L, L
2=0.25L, L
3=0.35L, the horizontal direction total length that wherein L is described changeover portion.At described L
1in section, blending angle α is reduced to 70 ° along fuel gas flow direction from 90 ° of linearities; At described L
2in section, blending angle α is reduced to 55 ° from 70 ° of linearities; At described L
3in section, blending angle α is reduced to 30 ° from 55 ° of linearities.
Another optimal technical scheme of the present utility model is: the aperture of film cooling holes is between 0.5～1.5mm.Each exhaust membrane Cooling Holes standoff distance along changeover portion body surface in fuel gas flow direction is 5～6mm, and the circumferential spacing of described film cooling holes is 7～8mm.
Adopt scheme described in the utility model, can the working condition of changeover portion be improved in many aspects: 1., guaranteeing, under the prerequisite of changeover portion cooling effect, to have reduced cold gas consumption in changeover portion, improve overall efficiency; 2. along fuel gas flow direction, reduce gradually the turbulivity that enters the cold gas of changeover portion from film cooling holes, reduced the thickness of cooling air film, improved the capacity utilization of changeover portion, improved cooling effect; 3. reduce the quantity of Cooling Holes, avoided changeover portion barrel strength decreased too much, improved the inhomogeneous inhomogeneous problem of cooling effect that causes of air-film thickness, avoided too high thermal stress, improved service life.
Accompanying drawing explanation
Fig. 1 is conventional gas-turbine combustion chamber structural principle schematic diagram.
The stereogram of the changeover portion embodiment that Fig. 2 provides for the utility model.
Fig. 3 is the central cross-section figure of changeover portion shown in Fig. 2.
Fig. 4 is the blending angle schematic diagram of film cooling holes.
Fig. 5 is the arrangement schematic diagram of the film cooling holes on changeover portion body.
In figure, symbol description is as follows: 10-changeover portion; 11-changeover portion body entrance; The outlet of 12-changeover portion body; 13-changeover portion body; 14-changeover portion body upper casing; 15-changeover portion body lower casing; The upper lower casing connecting sewing of 16-; 17-film cooling holes; 18-entrance annulus housing; The fan-shaped housing of 19-discharge ring; 20-combustion chamber; 21-turbine one-level stator blade; 22-burner inner liner; 23-nozzle; 30-Cooling Holes axis; The projection of 31-Cooling Holes axis; 32-cooling blast; 33-high-temperature fuel gas main flow.
The specific embodiment
Below in conjunction with accompanying drawing, principle of the present utility model, structure and the specific embodiment are described further, in below describing, circumferentially refer to that changeover portion is perpendicular to the circumferencial direction of axis.
Fig. 1 is conventional gas-turbine combustion chamber structural principle schematic diagram, in Fig. 1, is the structure of typical combustion chamber 20, comprises the parts such as nozzle 23, burner inner liner 22 and changeover portion 10.Fuel or fuel and air Mixture are from nozzle 23 ejections, burning in burner inner liner 22, flame temperature is up to 1800～2400K, add in advance diluent dilution or through the cooled fuel gas temperature of burner inner liner blending hole still up to 1400～1800K, through changeover portion 10, enter turbine one-level stator blade 21, promote turbine acting.Due to changeover portion spatial extent and change in shape larger, simultaneously its circulation fuel gas temperature surpasses passage barrel material normal working temperature, therefore need to meet changeover portion aeroperformance and effective cooling design.
The stereogram of the changeover portion embodiment that Fig. 2 provides for the utility model, the central cross-section figure that Fig. 3 is this changeover portion.Shown in changeover portion 10 comprise an entrance annulus housing 18, the fan-shaped housing 19 of changeover portion body and discharge ring.Changeover portion body consists of changeover portion body upper casing 14 and changeover portion body lower casing 15, is provided with the many exhaust membranes Cooling Holes 17 that runs through wallboard on changeover portion body wallboard.
In the present embodiment, changeover portion body along continuous straight runs overall length is L, can be divided into first paragraph, second segment and the 3rd section, is respectively L
1, L
2and L
3,, three segment length not etc., wherein, L
1for the length from changeover portion body entrance to first paragraph end, L
2for the length from changeover portion body first paragraph end to second segment end, L
3for the length of second segment end to the outlet of changeover portion body.L
1, L
2, L
3each segment length all between 0～0.5L, L
1, L
2, L
3the angular dimension of the blending angle α of the film cooling holes 17 on each section is between 30～90 °; Along fuel gas flow direction, blending angle α reduces gradually along the fuel gas flow direction in changeover portion 10, and the blending angle of upstream orifice is greater than the blending angle of downstream aperture.
In the present embodiment, described each exhaust membrane Cooling Holes is preferably 5～6mm along the standoff distance of changeover portion body surface in fuel gas flow direction, and the circumferential spacing of described film cooling holes is preferably 7～8mm, L
1=0.4L, L
2=0.25L, L
3=0.35L.
Wherein, at L
1in section, blending angle α is reduced to 70 ° along fuel gas flow direction from 90 ° of linearities; At L
2in section, blending angle α is reduced to 55 ° along fuel gas flow direction from 70 ° of linearities; At L
3in section, blending angle α is reduced to 30 ° along fuel gas flow direction from 55 ° of linearities.
Fig. 4 is the blending angle schematic diagram of film cooling holes, and described blending angle α refers to the angle of Cooling Holes axis projection 31 and Cooling Holes axis 30.According to the utility model, film cooling holes can be cylindrical hole, and its aperture is between 0.5～1.5mm.
Fig. 5 is the arrangement schematic diagram of the film cooling holes on changeover portion body.The both sides of changeover portion body wooden partition are respectively high-temperature fuel gas main flow 33 and cooling blast 32, and cooling blast 32 enters high-temperature fuel gas main flow 33 by the film cooling holes 17 on wooden partition.Air-flow carries out heat convection with wall inner surface in film cooling holes 17, takes away the heat of changeover portion body wall; Flow out after wooden partition, near the hot side of changeover portion body wooden partition of pressing close to main flow region, form the air film that one deck temperature is lower, wooden partition is not directly contacted with combustion gas.In the present embodiment, the size of the blending angle α on changeover portion body reduces gradually along the direction of the inner fuel gas flow of changeover portion, i.e. blending angle α
1> blending angle α
2> blending angle α
3> blending angle α
4.Certainly, also can there is the identical situation of blending angle, subregion α, but along the blending of fuel gas flow direction, contend decrescence little in total trend.
For traditional cooling wall structure, at cooling blast, enter after the continuous stack of changeover portion, can cause the continuous thickening of air film, inhomogeneous along fuel gas flow direction cooling effect, produce larger thermal stress.And the technical solution of the utility model has been improved the inhomogeneous inhomogeneous problem of cooling effect that causes of air-film thickness, avoided too high thermal stress, avoid causing the faults such as wall warpage and crackle, the service life of having improved changeover portion.Adopt the arrangement of this film cooling holes can reduce cold gas consumption in changeover portion, improve overall efficiency; Can reduce gradually the turbulivity that enters the cold gas of changeover portion from film cooling holes along fuel gas flow direction, reduce the thickness of cooling air film, thereby reduce the thermal stress of changeover portion barrel, and improve the capacity utilization of changeover portion; Improve cooling effect, thereby reduced the quantity of Cooling Holes, reduced the cost of manufacturing.
Claims (5)
1. a gas-turbine combustion chamber changeover portion, this changeover portion (10) comprises entrance circular ring shell body (18), changeover portion body and the fan-shaped housing of discharge ring (19), described changeover portion body wallboard is provided with the many exhaust membranes Cooling Holes (17) that runs through wallboard, it is characterized in that: the blending angle α of film cooling holes (17) is between 30 °～90 °, described blending angle α reduces gradually along the fuel gas flow direction in changeover portion (10), and the blending angle of upstream orifice is greater than the blending angle of downstream aperture.
2. a kind of gas-turbine combustion chamber changeover portion according to claim 1, is characterized in that: described changeover portion body along continuous straight runs is divided into first paragraph L successively
1, second segment L
2with the 3rd section of L
3, the length of three sections not etc., all between 0～0.5L, wherein: L
1=0.4L, L
2=0.25L, L
3=0.35L, the horizontal direction total length that wherein L is described changeover portion.
3. a kind of gas-turbine combustion chamber changeover portion according to claim 2, is characterized in that: at described L
1in section, blending angle α is reduced to 70 ° along fuel gas flow direction from 90 ° of linearities; At described L
2in section, blending angle α is reduced to 55 ° from 70 ° of linearities; At described L
3in section, blending angle α is reduced to 30 ° from 55 ° of linearities.
4. according to a kind of gas-turbine combustion chamber changeover portion described in claim 1,2 or 3, it is characterized in that: the aperture of described film cooling holes (17) is between 0.5mm～1.5mm.
5. a kind of gas-turbine combustion chamber changeover portion according to claim 4, is characterized in that: described each exhaust membrane Cooling Holes (17) standoff distance along described changeover portion body surface in fuel gas flow direction is 5mm～6mm, and circumferentially spacing is 7mm～8mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320548244.4U CN203464332U (en) | 2013-09-04 | 2013-09-04 | Transition section of combustion chamber of combustion gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320548244.4U CN203464332U (en) | 2013-09-04 | 2013-09-04 | Transition section of combustion chamber of combustion gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203464332U true CN203464332U (en) | 2014-03-05 |
Family
ID=50176696
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320548244.4U Expired - Lifetime CN203464332U (en) | 2013-09-04 | 2013-09-04 | Transition section of combustion chamber of combustion gas turbine |
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| Country | Link |
|---|---|
| CN (1) | CN203464332U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105716112A (en) * | 2014-12-04 | 2016-06-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Method used for regulating temperature field of combustion chamber |
| CN106524969A (en) * | 2016-11-25 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for size detection of transition section of gas-turbine combustion chamber |
| CN107035532A (en) * | 2015-12-22 | 2017-08-11 | 通用电气公司 | Classification fuel and air injection in the combustion system of combustion gas turbine |
| CN112840160A (en) * | 2018-09-26 | 2021-05-25 | 三菱动力株式会社 | Combustor and gas turbine equipped with the same |
| CN112984560A (en) * | 2021-04-20 | 2021-06-18 | 中国联合重型燃气轮机技术有限公司 | Gas turbine, combustion chamber and transition section |
| CN115200049A (en) * | 2022-07-19 | 2022-10-18 | 中国航发沈阳发动机研究所 | Gas turbine combustion chamber transition section |
-
2013
- 2013-09-04 CN CN201320548244.4U patent/CN203464332U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105716112A (en) * | 2014-12-04 | 2016-06-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Method used for regulating temperature field of combustion chamber |
| CN107035532A (en) * | 2015-12-22 | 2017-08-11 | 通用电气公司 | Classification fuel and air injection in the combustion system of combustion gas turbine |
| CN107035532B (en) * | 2015-12-22 | 2021-04-02 | 通用电气公司 | Staged fuel and air injection in combustion systems of gas turbines |
| CN106524969A (en) * | 2016-11-25 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for size detection of transition section of gas-turbine combustion chamber |
| CN106524969B (en) * | 2016-11-25 | 2019-03-05 | 沈阳黎明航空发动机(集团)有限责任公司 | A method of for gas-turbine combustion chamber changeover portion size detection |
| CN112840160A (en) * | 2018-09-26 | 2021-05-25 | 三菱动力株式会社 | Combustor and gas turbine equipped with the same |
| CN112984560A (en) * | 2021-04-20 | 2021-06-18 | 中国联合重型燃气轮机技术有限公司 | Gas turbine, combustion chamber and transition section |
| CN115200049A (en) * | 2022-07-19 | 2022-10-18 | 中国航发沈阳发动机研究所 | Gas turbine combustion chamber transition section |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Method for detecting sectional profile of transition section of gas turbine combustion chamber Effective date of registration: 20161104 Granted publication date: 20140305 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |
|
| 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: 20140305 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191227 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: CHINA UNITED HEAVY GAS TURBINE TECHNOLOGY Co.,Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140305 |
|
| CX01 | Expiry of patent term |