CN204127994U - Gas-turbine combustion chamber transition section structure - Google Patents
Gas-turbine combustion chamber transition section structure Download PDFInfo
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- CN204127994U CN204127994U CN201420445526.6U CN201420445526U CN204127994U CN 204127994 U CN204127994 U CN 204127994U CN 201420445526 U CN201420445526 U CN 201420445526U CN 204127994 U CN204127994 U CN 204127994U
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- outlet
- changeover portion
- combustion chamber
- gas
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Abstract
The utility model relates to gas turbine technology field, discloses a kind of gas-turbine combustion chamber transition section structure, between combustion chamber flame drum and turbine, comprises changeover portion body; The import of described changeover portion body is rounded, and its outlet is in fan-shaped; The import of described changeover portion body connects a suction casing for being connected with described burner inner liner; The outlet of described changeover portion body is provided with a point fork, forms two diverging outlet; Each described diverging outlet connects an outlet housing for being connected with described turbine.The outlet of changeover portion body is provided with a point fork, forms two diverging outlet, better can bear the pressure differential of changeover portion body surfaces externally and internally, effectively reduce the creep that pressure causes.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of gas-turbine combustion chamber transition section structure.
Background technology
Typical gas turbine is made up of compressor, combustion chamber, turbine and auxiliary system, and multiple combustion chamber is 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 accepts combustion chamber flame drum and turbine, and the combustion gas passed through is temperatures as high 1400 ~ 1800K after burner inner liner blending cooling, and changeover portion has complicated unique three-D space structure.Its import cross sectional shape is consistent with burner inner liner, rounded; Outlet is connected with some combustion chambers, forms described turbine one-level stator blade annular entrance, and single changeover portion outlet is in fan-shaped.
Because changeover portion outer surface specific inner surface has higher air pressure, under the high temperature conditions, easily there is creep in fan-shaped afterframe, causes changeover portion narrow egress.This problem is particularly outstanding when burner inner liner number is less, and severe patient even can cause gas turbine normally to work.This problem limits the minimum number of combustion chamber flame drum, quantity is fewer, and the exhibition angle of changeover portion outlet is larger, more easily occurs creep problem.This problem also shortens the service life of changeover portion simultaneously, often needs to change the changeover portion of combustion chamber, and the repair cycle is long, and cost is high.
Utility model content
(1) technical problem that will solve
The purpose of this utility model is to provide a kind of combustion gas turbine combustion chamber transition section structure, the outlet of changeover portion body is provided with a point fork, form two diverging outlet, better can bear the pressure differential of changeover portion body surfaces externally and internally, effectively reduce the creep that pressure causes.
(2) technical scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of gas-turbine combustion chamber transition section structure, between combustion chamber flame drum and turbine, comprises changeover portion body; The import of described changeover portion body is rounded, and its outlet is in fan-shaped; The import of described changeover portion body connects a suction casing for being connected with described burner inner liner; The outlet of described changeover portion body is provided with a point fork, forms two diverging outlet; Each described diverging outlet connects an outlet housing for being connected with described turbine.
Wherein, described point of fork is class " V " font, and the opening direction of described point of fork is identical with the Way out of described changeover portion body.
Wherein, described outlet housing is provided with multiple outlet housing Cooling Holes.
Wherein, multiple described outlet housing Cooling Holes is arranged on the end face of described outlet housing.
Wherein, described point of fork is arranged in the middle part of the arc of described changeover portion body outlet, and the size of two described diverging outlet is identical.
Preferably, described point of fork is made up of high temperature alloy, and described point of fork is provided with multiple diffusion cooling hole.
Wherein, multiple described diffusion cooling hole is evenly arranged in described point fork.
Preferably, the medial gap of described point of fork is provided with impact lining, and described impact lining is provided with multiple impinging cooling hole.
Wherein, multiple described impinging cooling hole is evenly arranged on described impact lining.
(3) beneficial effect
The gas-turbine combustion chamber transition section structure that the utility model provides, have the following advantages: (1) is provided with a point fork due to the outlet of changeover portion body, form two diverging outlet, and be connected with turbine by two outlet housings, better can bear the pressure differential of changeover portion body surfaces externally and internally, effectively reduce the creep that pressure causes; (2) because outlet housing of the present utility model is provided with outlet housing Cooling Holes, improve cooling effect, be conducive to the thermal force reducing changeover portion, thus extend the service life of changeover portion; (3) divide fork to adopt class " V " font structure, the cooling blast of formation, is conducive to the cooling at changeover portion back, improves the condition of work of changeover portion.
Accompanying drawing explanation
Fig. 1 is the three-dimensional structure diagram of the utility model embodiment 1;
Fig. 2 is the sectional view along A-A direction in Fig. 1;
Fig. 3 is the stereogram of the part-structure of the utility model embodiment 1;
Fig. 4 is the three-dimensional structure diagram of the utility model embodiment 2;
Fig. 5 is the sectional view along B-B direction in Fig. 4;
Fig. 6 is the sectional view along C-C direction in Fig. 5.
In figure, 1: transition section structure; 2: suction casing; 3: changeover portion body; 4: outlet housing; 5: point fork; 6: outlet housing Cooling Holes; 7: diffusion cooling hole; 8: impact lining; 9: impinging cooling hole.
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 instance for illustration of the utility model, but is not used for limiting scope of the present utility model.
Embodiment 1:
As shown in Figures 1 to 3, gas-turbine combustion chamber transition section structure 1, between combustion chamber flame drum and turbine, comprises changeover portion body 3; The import of changeover portion body 3 is rounded, and its outlet is in fan-shaped; The import of changeover portion body 3 connects a suction casing 2 for being connected with burner inner liner.The outlet of changeover portion body 3 is provided with point fork 5, and the cross section of point fork 5 is class " V " font, and the opening direction of point fork 5 of V-shape is identical with the Way out of changeover portion body 3, and what make changeover portion body 3 goes out interruption-forming two diverging outlet.Preferably, point fork 5 is arranged on the arc medium position that changeover portion body 3 exports, and makes the size of two diverging outlet identical.Each diverging outlet connects an outlet housing 4 for being connected with turbine.Point fork 5 is made up of high temperature alloy, and point fork 5 is provided with multiple diffusion cooling hole 7, and multiple diffusion cooling hole 7 is evenly arranged in point fork 5.Point fork that high temperature alloy is made, improves cooling effect, is conducive to the thermal force reducing changeover portion.In the present embodiment, excise out two " V " font breach in the position that changeover portion body 3 is corresponding with point fork 5, refrigerating gas is passed in point fork preferably.
Further, export housing 4 and be provided with multiple outlet housing Cooling Holes 6.Multiple outlet housing Cooling Holes 7 is along the end face circumference evenly arrangement of outlet housing.
Embodiment 2:
As shown in Figs. 4-6, gas-turbine combustion chamber transition section structure 1, between combustion chamber flame drum and turbine, comprises changeover portion body 3; The import of changeover portion body 3 is rounded, and its outlet is in fan-shaped; The import of changeover portion body 3 connects a suction casing 2 for being connected with burner inner liner, and the entry shape of suction casing and changeover portion body 3 matches.The outlet of changeover portion body 3 is provided with point fork 5, and the cross section of point fork 5 is class " V " font, and V-shape divides the opening direction of fork 5 identical with the Way out of changeover portion body 3, and what make changeover portion body 3 goes out interruption-forming two diverging outlet.Preferably, point fork 5 is arranged on the arc medium position that changeover portion body 3 exports, and makes the size of two diverging outlet identical.Each diverging outlet connects an outlet housing 4 for being connected with turbine.Be provided with at the medial gap of point fork 5 and impact lining 8, impact lining 8 and be provided with multiple impinging cooling hole 9, multiple impinging cooling hole 9 is evenly arranged in be impacted on lining 8.As shown in Figure 6, the shape of impacting lining 8 is consistent with the interior shape of point fork 5, impact between lining 8 and point fork 5 and there is gap, refrigerating gas from impinging cooling hole 9 through impact lining 8, high speed convection gas is produced with point fork 5, produce impinging cooling, the temperature of point fork 5 can be taken away rapidly, reach good cooling effect.
Further, export housing 4 and be provided with multiple outlet housing Cooling Holes 6.Multiple outlet housing Cooling Holes 6 is along the end face circumference evenly arrangement of outlet housing 4.
The outlet of changeover portion body of the present utility model is provided with a point fork, forms two diverging outlet, and is connected with turbine by two outlet housings, better can bear the pressure differential of changeover portion body surfaces externally and internally, effectively reduce the creep that pressure causes; Outlet housing of the present utility model is provided with outlet housing Cooling Holes, improves cooling effect, is conducive to the thermal force reducing changeover portion, thus extends the service life of changeover portion; Divide fork to adopt class " V " font structure, the cooling blast of formation, is conducive to the cooling at changeover portion back, improves the condition of work of changeover portion; Point fork is arranged on the middle part of changeover portion body outlet, makes the size of diverging outlet identical, two diverging outlet uniform force, improves changeover portion stability in use, increases the service life.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (9)
1. a gas-turbine combustion chamber transition section structure, between combustion chamber flame drum and turbine, comprises changeover portion body; The import of described changeover portion body is rounded, and its outlet is in fan-shaped; The import of described changeover portion body connects a suction casing for being connected with described burner inner liner; It is characterized in that, the outlet of described changeover portion body is provided with a point fork, forms two diverging outlet; Each described diverging outlet connects an outlet housing for being connected with described turbine.
2. gas-turbine combustion chamber transition section structure as claimed in claim 1, it is characterized in that, described point of fork is class " V " font, and the opening direction of described point of fork is identical with the Way out of described changeover portion body.
3. gas-turbine combustion chamber transition section structure as claimed in claim 1, it is characterized in that, described outlet housing is provided with multiple outlet housing Cooling Holes.
4. gas-turbine combustion chamber transition section structure as claimed in claim 3, it is characterized in that, multiple described outlet housing Cooling Holes is arranged on the end face of described outlet housing.
5. gas-turbine combustion chamber transition section structure as claimed in claim 1, is characterized in that, described point of fork is arranged in the middle part of the arc of described changeover portion body outlet, and the size of two described diverging outlet is identical.
6. the gas-turbine combustion chamber transition section structure as described in any one of claim 1 to 5, is characterized in that, described point of fork is made up of high temperature alloy, and described point of fork is provided with multiple diffusion cooling hole.
7. gas-turbine combustion chamber transition section structure as claimed in claim 6, is characterized in that, multiple described diffusion cooling hole is evenly arranged in described point fork.
8. the gas-turbine combustion chamber transition section structure as described in any one of claim 1 to 5, is characterized in that, the medial gap of described point of fork is provided with impact lining, and described impact lining is provided with multiple impinging cooling hole.
9. gas-turbine combustion chamber transition section structure as claimed in claim 8, it is characterized in that, multiple described impinging cooling hole is evenly arranged on described impact lining.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420445526.6U CN204127994U (en) | 2014-08-08 | 2014-08-08 | Gas-turbine combustion chamber transition section structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420445526.6U CN204127994U (en) | 2014-08-08 | 2014-08-08 | Gas-turbine combustion chamber transition section structure |
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| Publication Number | Publication Date |
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| CN204127994U true CN204127994U (en) | 2015-01-28 |
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| CN201420445526.6U Active CN204127994U (en) | 2014-08-08 | 2014-08-08 | Gas-turbine combustion chamber transition section structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104235879A (en) * | 2014-08-08 | 2014-12-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion-chamber transition-section structure |
-
2014
- 2014-08-08 CN CN201420445526.6U patent/CN204127994U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104235879A (en) * | 2014-08-08 | 2014-12-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion-chamber transition-section structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: Gas-turbine combustion-chamber transition-section structure Effective date of registration: 20161104 Granted publication date: 20150128 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 | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150128 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191225 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-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |