CN202613499U - Gas turbine backflow combustion chamber - Google Patents
Gas turbine backflow combustion chamber Download PDFInfo
- Publication number
- CN202613499U CN202613499U CN 201220217580 CN201220217580U CN202613499U CN 202613499 U CN202613499 U CN 202613499U CN 201220217580 CN201220217580 CN 201220217580 CN 201220217580 U CN201220217580 U CN 201220217580U CN 202613499 U CN202613499 U CN 202613499U
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- shell body
- gas turbine
- inner liner
- burner inner
- outer shell
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Abstract
The utility model provides a gas turbine backflow combustion chamber which comprises an exhaust bending pipe outer shell body and a flame tube, wherein the exhaust bending pipe outer shell body and the flame tube are connected in a separated mode and matched with each other through unilateral check buttons formed by inner steps arranged on the exhaust bending pipe outer shell body and outer steps arranged on the flame tube. The exhaust bending pipe outer shell body is a disc piece, and the flame tube is a cylinder piece. At the same time, a plurality of supporting check blocks further enable the exhaust bending pipe outer shell body to axially abut against a matched position of the outer periphery of the flame tube and enable the matched exhaust bending pipe outer shell body and the outer periphery of the flame tube not to move axially. A gap exists between the exhaust bending pipe outer shell body and the flame tube, the gap enables the thermal stress and thermal deformation on the exhaust bending pipe outer shell body and the flame tube to be released, and the reliability of the combustion chamber is improved. At the same time, the supporting structure is simple, the exhaust bending pipe outer shell body and the flame tube are respectively and independently machined and installed, the machining technology of parts is greatly improved, and machining and assembling difficulties are reduced.
Description
Technical field
The utility model relates to the gas turbine field, especially, relates to a kind of gas turbine reverse flow type combustor.
Background technology
At present, the domestic middle-size and small-size gas-turbine unit structures that adopt annular reverse flow type combustor more, referring to Fig. 1, this annular reverse flow type combustor comprises exhaust elbow shell body 10, burner inner liner 20, diffusion casing 30 and outer casing 40.Wherein, Exhaust elbow shell body 10 is that disc, burner inner liner 20 are cylindrical shape; During installation; The annular backflow burner inner liner assembly of exhaust elbow shell body 10 and burner inner liner 20 integrally welded shapings, and exhaust elbow shell body 10 is installed on the diffusion casing 30 through securing member 50, and burner inner liner 20 is connected with outer casing 40 through some bearing assemblies 60 to be fixed.
In the course of work of combustion chamber, because the Temperature Distribution of combustion chamber each several part and thermal expansion are different, cause exhaust elbow shell body 10 and burner inner liner 20 can have bigger thermal stress and thermal stress deformation, influence the life-span of gas-turbine unit; Simultaneously, also there is processing difficulties in integral annular backflow burner inner liner assembly, and welding procedure property is poor, problems such as assembling and maintainable difference.
The utility model content
The utility model purpose is to provide a kind of novel gas turbine reverse flow type combustor, to solve the technical problem of the integrally formed annular backflow burner inner liner assembly mounting, commissioning and maintenance poor performance of existing welded type.
For realizing above-mentioned purpose, according to the utility model a kind of gas turbine reverse flow type combustor is provided, comprise exhaust elbow shell body and burner inner liner, split is connected the exhaust elbow shell body with burner inner liner.
Further, the exhaust elbow shell body is a disc, and burner inner liner is a cylindrical element.
Further, the end of exhaust elbow shell body is provided with interior step, and the outer peripheral edges of burner inner liner are provided with outer step, and interior step forms the monolateral button that ends with outer step and is connected.
Further, interior step and exhaust elbow shell body are one-body molded, and outer step and burner inner liner are one-body molded.
Further, interior step is loop configuration with outer step.
Further, interior step and outer step matched in clearance.
Further, also comprise diffusion casing, outer casing, securing member and some bearing assemblies, the exhaust elbow shell body is fixedly mounted on the diffusion casing through securing member, and burner inner liner is fixed in outer casing through some bearing assemblies.
Further, each bearing assembly comprises supporting base that is arranged on the burner inner liner outer surface and the cramp bar that passes through outer casing wall, and cramp bar cooperates with supporting base.
Further, be axially arranged with some support stops in diffusion casing upper edge, support stop is arranged at outer peripheral edges and the backstop of diffusion casing in the end wall of exhaust elbow shell body.
The utlity model has following beneficial effect: the gas turbine reverse flow type combustor of the utility model preferred embodiment; Split is connected the exhaust elbow shell body with burner inner liner; And pass through interior step and detain cooperation with monolateral the ending that outer step forms; Simultaneously, some support stops further push against the exhaust elbow shell body in the cooperation place of burner inner liner flange vertically, make the monolateral button that ends cooperate more reliable.Have the gap between exhaust elbow shell body, the burner inner liner, this gap makes thermal stress, the thermal deformation on exhaust elbow shell body, the burner inner liner be released, and has improved the reliability of combustion chamber.Simultaneously, this supporting structure is simple, and exhaust elbow shell body and burner inner liner be processing and installation separately respectively, has improved the processing technology of part greatly, has reduced processing and assembly difficulty.
Except top described purpose, feature and advantage, the utility model also has other purpose, feature and advantage.To do further detailed explanation to the utility model with reference to figure below.
Description of drawings
The accompanying drawing that constitutes the application's a part is used to provide the further understanding to the utility model, and illustrative examples of the utility model and explanation thereof are used to explain the utility model, do not constitute the improper qualification to the utility model.In the accompanying drawings:
Fig. 1 is the prior art contrast scheme sketch map of the utility model preferred embodiment;
Fig. 2 is that the master of the utility model preferred embodiment looks sketch map.
The specific embodiment
Embodiment to the utility model is elaborated below in conjunction with accompanying drawing, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
Referring to Fig. 2, the gas turbine reverse flow type combustor of the utility model comprises exhaust elbow shell body 1, the burner inner liner 2 that is connected with 1 split of exhaust elbow shell body.
Exhaust elbow shell body 1 is that disc and burner inner liner 2 are cylindrical element.The end of exhaust elbow shell body 1 is provided with interior step 11, and burner inner liner 2 outer end peripheries are provided with outer step 21, and interior step 11 forms the monolateral buckle of ending with outer step 21, makes exhaust elbow shell body 1 axially only buckle with burner inner liner 2 and fits in one.
For the ease of producing and processing, preferably, interior step 11 is one-body molded with exhaust elbow shell body 1, and outer step 21 is one-body molded with burner inner liner 2.Interior step 11 is loop configuration with outer step 21.In use move after can be suitably for satisfying burner inner liner 2 because of thermal expansion; Can not make simultaneously exhaust elbow housing 1 produce distortion; More preferably; The interior step 11 of exhaust elbow shell body 1 and the outer step of burner inner liner 2 21 cooperate part to leave less clearance, step 11 and outer step 21 matched in clearance in promptly guaranteeing.
In the preferred embodiment of the utility model, the gas turbine reverse flow type combustor also comprises diffusion casing 3, outer casing 4, securing member 5 and the some bearing assemblies 6 that radially are provided with.Exhaust elbow shell body 1 is through securing member 5 dismountable being fixedly mounted on the diffusion casing 3; Burner inner liner 2 is connected and fixed on outer casing 4 through some bearing assemblies 6; Wherein each bearing assembly 6 comprises supporting base 61 that radially is arranged on burner inner liner 2 outer surfaces and the cramp bar 62 that passes through outer casing 4 walls, and cramp bar 62 cooperates with supporting base 61.
When install the gas turbine reverse flow type combustor of the utility model; At first exhaust elbow shell body 1 is installed on the diffusion casing 3 through securing member 5; The outer step 21 of burner inner liner 2 external end heads is axially inserted the inner surface place applying of the interior step 11 of exhaust elbow shell body 1, at this moment, the end face of interior step 11 radially forms matched in clearance with the end face of outer step 21 again; Simultaneously, interior step 11 forms dismountable monolateral button cooperation that ends with outer step 21.This syndeton makes and leaves less clearance between exhaust elbow shell body 1, the burner inner liner 2.At last, cramp bar 62 is sleeved in the supporting base 61, burner inner liner 2 is fixedly connected on the outer casing 4.
For avoiding in exhaust elbow shell body 1 and burner inner liner 2 uses owing to move after the thermal expansion generation axially; Preferably; Be axially arranged with some support stops 31 in diffusion casing 3 upper edges, support stop 31 is arranged at outer peripheral edges and the backstop of diffusion casing 3 in the end wall of exhaust elbow shell body 1.Thereby, exhaust elbow shell body 1 be supported vertically block 31 against, prevent exhaust elbow shell body 1 distortion.
The gas turbine reverse flow type combustor of the utility model preferred embodiment, 2 splits are connected exhaust elbow shell body 1 with burner inner liner, and the outer step 21 of interior step through exhaust elbow shell body 1 11 and burner inner liner 2 form monolaterally only buckle cooperation.Have the gap between exhaust elbow shell body 1, the burner inner liner 2, this gap makes thermal stress, the thermal deformation on exhaust elbow shell body 1, the burner inner liner 2 be released, and has improved the reliability of combustion chamber.Simultaneously, this supporting structure is simple, and exhaust elbow shell body 1 is processed separately respectively and installed with burner inner liner 2, has improved the processing technology of part greatly, has reduced processing and assembly difficulty.
The preferred embodiment that the above is merely the utility model is not limited to the utility model, and for a person skilled in the art, the utility model can have various changes and variation.All within the spirit and principle of the utility model, any modification of being done, be equal to replacement, improvement etc., all should be included within the protection domain of the utility model.
Claims (9)
1. a gas turbine reverse flow type combustor comprises exhaust elbow shell body (1) and burner inner liner (2), it is characterized in that, split is connected said exhaust elbow shell body (1) with said burner inner liner (2).
2. gas turbine according to claim 1 reverse flow type combustor is characterized in that, said exhaust elbow shell body (1) is a disc, and said burner inner liner (2) is a cylindrical element.
3. gas turbine according to claim 1 reverse flow type combustor; It is characterized in that; The end of exhaust elbow shell body (1) is provided with interior step (11); The outer peripheral edges of said burner inner liner (2) are provided with outer step (21), and said interior step (11) forms the monolateral button that ends with said outer step (21) and is connected.
4. gas turbine according to claim 3 reverse flow type combustor is characterized in that, said interior step (11) is one-body molded with said exhaust elbow shell body (1), and said outer step (21) is one-body molded with said burner inner liner (2).
5. gas turbine according to claim 3 reverse flow type combustor is characterized in that, said interior step (11) is loop configuration with said outer step (21).
6. gas turbine according to claim 3 reverse flow type combustor is characterized in that, said interior step (11) and said outer step (21) matched in clearance.
7. gas turbine according to claim 1 reverse flow type combustor; It is characterized in that; Also comprise diffusion casing (3), outer casing (4), securing member (5) and some bearing assemblies (6); Said exhaust elbow shell body (1) is fixedly mounted on the said diffusion casing (3) through said securing member (5), and said burner inner liner (2) is fixed in said outer casing (4) through said some bearing assemblies (6).
8. gas turbine according to claim 7 reverse flow type combustor; It is characterized in that; Each said bearing assembly (6) comprises supporting base (61) that is arranged on said burner inner liner (2) outer surface and the cramp bar (62) that passes through said outer casing (4) wall, and said cramp bar (62) cooperates with said supporting base (61).
9. gas turbine according to claim 7 reverse flow type combustor; It is characterized in that; Be axially arranged with some support stops (31) in said diffusion casing (3) upper edge, said support stop (31) is arranged at outer peripheral edges and the backstop of said diffusion casing (3) in the end wall of said exhaust elbow shell body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220217580 CN202613499U (en) | 2012-05-15 | 2012-05-15 | Gas turbine backflow combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220217580 CN202613499U (en) | 2012-05-15 | 2012-05-15 | Gas turbine backflow combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202613499U true CN202613499U (en) | 2012-12-19 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220217580 Expired - Lifetime CN202613499U (en) | 2012-05-15 | 2012-05-15 | Gas turbine backflow combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202613499U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
| CN105299692A (en) * | 2014-06-03 | 2016-02-03 | 贵州黎阳天翔科技有限公司 | Combustion chamber device of large-area smoke disinfection and epidemic prevention equipment |
| CN107120689A (en) * | 2017-04-28 | 2017-09-01 | 中国航发湖南动力机械研究所 | Bend pipe structure and reverse flow type combustor, gas-turbine unit in reflowed combustion room |
| CN109974033A (en) * | 2019-03-21 | 2019-07-05 | 中国航发湖南动力机械研究所 | Reverse flow type combustor and its double wall bend pipe structure |
| CN110081462A (en) * | 2019-04-29 | 2019-08-02 | 天津天成智造科技有限公司 | A kind of low pollution combustor |
| CN111023151A (en) * | 2019-12-30 | 2020-04-17 | 重庆天骄航空动力有限公司 | Connecting structure of backflow combustion chamber and turbine guider and gas turbine engine |
| CN113188154A (en) * | 2021-05-10 | 2021-07-30 | 中国航发湖南动力机械研究所 | Novel flame tube with cooling structure |
| CN113685844A (en) * | 2021-08-24 | 2021-11-23 | 中国航发湖南动力机械研究所 | Little return bend assembly fixture of combustion chamber full ring test spare |
| CN115183277A (en) * | 2022-06-02 | 2022-10-14 | 中国航发四川燃气涡轮研究院 | Flame tube |
| CN116293823A (en) * | 2023-03-15 | 2023-06-23 | 中国航发湖南动力机械研究所 | Large bent pipe and backflow combustion chamber |
-
2012
- 2012-05-15 CN CN 201220217580 patent/CN202613499U/en not_active Expired - Lifetime
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105299692A (en) * | 2014-06-03 | 2016-02-03 | 贵州黎阳天翔科技有限公司 | Combustion chamber device of large-area smoke disinfection and epidemic prevention equipment |
| CN104406197A (en) * | 2014-11-24 | 2015-03-11 | 中国科学院工程热物理研究所 | Low-emission reverse flow combustor adopting radial swirl injection and fuel oil grading schemes |
| CN107120689A (en) * | 2017-04-28 | 2017-09-01 | 中国航发湖南动力机械研究所 | Bend pipe structure and reverse flow type combustor, gas-turbine unit in reflowed combustion room |
| CN109974033B (en) * | 2019-03-21 | 2020-11-13 | 中国航发湖南动力机械研究所 | Backflow combustion chamber and double-wall bent pipe structure thereof |
| CN109974033A (en) * | 2019-03-21 | 2019-07-05 | 中国航发湖南动力机械研究所 | Reverse flow type combustor and its double wall bend pipe structure |
| CN110081462A (en) * | 2019-04-29 | 2019-08-02 | 天津天成智造科技有限公司 | A kind of low pollution combustor |
| CN111023151A (en) * | 2019-12-30 | 2020-04-17 | 重庆天骄航空动力有限公司 | Connecting structure of backflow combustion chamber and turbine guider and gas turbine engine |
| CN111023151B (en) * | 2019-12-30 | 2021-04-30 | 重庆天骄航空动力有限公司 | Connecting structure of backflow combustion chamber and turbine guider and gas turbine engine |
| CN113188154A (en) * | 2021-05-10 | 2021-07-30 | 中国航发湖南动力机械研究所 | Novel flame tube with cooling structure |
| CN113685844A (en) * | 2021-08-24 | 2021-11-23 | 中国航发湖南动力机械研究所 | Little return bend assembly fixture of combustion chamber full ring test spare |
| CN113685844B (en) * | 2021-08-24 | 2022-11-25 | 中国航发湖南动力机械研究所 | Little return bend assembly fixture of combustion chamber full ring test spare |
| CN115183277A (en) * | 2022-06-02 | 2022-10-14 | 中国航发四川燃气涡轮研究院 | Flame tube |
| CN115183277B (en) * | 2022-06-02 | 2024-05-17 | 中国航发四川燃气涡轮研究院 | Flame tube |
| CN116293823A (en) * | 2023-03-15 | 2023-06-23 | 中国航发湖南动力机械研究所 | Large bent pipe and backflow combustion chamber |
| CN116293823B (en) * | 2023-03-15 | 2024-06-25 | 中国航发湖南动力机械研究所 | Large bent pipe and backflow combustion chamber |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121219 |
|
| CX01 | Expiry of patent term |