CA2499908A1 - Gas turbine combustor cooling stucture - Google Patents
Gas turbine combustor cooling stuctureInfo
- Publication number
- CA2499908A1 CA2499908A1 CA002499908A CA2499908A CA2499908A1 CA 2499908 A1 CA2499908 A1 CA 2499908A1 CA 002499908 A CA002499908 A CA 002499908A CA 2499908 A CA2499908 A CA 2499908A CA 2499908 A1 CA2499908 A1 CA 2499908A1
- Authority
- CA
- Canada
- Prior art keywords
- groove
- hole
- cooling
- wall
- air
- Prior art date
- 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.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title abstract 5
- 239000002826 coolant Substances 0.000 abstract 2
- 230000000694 effects Effects 0.000 abstract 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Cooling structure of gas turbine combustor in which cooling medium flows through grooves in wall is improved so that adjustment of flow velocity, pressure loss and heat transfer rate of cooling medium flow in the wall becomes possible and cooling effect thereof is enhanced. Wall of combustor tail tube is made in double structure in which outer plate (1) and inner plate (4) are jointed together being lapped one on another . The outer plate (1) has air inlet hole (3) and groove (2) formed therein . The groove (2) is closed by jointing of the inner plate (4) to the outer plate (1).
The inner plate (4) has air outlet hole (5) formed therein.
The groove (2) communicates with the air inlet hole (3) and the air outlet hole (5). Cross sectional shape of the groove (2) is changed two-dimensionally or three-dimensionally such that width enlarges toward the hole (5) from the hole (3) or depth is constant or changed in tapered form. Cooling air flows into the groove (2) from the air inlet hole (3) of tail tube surface to flow toward both sides along the groove (2) for cooling of the wall. The air is thereby heated to expand to increase flow velocity and pressure loss, but flow passage enlarges toward the hole (5) and flow velocity is suppressed and pressure loss is reduced.
The inner plate (4) has air outlet hole (5) formed therein.
The groove (2) communicates with the air inlet hole (3) and the air outlet hole (5). Cross sectional shape of the groove (2) is changed two-dimensionally or three-dimensionally such that width enlarges toward the hole (5) from the hole (3) or depth is constant or changed in tapered form. Cooling air flows into the groove (2) from the air inlet hole (3) of tail tube surface to flow toward both sides along the groove (2) for cooling of the wall. The air is thereby heated to expand to increase flow velocity and pressure loss, but flow passage enlarges toward the hole (5) and flow velocity is suppressed and pressure loss is reduced.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32237898A JP3626861B2 (en) | 1998-11-12 | 1998-11-12 | Gas turbine combustor cooling structure |
| JP10-322378 | 1998-11-12 | ||
| JP32370498A JP3626862B2 (en) | 1998-11-13 | 1998-11-13 | Gas turbine combustor pilot cone cooling structure |
| JP10-323704 | 1998-11-13 | ||
| CA002288557A CA2288557C (en) | 1998-11-12 | 1999-11-04 | Gas turbine combustor cooling structure |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002288557A Division CA2288557C (en) | 1998-11-12 | 1999-11-04 | Gas turbine combustor cooling structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2499908A1 true CA2499908A1 (en) | 2000-05-12 |
| CA2499908C CA2499908C (en) | 2007-06-26 |
Family
ID=34527231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002499908A Expired - Fee Related CA2499908C (en) | 1998-11-12 | 1999-11-04 | Gas turbine combustor cooling stucture |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2499908C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217948A (en) * | 2021-05-13 | 2021-08-06 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber laminate and combustion chamber |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112880296B (en) * | 2020-12-31 | 2022-11-29 | 山东微波电真空技术有限公司 | Assembly machine capable of achieving rapid cooling |
-
1999
- 1999-11-04 CA CA002499908A patent/CA2499908C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113217948A (en) * | 2021-05-13 | 2021-08-06 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber laminate and combustion chamber |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2499908C (en) | 2007-06-26 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |