CN204254678U - A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner - Google Patents
A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner Download PDFInfo
- Publication number
- CN204254678U CN204254678U CN201420643083.1U CN201420643083U CN204254678U CN 204254678 U CN204254678 U CN 204254678U CN 201420643083 U CN201420643083 U CN 201420643083U CN 204254678 U CN204254678 U CN 204254678U
- Authority
- CN
- China
- Prior art keywords
- inner liner
- burner inner
- current limiting
- cooling
- annular current
- 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.)
- Withdrawn - After Issue
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
An alternating expression cooling structure for gas-turbine combustion chamber burner inner liner, belongs to gas turbine technology field.This cooling structure comprises along the axial arranged multiple annular current limiting plate of burner inner liner, is fixed on the inwall of water conservancy diversion lining outside annular current limiting plate, is circumferentially provided with Cooling Holes inside each annular current limiting plate, and Cooling Holes is rectangle or semicircle.Cooling Holes can strengthen convection transfer rate, improves the cooling effect of burner inner liner, prevents burner inner liner temperature too high.Annular current limiting plate radial direction extends to burner inner liner, and the Cooling Holes of two adjacent annular current limiting plates is interspersed in the circumferential, can limit the flowing of air, increases the flowing time of return air, is conducive to fully cooling burner inner liner.By improving cooling, improve the reliability of burner inner liner, contributing to the service life of improving burner inner liner.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of cooling structure of gas-turbine combustion chamber burner inner liner.
Background technology
Gas turbine comprises the large parts of compressor, combustion chamber and turbine three.Wherein, the highest temperature zone of gas turbine is present in combustion chamber, and chemical energy, as the fuel gas buring parts connecting compressor and turbine, is heat energy by combustion chamber, hot-air is passed into turbine acting.At chamber front end, fuel nozzle is housed, the fuel of nozzle ejection is with the air entered in combustion chamber combustion, and ignition temperature can reach more than 2000 degrees Celsius, and pressure can reach 20 atmospheric pressure.Combustion chamber outer shell is at high temperature difficult to bear such high pressure.For reducing the temperature of combustion chamber casing wall, to ensure its intensity, usually in combustion chamber, establishing burner inner liner, reducing outer shell and being heated, outer shell is mainly played the role of pressure.
Burner inner liner generally adopts high-temperature alloy to make, and current burner inner liner metal material normal working temperature, all below 1000 degrees Celsius, therefore must cool burner inner liner, and the working life impact of the reasonability of cooling structure on burner inner liner is very large.The basic type of cooling at present for term durability gas turbine flame barrel mainly contains gaseous film control, disperses cooling, impacts and disperse combination cooling, laminate cooling etc., general principle is be introduced in burner inner liner by a part of cold air from combustion chamber return air plenums mostly, air film is formed at burner inner liner inwall, cooling flame barrel on the one hand, isolates hot combustion gas on the other hand.
And modern advanced dry low NOx discharge (DLN) combustion chamber, more air is often needed to enter combustion chamber from burner inner liner head, participate in tissue burning, while promoting combustion chamber temperature rise further, control flame temperature, thus promote gas turbine whole efficiency and reduce NOx emission.For realizing this purpose, DLN combustion chamber flame drum under high parameter is not often offered primary holes, air admission hole that blending hole equal aperture is larger, and adopt as dispersed cooling, impinging cooling or fin cooling etc. that to expend cold gas few or do not expend the cooling technology of cooling-air completely widely, thus provide more air for organizing burning.
On the one hand, burner inner liner at high temperature works for a long time, is faced with creep, problem of oxidation, and it subjects thermal mechanical fatigue in the continuous shutdown process of gas turbine; On the other hand, due to burner inner liner combustion field uncertainty, cause the inhomogeneities of thermic load and the restriction of traditional cooling structure cooling performance, cause burner inner liner wall self-temperature skewness, easily cause larger thermal stress.
Utility model content
The purpose of this utility model is to provide a kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner, makes it cool burner inner liner further, improves cooling effectiveness, avoids the high thermal stress that the too high and skewness of flame tube wall surface temperature causes.
In order to solve the problem, the technical solution of the utility model is as follows:
A kind of alternating expression flame tube cooling structure of gas-turbine combustion chamber, annular return air duct is formed between burner inner liner and water conservancy diversion lining, it is characterized in that: alternating expression flame tube cooling structure is arranged in described annular return air duct, this structure is made up of the multiple annular current limiting plate axial arranged along burner inner liner, be fixed on the inwall of water conservancy diversion lining outside annular current limiting plate, inside each annular current limiting plate, be circumferentially provided with Cooling Holes.
In technique scheme, the Cooling Holes inside described each annular current limiting plate is evenly arranged, and the Cooling Holes on adjacent two annular current limiting plates is staggered in arrangement in the circumferential.
Technical characteristic of the present utility model is also: the axial distance of two adjacent annular current limiting plates is between 90mm ~ 200mm.Cooling Holes on each annular current limiting plate is rectangle or semicircle; The center distance of adjacent two Cooling Holes is between 50mm ~ 150mm.
The structure of the staggered cellular type cooling flame cylinder that the utility model provides, have the following advantages: under the effect of the annular current limiting plate 1. in water conservancy diversion lining, return air can be forced to burner inner liner through each current limiting plate, and have certain acceleration effect, thus significantly improve the coefficient of heat transfer on burner inner liner surface, improve the cooling effect of burner inner liner; 2. because water conservancy diversion lining is provided with annular current limiting plate, can the speed of limit return flow air, the Cooling Holes be evenly arranged can improve the uniformity of the air entering burner inner liner, contributes to tissue burning.
Accompanying drawing explanation
Fig. 1 is the structural representation of the gas-turbine combustion chamber burner inner liner with cooling structure.
Fig. 2 is the A-A sectional view of Fig. 1.
Fig. 3 is the three-dimensional structure schematic diagram of the gas-turbine combustion chamber burner inner liner with cooling structure.
In figure, 1-water conservancy diversion lining; 2-burner inner liner; 3-annular current limiting plate; 4-annular return air duct; 5-Cooling Holes.
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.
Fig. 1 is the structural representation of the gas-turbine combustion chamber burner inner liner with cooling structure, and the outer setting of burner inner liner 2 has water conservancy diversion lining 1, forms annular return air duct 4 between water conservancy diversion lining and burner inner liner; This cooling structure is arranged in described annular return air duct, comprise multiple annular current limiting plate 3 axial arranged along burner inner liner, the outside of each annular current limiting plate is fixed on the inwall of water conservancy diversion lining, and the axial distance of adjacent two described annular current limiting plates 3 is between 90mm ~ 200mm.Circumferentially be provided with Cooling Holes 5 inside each annular current limiting plate, air passes annular current limiting plate in the space that Cooling Holes and burner inner liner are formed.Cooling Holes inside each annular current limiting plate is preferably evenly arranged, and the Cooling Holes on adjacent two annular current limiting plates 3 is staggered in arrangement in the circumferential, return air enters annular return air duct 4 from water conservancy diversion Bushing outlet, arrive annular current limiting plate 3 place, pass from Cooling Holes 5, the flowing of air can be limited like this, increase the flowing time of return air, be conducive to fully cooling burner inner liner.
Fig. 2 is the A-A sectional view of Fig. 1, described annular current limiting plate 3 extends to burner inner liner 2 outside wall surface from water conservancy diversion lining 1 internal face radial direction, reasonable barrier effect can be played to return air, multiple semicircular Cooling Holes 5 is being offered near burner inner liner 2 place, return air accelerates through from described cooling 5 hole, effectively strengthens the coefficient of heat transfer on burner inner liner surface.On each annular current limiting plate, the center distance of adjacent two Cooling Holes 5 is between 50mm ~ 150mm.The Cooling Holes 5 of adjacent two described annular current limiting plates is interspersed in the circumferential, can increase the flowing time of return air like this, improve cooling effect.
Claims (4)
1. the alternating expression cooling structure of a gas-turbine combustion chamber burner inner liner, the outer setting of described burner inner liner (2) has water conservancy diversion lining (1), annular return air duct (4) is formed between water conservancy diversion lining and burner inner liner, it is characterized in that: this cooling structure is arranged in described annular return air duct (4), comprise multiple annular current limiting plate (3) axial arranged along burner inner liner (2); The outside of each annular current limiting plate (3) is fixed on the inwall of water conservancy diversion lining (1), and each annular current limiting plate (3) inner side is circumferentially provided with Cooling Holes (5); The Cooling Holes (5) of each annular current limiting plate (3) inner side is evenly arranged, and the Cooling Holes on adjacent two annular current limiting plates (3) is staggered in arrangement in the circumferential.
2. the alternating expression cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1, is characterized in that, the axial distance between two adjacent annular current limiting plates (3) is between 90mm ~ 200mm.
3. the alternating expression cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1 or 2, is characterized in that, on each annular current limiting plate, the center distance of adjacent two Cooling Holes (5) is between 50mm ~ 150mm.
4. the alternating expression cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 3, is characterized in that, described Cooling Holes (5) is rectangular opening or semi-circular hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420643083.1U CN204254678U (en) | 2014-10-31 | 2014-10-31 | A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420643083.1U CN204254678U (en) | 2014-10-31 | 2014-10-31 | A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204254678U true CN204254678U (en) | 2015-04-08 |
Family
ID=52958979
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420643083.1U Withdrawn - After Issue CN204254678U (en) | 2014-10-31 | 2014-10-31 | A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204254678U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104359126A (en) * | 2014-10-31 | 2015-02-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Staggered cooling structure of flame tube in combustion chamber of gas turbine |
| CN111086185A (en) * | 2019-12-25 | 2020-05-01 | 安徽环瑞电热器材有限公司 | Cable extrusion device |
| CN113567143A (en) * | 2021-08-27 | 2021-10-29 | 华能国际电力股份有限公司 | Visual gas turbine combustion chamber experimental system |
-
2014
- 2014-10-31 CN CN201420643083.1U patent/CN204254678U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104359126A (en) * | 2014-10-31 | 2015-02-18 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Staggered cooling structure of flame tube in combustion chamber of gas turbine |
| CN104359126B (en) * | 2014-10-31 | 2017-09-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner |
| CN111086185A (en) * | 2019-12-25 | 2020-05-01 | 安徽环瑞电热器材有限公司 | Cable extrusion device |
| CN111086185B (en) * | 2019-12-25 | 2021-12-10 | 安徽环瑞电热器材有限公司 | Cable extrusion device |
| CN113567143A (en) * | 2021-08-27 | 2021-10-29 | 华能国际电力股份有限公司 | Visual gas turbine combustion chamber experimental system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201488267U (en) | Hot blast stove | |
| CN203671657U (en) | Flame tube and gas turbine combustion chamber comprising same | |
| CN104359126A (en) | Staggered cooling structure of flame tube in combustion chamber of gas turbine | |
| CN204176685U (en) | The double-deck gaseous film control structure of gas-turbine combustion chamber burner inner liner | |
| CN104359127A (en) | Channel type cooling structure of flame tube in combustion chamber of gas turbine | |
| CN208620599U (en) | A kind of novel gas fuel oil mixing type air hot-blast stove | |
| CN204227466U (en) | Gas-turbine combustion chamber burner inner liner wall cooling structure | |
| CN204254677U (en) | A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner | |
| CN113188154B (en) | Flame tube with cooling structure | |
| CN104296160A (en) | Flow guide bush of combustion chamber of combustion gas turbine and with cooling function | |
| CN204254678U (en) | A kind of alternating expression cooling structure of gas-turbine combustion chamber burner inner liner | |
| CN206600840U (en) | A kind of burner inner liner of combustion chamber | |
| WO2022012398A1 (en) | Single-boiler-sheet series cast aluminum-silicon water heater coupled to pre-mixing water-cooling combustor | |
| CN203464332U (en) | Transition section of combustion chamber of combustion gas turbine | |
| CN106556030A (en) | Combustor fuel nozzle and its thermal protection structure | |
| CN204254676U (en) | A kind of cooling structure of gas-turbine combustion chamber burner inner liner | |
| CN204227467U (en) | A kind of flame combustion chamber barrel structure | |
| CN204830036U (en) | Combustion heater's gas room structure | |
| CN204254675U (en) | A kind of distribute type cooling structure of gas-turbine combustion chamber burner inner liner | |
| CN204084461U (en) | A kind of water conservancy diversion lining with the gas-turbine combustion chamber of refrigerating function | |
| CN204648314U (en) | A kind of water conservancy diversion lining of gas-turbine combustion chamber | |
| CN204388127U (en) | Natural gas fuel gas turbine toroidal combustion chamber | |
| CN104141540A (en) | Cooling mechanism for transition section of combustion chamber in gas turbine and combustion chamber in gas turbine | |
| CN204648317U (en) | A kind of gas-turbine combustion chamber burner inner liner with cooling structure | |
| WO2022227582A1 (en) | Combustion chamber structure having heat exchanger |
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: Staggered cooling structure of flame tube in combustion chamber of gas turbine Effective date of registration: 20161104 Granted publication date: 20150408 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 | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150408 Effective date of abandoning: 20170915 |