CN204254677U - A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner - Google Patents
A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner Download PDFInfo
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- CN204254677U CN204254677U CN201420643073.8U CN201420643073U CN204254677U CN 204254677 U CN204254677 U CN 204254677U CN 201420643073 U CN201420643073 U CN 201420643073U CN 204254677 U CN204254677 U CN 204254677U
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- inner liner
- burner inner
- return air
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- conservancy diversion
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Abstract
A channel-type cooling structure for gas-turbine combustion chamber burner inner liner, belongs to gas turbine technology field.This cooling structure comprises along many axial arranged dividing plates of burner inner liner and cover board of front end and rear-end plate; Dividing plate is fixed on the inwall of water conservancy diversion lining, and cover board of front end is fixed on the water conservancy diversion lining inwall at annular return air channel inlet place, and rear-end plate is fixed on the water conservancy diversion lining inwall at annular return air channel outlet place; Cover board of front end and rear-end plate are provided with multiple metering hole.Owing to being provided with multiple dividing plate in annular return air duct, annular return air duct can be separated into multiple axial cooling duct, return air can be flowed in multiple axial cooling duct, reduce the tangential velocity of air, improve flow condition, contribute to strengthening convection transfer rate, improve cooling effectiveness; The uniformity that air enters burner inner liner can be improved simultaneously, improve the flow condition in burner inner liner, contribute to tissue burning.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of gas-turbine combustion chamber flame tube cooling structure.
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, making its main pressure-bearing.
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 gas-turbine combustion chamber burner inner liner 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, often need more air 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 combustion engine 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 and 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 channel-type 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 channel-type cooling structure of gas-turbine combustion chamber burner inner liner, the outer setting of described burner inner liner has water conservancy diversion lining, annular return air duct is formed between water conservancy diversion lining and burner inner liner, it is characterized in that, channel-type cooling structure is arranged on this structure in described annular return air duct and comprises along many axial arranged dividing plates of burner inner liner and cover board of front end and rear-end plate; Many dividing plate is circumferentially fixed on the inwall of water conservancy diversion lining, and annular return air duct is separated into multiple axial cooling duct; Cover board of front end is fixed on the water conservancy diversion lining inwall at annular return air channel inlet place, and rear-end plate is fixed on the water conservancy diversion lining inwall at annular return air channel outlet place, and cover board of front end and rear-end plate are respectively arranged with multiple metering hole.
Wherein, described dividing plate circumference on water conservancy diversion lining is evenly arranged, and the vertical interval between two adjacent described dividing plates is at least between 25mm ~ 100mm.
Wherein, described metering hole is radially arranged in array, and each row are circumferentially evenly arranged.
Wherein, the columns of described metering hole is identical with dividing plate quantity.
Wherein, the diameter of the described multiple metering hole of each row diminishes to water conservancy diversion lining from burner inner liner successively by radial direction.
The utility model has the following advantages and the technique effect of high-lighting: 1. owing to being provided with multiple dividing plate in annular return air duct, annular return air duct can be separated into multiple axial cooling duct, return air can be flowed in multiple axial cooling duct, reduce the tangential velocity of air, improve flow condition, contribute to strengthening convection transfer rate, improve cooling effectiveness; 2. improve the uniformity that air enters burner inner liner, improve the flow condition in burner inner liner, contribute 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; 3a-cover board of front end; 3b-rear-end plate; 4-dividing plate; 5-annular return air duct; 6-metering hole.
Detailed description of the invention
Below in conjunction with drawings and Examples, principle of the present utility model, structure and detailed description of the invention are described in further detail.
Fig. 1 is the sectional view of the gas-turbine combustion chamber burner inner liner gas-turbine combustion chamber burner inner liner with channel-type cooling structure, and as shown in the figure, the outer setting of burner inner liner 2 has water conservancy diversion lining 1, forms annular return air duct 5 between water conservancy diversion lining 1 and burner inner liner 2.Cooling structure is arranged in described annular return air duct 5, and this structure comprises along the axial arranged many dividing plates 4 of burner inner liner 2 and cover board of front end 3a and rear-end plate 3b; Dividing plate 4 is fixed on the inwall of water conservancy diversion lining 1, cover board of front end 3a is fixed on the inwall of the water conservancy diversion lining 1 of annular return air duct 5 porch, rear-end plate 3b is fixed on the inwall of the water conservancy diversion lining 1 in annular return air duct 5 exit, cover board of front end 3a and rear-end plate 3b is provided with multiple metering hole 6, and return air can enter axial cooling duct by metering hole.
In the utility model, described dividing plate 4 is evenly arranged at the circumferencial direction of water conservancy diversion lining 1; Vertical interval between two adjacent dividing plates 4 at least between 25mm ~ 100mm (see Fig. 2, Fig. 3).Owing to being provided with multiple dividing plate in annular return air duct, annular return air duct can be separated into multiple axial cooling duct, return air can be flowed in multiple axial cooling duct, reduce the tangential velocity of air, improve flow condition, contribute to strengthening convection transfer rate, improve cooling effectiveness; Can further improve the uniformity that air enters burner inner liner simultaneously, improve the flow condition in burner inner liner, contribute to tissue burning.
Fig. 2 is the A-A sectional view of Fig. 1, and described metering hole 6 is radially arranged in array, and each row are circumferentially evenly arranged, and the columns of metering hole 6 should be identical with dividing plate quantity.Described return air plenums 5 is divided into multiple uniform axial cooling duct by dividing plate.The diameter of the multiple metering holes 6 described in each row diminishes to water conservancy diversion lining 1 from burner inner liner 2 successively by radial direction, adjustable air velocity radial distributes, the flow of the return air near burner inner liner place is increased, be conducive to the air velocity improving burner inner liner 2 near wall, strengthen the coefficient of heat transfer, improve the cooling effectiveness of burner inner liner 2.
Claims (5)
1. the channel-type 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 (5) is formed between water conservancy diversion lining and burner inner liner, it is characterized in that, channel-type cooling structure is arranged in described annular return air duct (5), and this structure comprises along the axial arranged many dividing plates (4) of burner inner liner (2) and cover board of front end (3a) and rear-end plate (3b); Many dividing plate (4) is circumferentially fixed on the inwall of water conservancy diversion lining (1), and annular return air duct is separated into multiple axial cooling duct; Described cover board of front end (3a) is fixed on water conservancy diversion lining (1) inwall of annular return air duct (5) porch, rear-end plate (3b) is fixed on water conservancy diversion lining (1) inwall in annular return air duct (5) exit, and cover board of front end (3a) and rear-end plate (3b) are respectively arranged with multiple metering hole (6).
2. the channel-type cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1, it is characterized in that, described dividing plate is circumferentially evenly arranged on water conservancy diversion lining (1), and the vertical interval between two adjacent dividing plates (4) is at least between 25mm ~ 100mm.
3. the channel-type cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1, is characterized in that, described metering hole (6) is radially arranged in array, and each row are circumferentially evenly arranged.
4. the channel-type cooling structure of a kind of gas-turbine combustion chamber burner inner liner as described in claim 1,2 or 3, is characterized in that, the columns of described metering hole (6) is identical with dividing plate quantity.
5. the channel-type cooling structure of a kind of gas-turbine combustion chamber burner inner liner as described in claim 1,2 or 3, is characterized in that, the diameter of each row metering hole (6) radially diminishes from burner inner liner successively to water conservancy diversion lining.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420643073.8U CN204254677U (en) | 2014-10-31 | 2014-10-31 | A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420643073.8U CN204254677U (en) | 2014-10-31 | 2014-10-31 | A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner |
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| CN204254677U true CN204254677U (en) | 2015-04-08 |
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| CN201420643073.8U Active CN204254677U (en) | 2014-10-31 | 2014-10-31 | A kind of channel-type cooling structure of gas-turbine combustion chamber burner inner liner |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104359127A (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 | Channel type cooling structure of flame tube in combustion chamber of gas turbine |
| CN104832948A (en) * | 2015-04-23 | 2015-08-12 | 中国人民解放军空军工程大学 | Fingerprint mesh cooling device for concave cavity combustion chamber |
| CN105276620A (en) * | 2015-06-26 | 2016-01-27 | 中航空天发动机研究院有限公司 | Composite cooling structure for wall of combustion chamber flame tube of aero-engine |
| CN106482133A (en) * | 2016-12-12 | 2017-03-08 | 深圳智慧能源技术有限公司 | Source of the gas energy is relied on to provide the torch of cooling air |
-
2014
- 2014-10-31 CN CN201420643073.8U patent/CN204254677U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104359127A (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 | Channel type cooling structure of flame tube in combustion chamber of gas turbine |
| CN104832948A (en) * | 2015-04-23 | 2015-08-12 | 中国人民解放军空军工程大学 | Fingerprint mesh cooling device for concave cavity combustion chamber |
| CN105276620A (en) * | 2015-06-26 | 2016-01-27 | 中航空天发动机研究院有限公司 | Composite cooling structure for wall of combustion chamber flame tube of aero-engine |
| CN105276620B (en) * | 2015-06-26 | 2018-02-13 | 中航空天发动机研究院有限公司 | A kind of aeroengine combustor buring room burner inner liner wall compound cooling structure |
| CN106482133A (en) * | 2016-12-12 | 2017-03-08 | 深圳智慧能源技术有限公司 | Source of the gas energy is relied on to provide the torch of cooling air |
| CN106482133B (en) * | 2016-12-12 | 2019-03-05 | 深圳智慧能源技术有限公司 | The torch of cooling air is provided by gas source energy |
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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: Channel type 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 | ||
| 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: 20150408 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |