CN204254675U - A kind of distribute type cooling structure of gas-turbine combustion chamber burner inner liner - Google Patents
A kind of distribute type cooling structure of gas-turbine combustion chamber burner inner liner Download PDFInfo
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- CN204254675U CN204254675U CN201420642719.0U CN201420642719U CN204254675U CN 204254675 U CN204254675 U CN 204254675U CN 201420642719 U CN201420642719 U CN 201420642719U CN 204254675 U CN204254675 U CN 204254675U
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- distribution plate
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Abstract
A distribute type cooling structure for gas-turbine combustion chamber burner inner liner, belongs to gas turbine technology field.This structure comprises distance sleeve, front flow distribution plate and rear flow distribution plate; Distance sleeve is arranged in described annular return air duct, and annular return air duct is divided into cooling duct and shunt air passage; Front flow distribution plate and rear flow distribution plate are provided with Cooling Holes and tap hole, and return air enters cooling duct and shunt air passage respectively by Cooling Holes and tap hole.Because annular return air duct is divided into cooling duct and shunt air passage by distance sleeve, under the effect of Cooling Holes and tap hole, make more air through burner inner liner near surface, the cooling of burner inner liner is significantly improved, obviously can reduce the wall surface temperature of burner inner liner; Cooling Holes and tap hole can change the pressure loss simultaneously, can regulate targetedly according to the actual operating state of combustion chamber to the pressure loss, thus meet the overall demand to pressure.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of distribute type 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, 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 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, 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 distribute 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 distribute 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: described cooling structure comprises distance sleeve, front flow distribution plate and rear flow distribution plate, distance sleeve is arranged in described annular return air duct, and annular return air duct is divided into cooling duct and shunt air passage; Described front flow distribution plate and rear flow distribution plate are separately positioned on the front-end and back-end of distance sleeve, and are separately fixed on the inwall of water conservancy diversion lining; Front flow distribution plate and rear flow distribution plate are provided with multiple Cooling Holes circumferentially and tap hole, and described Cooling Holes and tap hole are connected with shunt air passage with cooling duct respectively.
In technique scheme, the ratio of the radial spacing of described distance sleeve distance burner inner liner and the radial spacing of distance sleeve distance water conservancy diversion lining is between 1.5 ~ 3:1.
Technical characteristic of the present utility model is also: described Cooling Holes and described tap hole are for circular or fan-shaped; The ratio of the gross area of described Cooling Holes and the gross area of described tap hole controls between 2 ~ 4:1.
The utility model has the following advantages and the technique effect of high-lighting: 1. because annular return air duct is divided into cooling duct and shunt air passage by distance sleeve, under the effect of Cooling Holes and tap hole, return air can be divided into two parts, make more air through burner inner liner near surface, the cooling of burner inner liner is significantly improved, obviously can reduces the wall surface temperature of burner inner liner; 2. Cooling Holes and tap hole can change the pressure loss, can regulate targetedly according to the actual operating state of combustion chamber to the pressure loss, thus meet the overall demand to pressure.
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; Flow distribution plate before 3a-; Flow distribution plate after 3b-; 4-distance sleeve; 5-cooling duct; 6-shunt air passage; 7-Cooling Holes; 8-tap 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.Following instance for illustration of the utility model, but is not used in restriction scope of the present utility model.
Fig. 1 is the structural representation of the gas-turbine combustion chamber burner inner liner with cooling structure, the outer setting of burner inner liner 2 has water conservancy diversion lining 1, annular return air duct is formed between water conservancy diversion lining and burner inner liner, cooling structure comprises distance sleeve 4, front flow distribution plate 3a and rear flow distribution plate 3b, distance sleeve is arranged in described annular return air duct, and annular return air duct is divided into cooling duct 5 and shunt air passage 6, described front flow distribution plate 3a and rear flow distribution plate 3b is separately positioned on the front-end and back-end of distance sleeve 4, and be separately fixed on the inwall of water conservancy diversion lining, front flow distribution plate 3a with rear flow distribution plate 3b are provided with Cooling Holes 7 be connected with shunt air passage with cooling duct respectively with tap hole 8.Enter in cooling duct by the air of Cooling Holes, Convective heat tranfer cooling is carried out to burner inner liner outside wall surface, make air enter shunt air passage by tap hole.
Fig. 2 and Fig. 3 is respectively A-A sectional view and the three-dimensional structure schematic diagram of the utility model embodiment in Fig. 1, distance sleeve 4 apart from the radial spacing of burner inner liner 2 and distance sleeve apart from the ratio of the radial spacing of water conservancy diversion lining 1 between 1.5 ~ 3:1, make more air through burner inner liner near surface, to ensure that there are enough sectional areas cooling duct 5, avoid the too high pressure loss.Described Cooling Holes 7 and tap hole 8 are circular or fan-shaped.The area ratio of described Cooling Holes 7 and tap hole 8 controls between 2 ~ 4:1., enter cooling duct 5 cool to ensure enough air; According to the air pressure adjustable Cooling Holes 7 of locality and the area ratio of tap hole 8, to adapt to local environment and to meet total demand.
Claims (4)
1. the distribute 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 is formed between water conservancy diversion lining and burner inner liner, it is characterized in that: described cooling structure comprises distance sleeve (4), front flow distribution plate (3a) and rear flow distribution plate (3b), distance sleeve (4) is arranged in described annular return air duct, and annular return air duct is divided into cooling duct (5) and shunt air passage (6); Described front flow distribution plate (3a) and rear flow distribution plate (3b) are separately positioned on the front-end and back-end of distance sleeve (4), and are separately fixed on the inwall of water conservancy diversion lining (1); Front flow distribution plate and rear flow distribution plate are provided with multiple Cooling Holes (7) circumferentially and tap hole (8), and described Cooling Holes (7) is connected with shunt air passage (6) with cooling duct (5) respectively with tap hole (8).
2. the distribute type cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1, it is characterized in that, the ratio of the radial spacing of the radial spacing of distance sleeve (4) distance burner inner liner (2) and distance sleeve distance water conservancy diversion lining (1) is between 1.5 ~ 3:1.
3. the distribute type cooling structure of a kind of gas-turbine combustion chamber burner inner liner as claimed in claim 1 or 2, is characterized in that, the ratio of the gross area of described Cooling Holes (7) and the gross area of described tap hole (8) controls between 2 ~ 4:1.
4. the distribute type 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 (7) and described tap hole (8) are circular or fan-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420642719.0U CN204254675U (en) | 2014-10-31 | 2014-10-31 | A kind of distribute type cooling structure of gas-turbine combustion chamber burner inner liner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420642719.0U CN204254675U (en) | 2014-10-31 | 2014-10-31 | A kind of distribute type cooling structure of gas-turbine combustion chamber burner inner liner |
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| CN204254675U true CN204254675U (en) | 2015-04-08 |
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| CN201420642719.0U Active CN204254675U (en) | 2014-10-31 | 2014-10-31 | A kind of distribute type cooling structure of gas-turbine combustion chamber burner inner liner |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110565479A (en) * | 2019-09-27 | 2019-12-13 | 中信国安建工集团有限公司 | Ecological pavement construction method |
| CN115200041A (en) * | 2022-07-19 | 2022-10-18 | 中国航发沈阳发动机研究所 | Low-emission combustor flame tube |
-
2014
- 2014-10-31 CN CN201420642719.0U patent/CN204254675U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110565479A (en) * | 2019-09-27 | 2019-12-13 | 中信国安建工集团有限公司 | Ecological pavement construction method |
| CN115200041A (en) * | 2022-07-19 | 2022-10-18 | 中国航发沈阳发动机研究所 | Low-emission combustor flame tube |
| CN115200041B (en) * | 2022-07-19 | 2023-06-20 | 中国航发沈阳发动机研究所 | Low-emission combustor flame tube |
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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: Distribution type cooling structure of gas turbine combustion chamber flame tube 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 |
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 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |