CN204404235U - A kind of gas-turbine combustion chamber changeover portion with cooling structure - Google Patents
A kind of gas-turbine combustion chamber changeover portion with cooling structure Download PDFInfo
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- CN204404235U CN204404235U CN201420843500.7U CN201420843500U CN204404235U CN 204404235 U CN204404235 U CN 204404235U CN 201420843500 U CN201420843500 U CN 201420843500U CN 204404235 U CN204404235 U CN 204404235U
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- changeover portion
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- combustion chamber
- cooling
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Abstract
With a gas-turbine combustion chamber changeover portion for cooling structure, belong to gas turbine technology field.The outer surface of changeover portion body is provided with multiple cooling component, and each cooling component comprises linkage section and radiating piece; Multiple cooling component is array distribution, two adjacent row cooling component stagger arrangement distributions.The shape of radiating piece be bowl-shape, helical form, dendroid or other can increase the shape that surface area has again less flow resistance.The utility model by increasing the heat exchange area of changeover portion outer surface, can reduce changeover portion temperature, extending the life-span of changeover portion; Cooling structure does not destroy the integrality of changeover portion body simultaneously, does not affect the reliability of thermal barrier coating, is conducive to the effect of heat insulation improving thermal barrier coating; The pressure loss that cooling structure brings is low, is conducive to the efficiency improving gas turbine.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of gas-turbine combustion chamber changeover portion with cooling structure.
Background technology
Heavy duty gas turbine, usually uses some cylindrical combustion chambers, produces hot combustion gas, introduces the first order turbine stator blade of engine.The hot combustion gas of the preferably annular that first order turbine stator blade accepts.By a changeover portion, be positioned between each combustion chamber and first order turbine stator blade, the gas flow field sprayed from each combustion chamber, cylindrical from roughly, changes over a part for annular.Thus the air-flow of all changeover portion ejections, produce desirable annular airflow.
The thermodynamic efficiency that Thermal Motor may obtain, depends on the maximum temperature of its working fluid, for gas turbine, then depends on the hot combustion gas of discharging from combustion chamber.The maximum safety temperature of hot combustion gas, is subject to the restriction with the operating temperature limit of the metal parts of this hot contacts fuel gas, and depends on the ability these parts being cooled to below hot gas temperature.The cooling task of advanced heavy duty gas turbine combustion chamber changeover portion is inconvenient, because cooling means known now, if not scarce capacity, is be attended by the cost that cannot bear.
In a kind of traditional gas-turbine combustion chamber, the outer surface of changeover portion increases a sleeve pipe, leaving the short distance placement of changeover portion outer surface, impact the array that sleeve pipe has an eyelet, the air that compressor is discharged passes through from the inside, produce a jet array, changeover portion outer surface is collided and cools.This method needs to there is enough pressure differentials between impingement sleeve and changeover portion outer surface, means that the compressed air that compressor produces can occur certain pressure loss after flowing through changeover portion outer surface.If Pressure Drop is too high, so the thermodynamic efficiency of gas turbine declines.
There is another kind for the cooling technology to changeover portion, be offer diffusion cooling hole on changeover portion, one deck cooling-air film can be formed at changeover portion inner surface, to a certain extent isolated hot combustion gas and changeover portion metal.Because changeover portion inner surface need spray thermal barrier coating, so the process holding diffusion cooling hole can cause damage to a certain degree to thermal barrier coating.Easily peel off after thermal barrier coating sustains damage, cause coming off.Exposed changeover portion temperature will obviously raise, and severe patient even causes changeover portion to be burnt.
Utility model content
The purpose of this utility model is to provide a kind of gas-turbine combustion chamber changeover portion with cooling structure, and this technical scheme by increasing the heat exchange area of changeover portion outer surface, can reduce changeover portion temperature, extending the life-span of changeover portion.
To achieve these goals, a kind of gas-turbine combustion chamber changeover portion with cooling structure that the utility model provides, described changeover portion comprises the outlet of changeover portion entrance, changeover portion body and changeover portion; It is characterized in that: described changeover portion body has multiple cooling component, each described cooling component comprises linkage section and radiating piece, and one end of linkage section is fixed on the outer surface of changeover portion body, and the other end of linkage section is connected with radiating piece.
Wherein, described cooling component array distribution, two adjacent row cooling component stagger arrangement distributions.
Wherein, formed by the normal of the outer surface of the axis of described linkage section and the changeover portion body of region, angle is more than or equal to 0 degree and is less than or equal to 5 degree.
Wherein, the shape of described radiating piece is bowl-shape, helical form or dendroid.
The gas-turbine combustion chamber changeover portion of what the utility model provided have cooling structure has the following advantages and the technique effect of high-lighting: 1. cooling structure can increase the heat exchange area of changeover portion outer surface, the metal temperature of remarkable reduction changeover portion body, contributes to the use extending changeover portion; 2. cooling structure does not destroy the integrality of changeover portion body, does not affect the reliability of thermal barrier coating, is conducive to the effect of heat insulation improving thermal barrier coating; 3. the pressure loss brought of cooling structure is low, is conducive to the efficiency improving gas turbine.
Accompanying drawing explanation
Fig. 1 is the three-dimensional structure schematic diagram of the gas-turbine combustion chamber changeover portion with cooling structure.
Fig. 2 is the A-A sectional view of Fig. 1.
Fig. 3 a, Fig. 3 b and Fig. 3 c are respectively the structural representation of the several different embodiment of the cooling structure of gas-turbine combustion chamber changeover portion.
In figure, 1 – changeover portion; 2 – changeover portion entrances; 3 – changeover portion bodies; 4 – changeover portion outlets; 5 – cooling components; 6 – linkage sections; 7 – radiating pieces.
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.Following instance for illustration of the utility model, but is not used in restriction scope of the present utility model.
As depicted in figs. 1 and 2, described changeover portion 1 comprises changeover portion entrance 2, changeover portion body 3 and changeover portion outlet 4, high-temperature fuel gas enters changeover portion by changeover portion entrance 2, in the internal flow of changeover portion body 3, be transitioned into sector crosssection gradually from circular cross-section, changeover portion outlet 4 is similarly fan-shaped, and multiple changeover portion 1 lines up a circle around combustion engine axis, multiple changeover portion outlet 4 forms annular, enters turbine one-level stator blade.Changeover portion body 3 has multiple cooling component 5, each described cooling component 5 comprises linkage section 6 and radiating piece 7, and cooling component 5 is fixed on the outer surface of changeover portion body 3 by one end of linkage section 6, and radiating piece 7 is fixed on the other end of linkage section 6.Cooling component 5 array distribution, two adjacent row cooling component 5 stagger arrangement distributions.The axis of linkage section 6 is approximately perpendicular to the outer surface of the changeover portion body 3 of its region, formed by the normal of the outer surface of the axis of linkage section 6 and the changeover portion body 3 of region, angle should be more than or equal to 0, and be less than or equal to 5 degree, to avoid reducing changeover portion superficial air flowing speed.
Fig. 3 a, Fig. 3 b and Fig. 3 c are the structural representation of the several different embodiment of the cooling structure of gas-turbine combustion chamber changeover portion, and the radiating piece 7 wherein shown in Fig. 3 a is bowl-shape, and the radiating piece 7 shown in Fig. 3 b is helical form, and the radiating piece 7 shown in Fig. 3 c is dendroid.Radiating piece 7 increases surface area, to improve heat exchange efficiency by reasonably designing.Radiating piece 7 has less flow resistance, to reduce the pressure loss simultaneously.Several cooling component 5 is fixed on changeover portion outer surface by welding, 3D printing or alternate manner above.Relative to dispersing cooling, an outstanding advantage does not need to open elongated hole on changeover portion body 3, both can reduce difficulty of processing, and have and perforate and thermal barrier coating can be avoided to have a negative impact each other; Relative to impinging cooling, there is the lower pressure loss, effectively can improve the efficiency of gas turbine.
Claims (4)
1., with a gas-turbine combustion chamber changeover portion for cooling structure, described changeover portion (1) comprises changeover portion entrance (2), changeover portion body (3) and changeover portion outlet (4); It is characterized in that: described changeover portion body (3) has multiple cooling component (5), each described cooling component (5) comprises linkage section (6) and radiating piece (7), one end of linkage section is fixed on the outer surface of changeover portion body (3), and the other end of linkage section is connected with radiating piece (7).
2. a kind of gas-turbine combustion chamber changeover portion with cooling structure as claimed in claim 1, is characterized in that, described cooling component (5) array distribution, two adjacent row cooling component (5) stagger arrangement distributions.
3. a kind of gas-turbine combustion chamber changeover portion with cooling structure as claimed in claim 1, it is characterized in that, formed by the normal of the outer surface of the axis of described linkage section (6) and the changeover portion body (3) of region, angle is more than or equal to 0 degree and is less than or equal to 5 degree.
4. a kind of gas-turbine combustion chamber changeover portion with cooling structure as described in claim 1,2 or 3, is characterized in that, the shape of described radiating piece (7) is bowl-shape, helical form or dendroid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420843500.7U CN204404235U (en) | 2014-12-25 | 2014-12-25 | A kind of gas-turbine combustion chamber changeover portion with cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420843500.7U CN204404235U (en) | 2014-12-25 | 2014-12-25 | A kind of gas-turbine combustion chamber changeover portion with cooling structure |
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| Publication Number | Publication Date |
|---|---|
| CN204404235U true CN204404235U (en) | 2015-06-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420843500.7U Active CN204404235U (en) | 2014-12-25 | 2014-12-25 | A kind of gas-turbine combustion chamber changeover portion with cooling structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566458A (en) * | 2014-12-25 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine combustor transition section with cooling structure |
| CN107035532A (en) * | 2015-12-22 | 2017-08-11 | 通用电气公司 | Classification fuel and air injection in the combustion system of combustion gas turbine |
-
2014
- 2014-12-25 CN CN201420843500.7U patent/CN204404235U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566458A (en) * | 2014-12-25 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine combustor transition section with cooling structure |
| CN107035532A (en) * | 2015-12-22 | 2017-08-11 | 通用电气公司 | Classification fuel and air injection in the combustion system of combustion gas turbine |
| CN107035532B (en) * | 2015-12-22 | 2021-04-02 | 通用电气公司 | Staged fuel and air injection in a combustion system of a gas turbine |
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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 | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Gas turbine combustor transition section with cooling structure Effective date of registration: 20171115 Granted publication date: 20150617 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 | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150617 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191225 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |