CN204404242U - There is the combustion chamber of porous burner inner liner - Google Patents
There is the combustion chamber of porous burner inner liner Download PDFInfo
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- CN204404242U CN204404242U CN201420811065.XU CN201420811065U CN204404242U CN 204404242 U CN204404242 U CN 204404242U CN 201420811065 U CN201420811065 U CN 201420811065U CN 204404242 U CN204404242 U CN 204404242U
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- inner liner
- burner inner
- air
- admission hole
- air admission
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Abstract
A kind of combustion chamber with porous burner inner liner, it comprises burning chamber shell and burner inner liner that at least one is surrounded by described burning chamber shell, described burning chamber shell and burner inner liner spaced apart to form gas channel, described burner inner liner defines a burner inner liner axis.Described burner inner liner has multiplely allows the air-flow in described gas channel enter described burner inner liner to form the air admission hole of air film at the internal face of described burner inner liner, described air admission hole guides described air-flow to advance towards the downstream direction of described burner inner liner, each air admission hole defines an air admission hole axis, each air admission hole axis tilts to described downstream direction and deviates from described burner inner liner axis, makes the air entering burner inner liner form the eddy flow of advancing with the path of helix at the internal face of burner inner liner.
Description
Technical field
The present invention relates to a kind of combustion chamber of gas turbine, particularly relate to a kind of combustion chamber with porous burner inner liner.
Background technology
The heating process in the thermodynamic cycle of gas turbine has been responsible in the combustion chamber of gas turbine, its function is heat energy by the converts chemical energy in fuel, the temperature allowed before pressure-air after compressor pressure is heated to turbine, does manual work to enter in turbine and exhaust apparatus to expand.Generally speaking, turbine inlet temperature is higher, and the efficiency of turbogenerator also can be higher.But temperature is higher, for combustion chamber, particularly the heat resistance of its burner inner liner proposes larger challenge.
In existing burner inner liner design; its cylindrical shell generally can be provided with perforate; the air allowing a part come from compressor enters in the combustion chamber of cylindrical shell formation via these perforates; to form air film at cylinder inner surface; open so that cylindrical shell is intercepted with the flame/high temperature gas flow formed by burning, thus the high temperature protection to cylindrical shell is provided.
On the other hand, miniature gas turbine plays more and more important role in distributed power generation network.Under the prerequisite that can meet performance requirement, the volume reducing combustion chamber is that one of target asked most is researched and developed in combustion chamber always.
Summary of the invention
In view of this, the present invention proposes a kind of Combustion chamber design that can reduce combustion chamber dimensions.
The combustion chamber with porous burner inner liner that the present invention proposes, comprise burning chamber shell and burner inner liner that at least one is surrounded by described burning chamber shell, described burning chamber shell and burner inner liner spaced apart to form gas channel, described burner inner liner defines a burner inner liner axis.Described burner inner liner has multiplely allows the air-flow in described gas channel enter described burner inner liner to form the air admission hole of air film at the internal face of described burner inner liner, described air admission hole guides described air-flow to advance towards the downstream direction of described burner inner liner, each air admission hole defines an air admission hole axis, each air admission hole axis tilts to described downstream direction and deviates from described burner inner liner axis, makes the air entering burner inner liner form the eddy flow of advancing with the path of helix at the internal face of burner inner liner.
In certain embodiments, the angle between air admission hole axis and burner inner liner internal face is between 5-45 degree.
Have in the combustion chamber of porous burner inner liner above-mentioned, air admission hole axis is that downstream tilts and deviates from burner inner liner axis, and the air therefore entering burner inner liner can form the eddy flow of advancing with the path of helix at the internal face of burner inner liner.The air flowed in these paths along helix can drive the flame of at least periphery to carry out swirling motion, thus the physical length of flame can be extended or reduce the axial length of flame when obtaining the identical length of flame, thus reduce the overall volume of burner inner liner axial dimension and combustion chamber.
Accompanying drawing explanation
Fig. 1 is the rough schematic view of an embodiment of the combustion chamber of gas turbine.
Fig. 2 and Fig. 3 depicts the angle of inclination of air admission hole relative to burner inner liner axis.
Detailed description of the invention
Before describing the embodiments in more detail, it should be understood that and the invention is not restricted to detailed construction in the application hereafter or described in accompanying drawing or arrangement of elements.The present invention can be the embodiment that alternate manner realizes.And, should be appreciated that wording used herein and term are only used as to describe purposes, should being construed as limiting property not explain.Similar wording meant and comprised item listed thereafter, its equivalent and other additional things " comprising " used herein, " comprising ", " having " etc.
Fig. 1 is an embodiment simplified construction figure of the combustion chamber of gas turbine.Combustion chamber 10 comprises burning chamber shell 12 and at least one burner inner liner 14.Burning chamber shell 12 surrounds burner inner liner 14, and combustion chamber 12 and burner inner liner 14 is spaced apart to form gas channel 16 betwixt.According to the type of combustion chamber 10, the quantity of housing 12 flame cylinder 14 can be one or more.
Burner inner liner 14 is around formation combustion chamber.The cylindrical shell of burner inner liner 14 is formed multiple air admission hole 18.The air part that the compressor (not shown) of gas turbine is come enters combustion chamber and fuel generation combustion reaction, some air enters the gas channel 16 between burning chamber shell 12 and burner inner liner 14, and enter burner inner liner 14 via these air admission holes 18 and advance to the downstream direction of burner inner liner 14, form air film at the internal face of burner inner liner 14, burner inner liner 14 and thermal-flame 19 are intercepted and opens.It will be apparent to those skilled in the art that alleged downstream direction refers to the direction that burner inner liner 14 combustion product entirety is advanced herein.
Fig. 2 and Fig. 3 exemplifies the one structure of these air admission holes 18.Simultaneously with reference to figure 1-3, these air admission holes 18 are obliquely installed towards downstream direction, so that air is introduced burner inner liner 14 with the angle tilted.Air admission hole 18 defines an air admission hole axis 20, and burner inner liner 14 defines a burner inner liner axis 22.In figs. 2 and 3, only draw the axis of air admission hole 18 and burner inner liner 14, describe the incline direction of air admission hole 18 with the relation of air admission hole axis 20 and burner inner liner axis 22.As Fig. 2, from the angle of the cross-sectional view strength of burner inner liner 14 (namely from along burner inner liner axis 22), burner inner liner axis 22 is departed from air admission hole axis 20, and namely the extended line of air admission hole axis 20 and burner inner liner axis 22 are disjoint.In certain embodiments, the angle between air admission hole axis 20 and burner inner liner 14 internal face is between 5-45 degree.As Fig. 3, from the angle of perpendicular to burner inner liner axis 22, air admission hole axis 20 is that downstream tilts, and air-flow downstream therefore can be guided to advance.Therefore, air admission hole axis 20 is that downstream tilts and deviates from burner inner liner axis 22.
The air that the air admission hole 18 tilted by these enters burner inner liner 14 can form the eddy flow of advancing with the path of helix 24 at the internal face of burner inner liner 14.Combustion flame 19 in burner inner liner 14 not only intercepts with burner inner liner 14 internal face by the air of these paths along helix 24 flowing to be opened, and the flame of at least periphery (that a part of flame contacted with air) can be driven to carry out swirling motion.Compared with the existing flame extended vertically, on same axial length, the flame of swirling motion will have the larger length of flame, thus make burning more abundant.On the other hand, in order to obtain the flame of equal length, the flame of swirling motion will have less axial length, therefore can reduce the axial length of combustion chamber, and then reduce the volume of burner inner liner axial dimension and gas turbine complete machine.
In sum, there is described herein a kind of combustion chamber with porous burner inner liner.Air admission hole axis is that downstream tilts and deviates from burner inner liner axis, and the air therefore entering burner inner liner can form the eddy flow of advancing with the path of helix at the internal face of burner inner liner.The air flowed in these paths along helix can drive the flame of at least periphery to carry out swirling motion, thus the physical length of flame can be extended or reduce the axial length of flame when obtaining the identical length of flame, thus reduce burner inner liner axial dimension.
Concept described herein may be embodied to other form when not departing from its spirit and characteristic.Disclosed specific embodiment should be regarded as exemplary instead of restrictive.Therefore, scope of the present invention is by appended claim, instead of determines according to these descriptions before.Any change in the letter and equivalency range of claim all should belong to the scope of these claims.
Claims (2)
1. one kind has the combustion chamber of porous burner inner liner, it comprises burning chamber shell and burner inner liner that at least one is surrounded by described burning chamber shell, described burning chamber shell and burner inner liner spaced apart to form gas channel, described burner inner liner defines a burner inner liner axis, it is characterized in that, described burner inner liner has multiplely allows the air-flow in described gas channel enter described burner inner liner to form the air admission hole of air film at the internal face of described burner inner liner, described air admission hole guides described air-flow to advance towards the downstream direction of described burner inner liner, each air admission hole defines an air admission hole axis, each air admission hole axis tilts to described downstream direction and deviates from described burner inner liner axis, the air entering burner inner liner is made to form the eddy flow of advancing with the path of helix at the internal face of burner inner liner.
2. have the combustion chamber of porous burner inner liner as claimed in claim 1, it is characterized in that, the angle between described air admission hole axis and described burner inner liner internal face is between 5-45 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420811065.XU CN204404242U (en) | 2014-12-18 | 2014-12-18 | There is the combustion chamber of porous burner inner liner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420811065.XU CN204404242U (en) | 2014-12-18 | 2014-12-18 | There is the combustion chamber of porous burner inner liner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204404242U true CN204404242U (en) | 2015-06-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420811065.XU Active CN204404242U (en) | 2014-12-18 | 2014-12-18 | There is the combustion chamber of porous burner inner liner |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016095157A1 (en) * | 2014-12-18 | 2016-06-23 | 深圳智慧能源技术有限公司 | Combustion chamber having porous flame tube |
| WO2021083338A1 (en) * | 2019-10-31 | 2021-05-06 | 芜湖美的厨卫电器制造有限公司 | Gas device |
-
2014
- 2014-12-18 CN CN201420811065.XU patent/CN204404242U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016095157A1 (en) * | 2014-12-18 | 2016-06-23 | 深圳智慧能源技术有限公司 | Combustion chamber having porous flame tube |
| WO2021083338A1 (en) * | 2019-10-31 | 2021-05-06 | 芜湖美的厨卫电器制造有限公司 | Gas device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
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| TR01 | Transfer of patent right |
Effective date of registration: 20150924 Address after: 518000 Guangdong city Shenzhen province two Bagua road Futian District Xufei garden C building 18 floor 1804-2 unit Patentee after: Wisdom Energy Technology (Shenzhen) Corporation Ltd. Address before: 518000 Guangdong city of Shenzhen province Futian District Fuhua Road No. 6 Building 1403 business tax Patentee before: Wang Qiwen |