CN104566474A - Fuel and air mixer and gas turbine - Google Patents
Fuel and air mixer and gas turbine Download PDFInfo
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- CN104566474A CN104566474A CN201410843175.9A CN201410843175A CN104566474A CN 104566474 A CN104566474 A CN 104566474A CN 201410843175 A CN201410843175 A CN 201410843175A CN 104566474 A CN104566474 A CN 104566474A
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Abstract
The invention relates to the technical field of power equipment, in particular to a fuel and air mixer and a gas turbine. The fuel and air mixer comprises a central body, an annular wall and a cyclone device. A head end wall of the central body is arranged at the tail end of the central body, an end wall of the annular wall is arranged at the tail end of the annular wall, an opposite impact pipe cavity between the head end wall of the central body and the end wall of the annular wall is enclosed by a ring wall of the opposite impact pipe cavity, and opposite impact gas flow holes which are communicated with mixing channels are formed in the ring wall of the opposite impact pipe cavity. The fuel and air mixer and the gas turbine have the advantages that fuel and air mixtures which are sprayed out of opposite impact jet holes are high in momentum, and the uniformity of the fuel and air mixtures further can be improved after opposite impact jet pairs are impacted by one another; local backflow regions can be formed in upstream regions of the opposite impact jet holes and peripheral regions between the opposite impact jet holes, so that the flame stability can be improved advantageously; the fuel and air mixer and the gas turbine are simple in structure, easy to implement and free of constraints of other components of a combustion chamber and problems in the aspects of matching and the like.
Description
Technical field
The present invention relates to chain drive technical field, particularly relate to a kind of fuel-air blender and gas turbine, be specifically related to a kind of fuel-air blender adopting opposed jets.
Background technology
At present; along with energy scarcity and the whole world are to the attention of environmental protection problem; the requirement of various countries to gas-turbine combustion chamber discharge and efficiency of combustion is more and more stricter; General Requirements gas turbine is between 50% and above loading zone; combustion chamber discharge can maintain reduced levels, keeps higher efficiency of combustion simultaneously.In order to reach the object of low emission, premixed combustion technology is widely adopted.Therefore, need to realize the device that fuel and air are pre-mixed, i.e. fuel-air blender, and form the fuel-air mixture mixing and have certain speed type at mixer outlet place, and then enter in burner inner liner and participate in burning.
Because the mode of fuel with premixed flame in combustion chamber ejected from fuel-air blender is burnt, for reaching extremely low disposal of pollutants, flame is operated near flammable border, add that the fuel-air mixture body effluxvelocity that blender ejects is larger, the stable of flame is more difficult, in prior art solution normally centerbody axial length be less than the length of fuel-air blender outside wall surface, fuel-air mixture body is first expanded to the central area in centerbody head end wall downstream when annular premixed channel flows out, in the formation recirculating zone, central area in centerbody head end wall downstream, then expansion further in the inherent burner inner liner of burner inner liner is entered, and then in burner inner liner, form larger recirculation zone, stablizing for flame, but these two recirculation zone are subject to the influence of other air-flows in burner inner liner, flame is existed can not stablize or the risk of poor stability.
In order to improve the stability of flame, in existing patent document (CN1704574), have employed the manufacture shock air contrary with main flow flow direction near mixer outlet centerbody to flow, form recirculation eddy current, decrease the air capacity be ejected in recirculating zone, thus effluxvelocity near reduction mixer outlet, improve flame holding.And the structure processing connections such as this blender internal layer baffle plate wait comparatively complicated, and be not easy to maintain and replace, and recycle eddy current and be not easy to control, be likely difficult to solve steady fiery problem.
Therefore, for above deficiency, need a kind of stability contributing to improving flame, structure is simple, not space-constrained fuel-air blender and gas turbine.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention there is provided a kind of fuel-air blender and gas turbine, and this fuel-air blender can realize the stability contributing to improving flame, and structure is simple, and not by the restriction in space.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of fuel-air blender, it comprises centerbody, annular wall and swirl-flow devices, described annular wall is coaxially arranged on the periphery of centerbody, between annular wall and centerbody, form hybrid channel, described swirl-flow devices is positioned on hybrid channel and the front end of close centerbody; The end of described centerbody is provided with centerbody head end wall, the end of described annular wall is provided with annular wall end wall, be enclosed to form by the tube chamber ring wall that liquidates the tube chamber that liquidates between described centerbody head end wall and annular wall end wall, described in the tube chamber ring wall that liquidates be provided with the airflow hole that liquidates be communicated with described hybrid channel.
Wherein, described in liquidate on tube chamber ring wall and at least offer the airflow hole that liquidates for a pair, and the axial line of the airflow hole that liquidates of each centering is identical.
Wherein, described in the airflow hole that liquidates be straight hole, described in the liquidate hole shape of airflow hole be circular or oval or rectangle.
Wherein, described centerbody head end wall is provided with centerbody head end wall spray-hole, and described annular wall end wall is provided with annular wall end wall spray-hole.
Wherein, described centerbody head end wall spray-hole and annular wall end wall spray-hole are straight hole or inclined hole.
Wherein, the diameter of described centerbody head end wall is not less than the diameter of centerbody.
Wherein, the axial location of described centerbody head end wall is in the axial range of annular wall.
Wherein, described swirl-flow devices comprises the swirl vane that centrally body circumference is arranged, and described swirl vane is provided with teasehole, and described centerbody is provided with the fuel channel be communicated with teasehole.
The present invention also provides a kind of gas turbine, and it comprises described fuel-air blender.
(3) beneficial effect
Technique scheme of the present invention has following beneficial effect: the invention provides a kind of fuel-air blender, the fuel-air mixture ejected from opposed jets hole has larger momentum, paired opposed jets, after impacting mutually, realizes the mixing uniformity improving fuel air mixture further; And, in limited physical space, also can form local return district by the circumferential zones between the region of upstream, opposed jets hole and opposed jets hole, thus contribute to the stability improving flame; This fuel-air mixer structure is simple, easily realizes, and not by the restriction of combustion chamber miscellaneous part, the problem such as not to mate.
Accompanying drawing explanation
Fig. 1 is the structural representation of embodiment of the present invention fuel-air blender;
Fig. 2 is the schematic perspective view of embodiment of the present invention fuel-air blender;
Fig. 3 is the using state figure of embodiment of the present invention fuel-air blender.
Wherein, 1: centerbody; 2: annular wall; 3: swirl-flow devices; 4: centerbody head end wall; 5: centerbody head end wall spray-hole; 6: liquidate tube chamber; 7: annular wall end wall; 8: liquidate tube chamber ring wall; 9: liquidate airflow hole; 10: annular wall end wall spray-hole; 11: swirl vane; 12: teasehole; 13: fuel channel; 14: liquidate air-flow; 15: recirculating zone in the chamber that liquidates; 16: hybrid channel.
Detailed description of the invention
Below in conjunction with drawings and Examples, embodiments of the present invention are described in further detail.Following examples for illustration of the present invention, but can not be used for limiting the scope of the invention.
In describing the invention, except as otherwise noted, the implication of " multiple " is two or more; Term " on ", D score, "left", "right", " interior ", " outward ", " front end ", " rear end ", " head ", the orientation of the instruction such as " afterbody " or position relationship be based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.In addition, term " first ", " second ", " the 3rd " etc. only for describing object, and can not be interpreted as instruction or hint relative importance.
In describing the invention, it should be noted that, unless otherwise clearly defined and limited, term " is connected ", " connection " should be interpreted broadly, such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary.For the ordinary skill in the art, concrete condition above-mentioned term concrete meaning in the present invention can be understood.
As Figure 1-3, the fuel-air blender described in the present embodiment, it comprises centerbody 1, annular wall 2 and swirl-flow devices 3, and annular wall 2 is coaxially arranged on the periphery of centerbody 1, forms hybrid channel 16 between annular wall 2 and centerbody 1.Swirl-flow devices 3 is positioned on the hybrid channel 16 and front end of close centerbody 1, that is, between centerbody 1 and annular wall 2, for the formation of eddy flow; The end of centerbody 1 is provided with centerbody head end wall 4, and accordingly, the end of annular wall 2 is provided with annular wall end wall 7.And, be enclosed to form by the tube chamber ring wall 8 that liquidates the tube chamber 6 that liquidates between centerbody head end wall 4 and annular wall end wall 7, that is, liquidate tube chamber ring wall 8 between centerbody head end wall 4 and annular wall end wall 7.The tube chamber 6 that liquidates formed is the chamber structure of open at one end shape, and its shape is not limited to certain particular form.At the airflow hole 9 that liquidates tube chamber ring wall 8 being provided with and being communicated with hybrid channel 16 that liquidates.
During use, the fuel-air mixture ejected from opposed jets hole 9 has larger momentum, and paired opposed jets, after impacting mutually, can further improve the mixing uniformity of fuel air mixture; And, in limited physical space, also can form local return district by the circumferential zones between the region of upstream, opposed jets hole 9 and opposed jets hole 9, contribute to the stability improving flame.
As shown in Figure 2, at least offer the airflow hole 9 that liquidates for a pair liquidating on tube chamber ring wall 8, and the axial line of the airflow hole 9 that liquidates of each centering is identical, thus can opposed jets be formed.
Further, airflow hole 9 is liquidated for straight hole.Such as, and the hole shape (cross section) of the airflow hole 9 that liquidates is circular or oval or rectangle, certainly, also can select the airflow hole 9 that liquidates of other hole shapes according to actual needs: pentagon etc.
The centerbody head end wall 4 of the present embodiment is provided with centerbody head end wall spray-hole 5, and meanwhile, annular wall end wall 7 is provided with annular wall end wall spray-hole 10.Wherein, centerbody head end wall spray-hole 5 is for being communicated with centerbody inner passage and liquidating tube chamber 6, and annular wall end wall spray-hole 10 is for being communicated with the ignition zone of hybrid channel 16 and burner inner liner.Certainly, centerbody head end wall spray-hole 5 also can be multiple with the form of annular wall end wall spray-hole 10, such as: straight hole or inclined hole.Wherein, straight hole is the through hole offered vertically, and inclined hole is the through hole offered with the direction vector of radial direction vertically.In addition, also for the tangential hole for making fuel be rotated through, certainly, the hole of other types can also be can be, such as, bellmouth etc.
Further, the diameter of centerbody head end wall 4 is not less than the diameter of centerbody 1.When the diameter of centerbody head end wall 4 is greater than the diameter of centerbody 1, and the radial space exceeded is when enough offering centerbody head end wall spray-hole 5, centerbody head end wall spray-hole 5 can spray a small amount of fuel-air mixture and enter the tube chamber 6 that liquidates, and most of fuel-air mixture is then by spraying in the tube chamber 6 that liquidates at the airflow hole 9 that liquidates that tube chamber ring wall 8 is offered in pairs that liquidates.
And the axial location of this centerbody head end wall 4 is in the axial range of annular wall 2, that is, centerbody head end wall 4 is within the coated scope of annular wall 2.
In the present embodiment, swirl-flow devices 3 comprises the swirl vane 11 that centrally body 1 circumference is arranged, and swirl vane 11 is provided with teasehole 12, centerbody 1 is provided with the fuel channel 13 be communicated with teasehole 12, for hybrid channel 16 transfer the fuel.
The present invention also provides a kind of gas turbine, and it comprises fuel-air blender, and this fuel-air mixer application is in the combustion chamber of gas turbine.
Operation principle of the present invention is as follows: first, extraneous air enters the hybrid channel 16 between centerbody 1 and annular wall 2 through the air-flow that swirl-flow devices 3 forms rotational flow, fuel enters the swirl vane 11 of hollow from fuel channel 13, and spray in hybrid channel 16 from the teasehole 12 that swirl vane 11 is arranged, air and the position of fuel residing for swirl-flow devices 3 start mixing, and flow through the axial location of the centerbody head end wall 4 of centerbody 1 end until annular wall end wall 7.
Afterwards, part of fuel air Mixture is directly injected into into burner inner liner by the annular wall end wall spray-hole 10 that annular wall end wall 7 is offered, and, centerbody head end wall spray-hole 5 can spray a small amount of fuel-air mixture and enter the tube chamber 6 that liquidates, and most of fuel-air mixture is by spraying in the tube chamber 6 that liquidates at the airflow hole 9 that liquidates that tube chamber ring wall 8 is offered in pairs that liquidates, the air-flow 14 that liquidates of large momentum impacts (as shown in Figure 3) mutually, except the mixing uniformity of fuel air mixture can be improved further, also the circumferential zones between the region and opposed jets hole of upstream, opposed jets hole is formed recirculating zone 15 (as shown in Figure 3) in the chamber that liquidates locally, this will contribute to the stability improving flame.
Simultaneously, the fuel-air mixture that the annular wall end wall spray-hole 10 that annular wall end wall 7 is offered sprays can cool annular wall end wall 7, the centerbody head end wall spray-hole 5 that centerbody head end wall 4 is offered can cool centerbody head end wall 4, and the air-flow of centerbody head end wall spray-hole 5 can not have obvious destruction to ensure stable recirculation zone to neighbouring recirculating zone.
To sum up, the invention provides a kind of fuel-air blender, the fuel-air mixture ejected from opposed jets hole has larger momentum, and paired opposed jets, after impacting mutually, realizes the mixing uniformity improving fuel air mixture further; And, in limited physical space, also can form local return district by the circumferential zones between the region of upstream, opposed jets hole and opposed jets hole, thus contribute to the stability improving flame; This fuel-air mixer structure is simple, easily realizes, and not by the restriction of combustion chamber miscellaneous part, the problem such as not to mate.
Embodiments of the invention provide in order to example with for the purpose of describing, and are not exhaustively or limit the invention to disclosed form.Many modifications and variations are apparent for the ordinary skill in the art.Selecting and describing embodiment is in order to principle of the present invention and practical application are better described, and enables those of ordinary skill in the art understand the present invention thus design the various embodiments with various amendment being suitable for special-purpose.
Claims (9)
1. a fuel-air blender, it is characterized in that, comprise centerbody (1), annular wall (2) and swirl-flow devices (3), described annular wall (2) is coaxially arranged on the periphery of centerbody (1), between annular wall (2) and centerbody (1), form hybrid channel (16), described swirl-flow devices (3) is positioned on hybrid channel (16) and the front end of close centerbody (1); It is characterized in that: the end of described centerbody (1) is provided with centerbody head end wall (4), the end of described annular wall (2) is provided with annular wall end wall (7), be enclosed to form the tube chamber that liquidates (6) by the tube chamber ring wall (8) that liquidates between described centerbody head end wall (4) and annular wall end wall (7), described in the tube chamber ring wall (8) that liquidates be provided with the airflow hole that liquidates (9) be communicated with described hybrid channel (16).
2. fuel-air blender according to claim 1, it is characterized in that, the airflow hole (9) that liquidates for a pair at least offered by the described tube chamber ring wall (8) that liquidates, and the axial line of the airflow hole that liquidates (9) of each centering is identical.
3. fuel-air blender according to claim 2, is characterized in that, described in the airflow hole (9) that liquidates be straight hole, described in the liquidate hole shape of airflow hole (9) be circular or oval or rectangle.
4. fuel-air blender according to claim 1, is characterized in that, described centerbody head end wall (4) is provided with centerbody head end wall spray-hole (5); Described annular wall end wall (7) is provided with annular wall end wall spray-hole (10).
5. fuel-air blender according to claim 4, is characterized in that, described centerbody head end wall spray-hole (5) and annular wall end wall spray-hole (10) are straight hole or inclined hole.
6. fuel-air blender according to claim 1, is characterized in that, the diameter of described centerbody head end wall (4) is not less than the diameter of centerbody (1).
7. fuel-air blender according to claim 1, is characterized in that, the axial location of described centerbody head end wall (4) is in the axial range of annular wall (2).
8. fuel-air blender according to claim 1, it is characterized in that, described swirl-flow devices (3) comprises the swirl vane (11) that centrally body (1) circumference is arranged, described swirl vane (11) is provided with teasehole (12), described centerbody (1) is provided with the fuel channel (13) be communicated with teasehole (12).
9. a gas turbine, is characterized in that, comprises the fuel-air blender according to any one of claim 1-8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410843175.9A CN104566474B (en) | 2014-12-30 | 2014-12-30 | A kind of fuel-air mixer and gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410843175.9A CN104566474B (en) | 2014-12-30 | 2014-12-30 | A kind of fuel-air mixer and gas turbine |
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| Publication Number | Publication Date |
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| CN104566474A true CN104566474A (en) | 2015-04-29 |
| CN104566474B CN104566474B (en) | 2018-02-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410843175.9A Active CN104566474B (en) | 2014-12-30 | 2014-12-30 | A kind of fuel-air mixer and gas turbine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520748A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Opposite-impact preheating combustion chamber |
| CN115523511A (en) * | 2022-09-02 | 2022-12-27 | 哈尔滨工程大学 | Hydrogen fuel high-efficiency stable low-emission combustion chamber based on opposed diffusion flame |
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| JPH11101435A (en) * | 1997-09-29 | 1999-04-13 | Hitachi Ltd | Gas turbine combustor |
| CN1704574A (en) * | 2004-06-03 | 2005-12-07 | 通用电气公司 | Premixing burner with impingement cooled centerbody and method of cooling centerbody |
| CN101644435A (en) * | 2008-08-08 | 2010-02-10 | 通用电气公司 | Lean direct injection diffusion tip and related method |
| CN102679398A (en) * | 2011-01-31 | 2012-09-19 | 通用电气公司 | System for premixing air and fuel in a fuel nozzle |
| CN103822229A (en) * | 2014-02-28 | 2014-05-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low swirl nozzle for combustion chamber of gas turbine |
| US20140366542A1 (en) * | 2006-06-26 | 2014-12-18 | Joseph Michael Teets | Fuel Air Premix Chamber For a Gas Turbine Engine |
| CN204438195U (en) * | 2014-12-30 | 2015-07-01 | 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 fuel-air blender and gas turbine |
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2014
- 2014-12-30 CN CN201410843175.9A patent/CN104566474B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11101435A (en) * | 1997-09-29 | 1999-04-13 | Hitachi Ltd | Gas turbine combustor |
| CN1704574A (en) * | 2004-06-03 | 2005-12-07 | 通用电气公司 | Premixing burner with impingement cooled centerbody and method of cooling centerbody |
| US20140366542A1 (en) * | 2006-06-26 | 2014-12-18 | Joseph Michael Teets | Fuel Air Premix Chamber For a Gas Turbine Engine |
| CN101644435A (en) * | 2008-08-08 | 2010-02-10 | 通用电气公司 | Lean direct injection diffusion tip and related method |
| CN102679398A (en) * | 2011-01-31 | 2012-09-19 | 通用电气公司 | System for premixing air and fuel in a fuel nozzle |
| CN103822229A (en) * | 2014-02-28 | 2014-05-28 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low swirl nozzle for combustion chamber of gas turbine |
| CN204438195U (en) * | 2014-12-30 | 2015-07-01 | 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 fuel-air blender and gas turbine |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520748A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Opposite-impact preheating combustion chamber |
| CN115523511A (en) * | 2022-09-02 | 2022-12-27 | 哈尔滨工程大学 | Hydrogen fuel high-efficiency stable low-emission combustion chamber based on opposed diffusion flame |
| CN115523511B (en) * | 2022-09-02 | 2023-10-13 | 哈尔滨工程大学 | Hydrogen fuel efficient stable low-emission combustion chamber based on opposite-flushing and diffusion flame |
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| CN104566474B (en) | 2018-02-06 |
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Effective date of registration: 20200116 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, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |
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