CN204438191U - The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use - Google Patents
The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use Download PDFInfo
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- CN204438191U CN204438191U CN201420815777.9U CN201420815777U CN204438191U CN 204438191 U CN204438191 U CN 204438191U CN 201420815777 U CN201420815777 U CN 201420815777U CN 204438191 U CN204438191 U CN 204438191U
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- swirl vane
- leading portion
- cyclone
- back segment
- nozzle
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Abstract
The utility model relates to gas turbine design technical field, particularly relates to the gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use.Wherein, cyclone comprises interior pipe, outer tube and swirl vane, described swirl vane comprises swirl vane leading portion and swirl vane back segment, and described swirl vane leading portion is fixedly connected with described outer tube with described interior pipe, and described swirl vane back segment is connected with described swirl vane leading portion is dismountable.The cyclone that this practicality newly provides, swirl vane on it is made up of swirl vane leading portion and swirl vane back segment, and swirl vane leading portion is fixedly connected with interior pipe, outer tube, swirl vane back segment and swirl vane removably connect, when regulating the eddy flow angle of nozzle, only needing the swirl vane back segment changing different angles, the rapid adjustment of nozzle eddy flow angular dimension can be completed, shorten the manufacturing cycle of gas-turbine combustion chamber nozzle, save the manufacturing cost of nozzle.
Description
Technical field
The utility model relates to gas turbine design technical field, particularly relates to the gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use.
Background technology
At present, the thermal efficiency of gas turbine improves in gas turbine manufacturer by promoting combustor exit temperature, and meanwhile, its product need meet day by day harsh pollutant emission requirement.Usual the produced major air disposal of pollutants of gas turbine adopting conventional carbon hydrocarbon fuel is nitrogen oxide, carbon monoxide and unburned hydrocarbon.As everyone knows, the maximum gas temperature of combustion chamber reaction zone is depended in the generation of nitrogen oxide to a great extent.The method of existing reduction combustion chamber reaction zone temperature is before fuel enters combustion zone, fuel and air is carried out premixed and forms lean mixture.In poor lean premixed combustor reaction zone, the thermal mass of additional air can reduce the peak temperature in reaction zone, to reduce the generation of nitrogen oxide.
In the combustion chamber burner design of premixed combustion, a very important parameter is the eddy flow angle of nozzle cyclone.Higher cyclone angle can produce larger recirculating zone.Recirculating zone contributes to igniting and flame propagation.But on the other hand, the Strong shear that strong eddy flow produces and high turbulence, can make flame front broken, flame quenching, thus cause the problem of shaking of burning.Therefore, in order to find suitable eddy flow angle, often need to carry out a lot of trials and adjustment to cyclone angle in designs of nozzles process.
Fig. 1 is the cyclone 1 ' assembly for premixed fuel nozzle adopting prior art.This cyclone 1 ' assembly is made up of the interior pipe 11 ' with center fuel passage 111 ', the swirl vane 13 ' with branch road fuel channel 1311 ' and fuel orifice 1312 ' and outer tube 12 '; Fuel is by center fuel passage 111 ' in centerbody, enter the branch road fuel channel 1311 ' in swirl vane 13 ' respectively, and from fuel orifice spray 1312 ' injection, the fuel of ejection mixes and produces eddy current together with the air from cyclone 1 ' upstream in cyclone 1 ', and the size of eddy current depends on the eddy flow angle of swirl vane 13 '; Adopt prior art premixed fuel nozzle cyclone 1 ' in, exist many to processing and debug relevant problem.In premixed fuel designs of nozzles, need to carry out flow test to nozzle, by iteration debugging, Flow in Nozzle performance is optimized, in iteration debugging, need to regulate the eddy flow angle of swirl vane 13 ', because the premixed fuel nozzle cyclone 1 ' adopting prior art is overall structure, adjusting eddy flow angle each time all needs to change whole cyclone 1 ', on the one hand, integral replacing brings larger manufacturing cost.On the other hand, the time cycle made in one piece is very long, and owing to there are some uncertain problems in nozzle debug process, the process-cycle can have a strong impact on the progress of designs of nozzles and test.
Therefore, for above deficiency, need to provide a kind of debugging cyclone for gas-turbine combustion chamber nozzle easily and fast.
Utility model content
(1) technical problem that will solve
The technical problems to be solved in the utility model is: traditional cyclone is monolithic construction, when carrying out eddy flow angle to nozzle and reconciling, adjust eddy flow angle each time all to need to change whole cyclone, debug very inconvenient, affect manufacturing cycle and the manufacturing cost of nozzle.
(2) technical scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of cyclone, comprise interior pipe, outer tube and swirl vane, described swirl vane comprises swirl vane leading portion and swirl vane back segment, described swirl vane leading portion is between described interior pipe and described outer tube, and be fixedly connected with described outer tube with described interior pipe, described swirl vane back segment is connected with described swirl vane leading portion is dismountable.
Wherein, be provided with center fuel passage in described interior pipe, described swirl vane leading portion is provided with branch road fuel channel and fuel orifice, described center fuel passage is connected with described fuel orifice by described branch road fuel channel.
Wherein, described swirl vane leading portion is provided with mounting groove, described swirl vane back segment is provided with fitting projection, and described mounting groove matches with described fitting projection.
Wherein, described swirl vane leading portion is provided with fitting projection, described swirl vane back segment is provided with mounting groove, and described mounting groove matches with described fitting projection.
Wherein, brazing is passed through between described swirl vane leading portion and described swirl vane back segment.
Wherein, the eddy flow angle of described swirl vane leading portion is 0 degree, and the eddy flow angle of described swirl vane back segment is 10-45 degree.
Wherein, described swirl vane leading portion accounts for the 10%-50% of whole swirl vane length.
Wherein, interior pipe, described outer tube and described swirl vane leading portion integrally casting is stated shaping.
The utility model additionally provides a kind of gas-turbine combustion chamber nozzle, includes the cyclone described in above-mentioned any embodiment
(3) beneficial effect
Technique scheme tool of the present utility model has the following advantages: the utility model provides a kind of cyclone, comprise interior pipe, outer tube and swirl vane, described swirl vane comprises swirl vane leading portion and swirl vane back segment, described swirl vane leading portion is fixedly connected with described outer tube with described interior pipe, and described swirl vane back segment is connected with described swirl vane leading portion is dismountable.The cyclone that this practicality newly provides, swirl vane on it is made up of swirl vane leading portion and swirl vane back segment, and swirl vane leading portion is fixedly connected with interior pipe, outer tube, swirl vane back segment and swirl vane removably connect, when regulating the eddy flow angle of nozzle, only needing the swirl vane back segment changing different angles, the rapid adjustment of nozzle eddy flow angular dimension can be completed, shorten the manufacturing cycle of gas-turbine combustion chamber nozzle, save the manufacturing cost of nozzle.
Accompanying drawing explanation
The advantage of the above-mentioned and/or additional aspect of the utility model will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1 is the sectional structure schematic diagram of cyclone in prior art;
Fig. 2 is the sectional structure schematic diagram of the cyclone described in the utility model embodiment;
Fig. 3 is the sectional structure schematic diagram of the gas-turbine combustion chamber nozzle of the cyclone that the utility model provides;
Fig. 4 is the stereogram of the cyclone back segment in Fig. 2.
Corresponding relation wherein in Fig. 1 to Fig. 4 between Reference numeral and component names is:
1 ', cyclone, 11 ', interior pipe, 111 ', center fuel passage, 12 ', outer tube, 13 ', swirl vane, 1311 ', branch road fuel channel, 1312 ', fuel orifice, 1, cyclone, 11, interior pipe, 111, center fuel passage, 12, outer tube, 13, swirl vane, 131, swirl vane leading portion, 1311, branch road fuel channel, 1312, fuel orifice, 1313, mounting groove, 132, swirl vane back segment, 1321, fitting projection, 2, nozzle, 21, nozzle mounting flange, 22, cartridge, 23, centerbody.
Detailed description of the invention
For making the object of the utility model embodiment, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, technical scheme in the utility model embodiment is clearly and completely described, obviously, described embodiment is a part of embodiment of the present utility model, instead of whole embodiments.Based on the embodiment in the utility model, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite not making creative work, all belongs to the scope of the utility model protection.
As shown in Figure 2, the utility model provides a kind of cyclone 1, comprise interior pipe 11, outer tube 12 and swirl vane 13, described swirl vane 13 comprises swirl vane back segment 132 and swirl vane back segment 132, center fuel passage 111 is provided with in described interior pipe 11, described swirl vane leading portion 131 is provided with branch road fuel channel 1311 fuel orifice 1312, described swirl vane back segment 132 does not arrange any fuel channel, described center fuel passage 111 is connected with described fuel orifice 1312 by described branch road fuel channel 1311, thus form complete fuel channel, described swirl vane leading portion 131 is fixedly connected with described outer tube 12 with described interior pipe 11, described swirl vane back segment 132 is connected with described swirl vane leading portion 131 is dismountable, like this when regulating the eddy flow angle of nozzle 2, only need the swirl vane back segment 132 changing different angles, the rapid adjustment of nozzle 2 eddy flow angular dimension can be completed, shorten the manufacturing cycle of gas-turbine combustion chamber nozzle 2, save the manufacturing cost of nozzle 2, simultaneously due to described swirl vane back segment 132 not arranging any fuel channel, English is female in dismounting, the risk of any leakage is there is not during replacing.Simultaneously, swirl vane back segment 132 is set to independently assembly, can process than easier in cast-in-block cyclone 1 blade when small lot batch manufacture, in the process tested or run, the swirl vane back segment 132 with different eddy flow angle can be replaced as required, instead of change whole fuel nozzle 2, the object of the manufacturing cycle reducing costs and shorten fuel nozzle 2 can be reached.
Preferably, as shown in Figure 2 and Figure 4, described swirl vane leading portion 131 is provided with mounting groove 1313, described swirl vane back segment 132 is provided with fitting projection 1321, described mounting groove 1313 matches with described fitting projection 1321, the location to swirl vane back segment 132 can be realized fast by the cooperation of mounting groove 1313 and fitting projection 1321, conveniently to install; Solder is put in the position of matching with described fitting projection 1321 at described mounting groove 1313, then heats, and makes swirl vane leading portion 131 and swirl vane back segment 132 pass through brazing; The solder fusing point used due to soldering is lower, can dismantle swirl vane back segment 132 easily by the method for heating, thus can the swirl vane back segment 132 of the different eddy flow angle of quick-replaceable; In order to reach the eddy flow effect of expection and reduce the pressure loss as far as possible, the profile of swirl vane 13 very irregular often.
Certainly; also can be that mounting groove 1313 is set on swirl vane back segment 132 in the above-described embodiments; swirl vane leading portion 131 arranges fitting projection 1321; also the object of the application can be realized; its aim does not depart from design philosophy of the present utility model, should belong to protection domain of the present utility model.
It should be noted that, other connected mode also can be adopted to realize the removably connecting, as the connected modes such as clamping also can realize the object of the application of swirl vane back segment 132 and swirl vane leading portion 131.
In order to ensure different eddy flow angle swirl vane back segment 132 between interchangeability, swirl vane leading portion 131 eddy flow angle is 0 °, and like this, when changing swirl vane back segment 132, the interface of itself and miscellaneous part can not change.
Preferably, the stability of poor premixed combustion when the eddy flow angle of swirl vane back segment 132 is 10 ~ 45 degree is better, and the concrete eddy flow angle of swirl vane back segment needs to determine according to the characteristic of combustion chamber.
Show through experiment, when swirl vane leading portion 131 accounts for 10% ~ 50% of whole cyclone 1 length of blade, the aeroperformance of swirl vane 13 is better.
As shown in Figure 3, the utility model additionally provides a kind of gas-turbine combustion chamber nozzle 2, and this nozzle 2 comprises nozzle mounting flange 21, cartridge 22 centerbody 23 and the cyclone 1 described in above-mentioned any embodiment.Fuel is entered by nozzle mounting flange 21, flow through the center fuel passage 111 inside the fuel channel in cartridge 22, cyclone 1, fuel orifice 1312 is arrived with the branch road fuel channel 1311 on swirl vane 13, mix with the air from cyclone 1 upstream after ejection, form Fuel-air pre-mixed gas.Fuel-air pre-mixed gas burns in the burner inner liner in nozzle 2 downstream.In the process that nozzle 2 designs, the size of eddy flow angle is the important indicator determining combustion stability, can be stably in order to ensure burning, carry out fully, often need the eddy flow angle repeatedly adjusting nozzle 2 cyclone 1, when debugging nozzle 2 eddy flow angle, only need the swirl vane back segment 132 changing different eddy flow angle, operate very simple and convenient, simultaneously owing to not needing to change whole cyclone 1, the manufacturing cost of nozzle 2 can be saved, and the manufacturing cycle of nozzle 2 can be shortened.
In sum, the utility model provides a kind of cyclone, comprise interior pipe, outer tube and swirl vane, described swirl vane comprises swirl vane leading portion and swirl vane back segment, center fuel passage is provided with in described interior pipe, described swirl vane leading portion is provided with branch road fuel channel fuel orifice, described swirl vane back segment does not arrange any fuel channel, described center fuel passage is connected with described fuel orifice by described branch road fuel channel, thus forms complete fuel channel; Described swirl vane leading portion is fixedly connected with described outer tube with described interior pipe, described swirl vane back segment is connected with described swirl vane leading portion is dismountable, like this when regulating the eddy flow angle of nozzle, only need the swirl vane back segment changing different angles, the rapid adjustment of nozzle eddy flow angular dimension can be completed, shorten the manufacturing cycle of gas-turbine combustion chamber nozzle, save the manufacturing cost of nozzle.
Last it is noted that above embodiment is only in order to illustrate the technical solution of the utility model, be not intended to limit; Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (9)
1. a cyclone, comprise interior pipe (11), outer tube (12) and swirl vane (13), it is characterized in that: described swirl vane (13) comprises swirl vane leading portion (131) and swirl vane back segment (132), described swirl vane leading portion (131) is positioned between described pipe (11) and described outer tube (12), and be fixedly connected with described outer tube (12) with described interior pipe (11), described swirl vane back segment (132) is connected with described swirl vane leading portion (131) is dismountable.
2. cyclone according to claim 1, it is characterized in that: in described interior pipe (11), be provided with center fuel passage (111), described swirl vane leading portion (131) is provided with branch road fuel channel (1311) and fuel orifice (1312), described center fuel passage (111) is connected with described fuel orifice (1312) by described branch road fuel channel (1311).
3. cyclone according to claim 1, it is characterized in that: described swirl vane leading portion (131) is provided with mounting groove (1313), described swirl vane back segment (132) is provided with fitting projection (1321), and described mounting groove (1313) matches with described fitting projection (1321).
4. cyclone according to claim 1, it is characterized in that: described swirl vane leading portion (131) is provided with fitting projection (1321), described swirl vane back segment (132) is provided with mounting groove (1313), and described mounting groove (1313) matches with described fitting projection (1321).
5. the cyclone according to claim 3 or 4, is characterized in that: pass through brazing between described swirl vane leading portion (131) and described swirl vane back segment (132).
6. cyclone according to claim 1, is characterized in that: the eddy flow angle of described swirl vane leading portion (131) is 0 degree, and the eddy flow angle of described swirl vane back segment (132) is 10-45 degree.
7. cyclone according to claim 1, is characterized in that: described swirl vane leading portion (131) accounts for the 10%-50% of whole swirl vane (13) length.
8. cyclone according to claim 1, is characterized in that: described interior pipe (11), described outer tube (12) and described swirl vane leading portion (131) integrally casting are shaping.
9. a gas-turbine combustion chamber nozzle, is characterized in that: include the cyclone according to any one of claim 1-8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815777.9U CN204438191U (en) | 2014-12-19 | 2014-12-19 | The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420815777.9U CN204438191U (en) | 2014-12-19 | 2014-12-19 | The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use |
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| Publication Number | Publication Date |
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| CN204438191U true CN204438191U (en) | 2015-07-01 |
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| CN201420815777.9U Active CN204438191U (en) | 2014-12-19 | 2014-12-19 | The gas-turbine combustion chamber nozzle of a kind of cyclone and this cyclone of use |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105180425A (en) * | 2015-10-12 | 2015-12-23 | 叙永县马岭粮油食品有限公司 | Natural gas hot-blast stove adopting flat flame burner |
| CN107091486A (en) * | 2017-04-10 | 2017-08-25 | 西北工业大学 | A kind of after-burner annular flame barrel structure with cyclone |
| CN108800206A (en) * | 2018-06-06 | 2018-11-13 | 西北工业大学 | A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber |
| CN109539310A (en) * | 2018-11-22 | 2019-03-29 | 西北工业大学 | A kind of integrated after-burner using adjustable preheating rectification supporting plate |
-
2014
- 2014-12-19 CN CN201420815777.9U patent/CN204438191U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105180425A (en) * | 2015-10-12 | 2015-12-23 | 叙永县马岭粮油食品有限公司 | Natural gas hot-blast stove adopting flat flame burner |
| CN107091486A (en) * | 2017-04-10 | 2017-08-25 | 西北工业大学 | A kind of after-burner annular flame barrel structure with cyclone |
| CN107091486B (en) * | 2017-04-10 | 2019-08-13 | 西北工业大学 | A kind of after-burner annular flame barrel structure with cyclone |
| CN108800206A (en) * | 2018-06-06 | 2018-11-13 | 西北工业大学 | A kind of poor premix mould nozzle that fuel is sprayed from blade and loopful combustion chamber |
| CN109539310A (en) * | 2018-11-22 | 2019-03-29 | 西北工业大学 | A kind of integrated after-burner using adjustable preheating rectification supporting plate |
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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: Hydrocyclone and gas turbine combustion chamber nozzle using same Effective date of registration: 20161104 Granted publication date: 20150701 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: 20150701 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 | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200102 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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| TR01 | Transfer of patent right |