CN204717745U - A kind of gas turbine pre-mixing nozzle - Google Patents
A kind of gas turbine pre-mixing nozzle Download PDFInfo
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- CN204717745U CN204717745U CN201520173428.6U CN201520173428U CN204717745U CN 204717745 U CN204717745 U CN 204717745U CN 201520173428 U CN201520173428 U CN 201520173428U CN 204717745 U CN204717745 U CN 204717745U
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- centerbody
- fuel passage
- fuel
- gas turbine
- heat exchange
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Abstract
The utility model relates to gas turbine technology field, discloses a kind of gas turbine pre-mixing nozzle, comprises flange, cyclone and centerbody, described centerbody one end is connected with tip plate through described cyclone, the other end and described Flange joint, described flange is provided with fuel inlet, the axial fuel passage be communicated with described fuel inlet is provided with in described centerbody, described cyclone is provided with swirl vane, described swirl vane is provided with the radial fuel passage be communicated with described axial fuel passage, described radial fuel passage is provided with fuel outlet, described centerbody inwall is provided with heat exchange fin, axial fuel passage is divided into the cartridge of inner-layer channel and outer layer channel by the axis be provided with in described axial fuel passage along described centerbody.Axial fuel passage is divided into inner-layer channel and outer layer channel by the utility model.When can reduce tempering, high-temperature fuel gas is for the damage of nozzle head, reduces the temperature difference of air and fuel, raising nozzle life.
Description
Technical field
The utility model relates to gas turbine technology field, and particularly relate to a kind of gas turbine pre-mixing nozzle, particularly one can reduce the temperature difference, and increases the gas turbine pre-mixing nozzle in life-span.
Background technology
Day by day serious along with environmental pollution, the requirement of environmental regulation with perform also more and more stricter.N in air
2with O
2chemically reactive and generate NO
xinitial temperature be about 1650 °, when chamber temperature is higher than 1650 °, just have NO
xproduce.For traditional diffusion combustion combustion chamber, the flame front temperature of diffusion combustion mode always equals the theoretical temperature combustion that stoichiometric ratio is 1, its dense or rare and different not because of fuel and the total Blend proportion of air, although this theoretical temperature combustion is slightly different because fuel element is different, but always higher than 1650 °, the thus NO of conventional diffusion combustion chamber
xdischarge capacity is always very high.Modern dry low NO_x combustor adopts the mode of premixed combustion, effectively can reduce pollutant emission.The general principle of dry low NO_x combustor design is: fuel and air are pre-mixed as homogeneous phase, the flammable mixture that dilutes, and make it burn in the mode of flame propagation, so that flame temperature is controlled below 1650 °, thus reduction NO
xgrowing amount.
Before mixing, fuel is incorporated into hybrid channel from air by different passages.The introducing of fuel and air completes in nozzle.The temperature that the air of high combustion chamber supplied by F level gas turbine is generally about 400 DEG C, and fuel is supplied by auxiliary system, generally between 50 ~ 200 DEG C.The temperature difference between fuel and air can cause the thermal stress that nozzle is higher, especially in geometry change region greatly, and such as, on the blade junction of radial fuel passage and centerbody axial fuel passage.Higher thermal stress can cause the reduction of nozzle life, even causes the major accidents such as fuel leakage.But the supply temperature increasing fuel can increase the construction cost of auxiliary system greatly, and can increase the potential safety hazard in fuel transport process.Thus, how in the significant problem that the situation decline low thermal stress that fuel temperature is lower is the design of gas turbine pre-mixing nozzle.
The danger that of facing in premixed combustion combustion chamber is very large is tempering.Owing to there are some destabilizing factors in combustion process, when flame propagation velocity is greater than the flow velocity of fuel-air mixture, flame can upstream propagate into Fuel-air pre-mixing zone from combustion zone, this can cause nozzle even other structures of head be burned, and then cause gas turbine work to stop.Head of combustion chamber generally can arrange anti-backfire watch-dog, but the high temperature that brings of the tempering often head construction such as defective nozzle in a short period of time.How cooling head, the damage that reduction tempering causes also is a significant problem of gas turbine pre-mixing nozzle design.
In view of the defect of above-mentioned prior art, need to provide one to reduce the temperature difference, and increase the gas turbine pre-mixing nozzle in life-span.
Utility model content
(1) technical problem that will solve
The technical problems to be solved in the utility model is that the premixed combustion combustion chamber of existing gas turbine pre-mixing nozzle is owing to existing destabilizing factor in combustion process, flame can upstream propagate into Fuel-air pre-mixing zone from combustion zone, this can cause nozzle even other structures of head be burned, and then cause gas turbine work to stop.Head of combustion chamber arranges anti-backfire watch-dog, but the problem of the high temperature that brings of the tempering often head construction such as defective nozzle in a short period of time.
(2) technical scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of gas turbine pre-mixing nozzle, comprises flange, cyclone and centerbody, described centerbody one end is connected with tip plate through described cyclone, the other end and described Flange joint, described flange is provided with fuel inlet, the axial fuel passage be communicated with described fuel inlet is provided with in described centerbody, described cyclone is provided with swirl vane, described swirl vane is provided with the radial fuel passage be communicated with described axial fuel passage, described radial fuel passage is provided with fuel outlet, described centerbody inwall is provided with heat exchange fin, axial fuel passage is divided into the cartridge of inner-layer channel and outer layer channel by the axis be provided with in described axial fuel passage along described centerbody.
Wherein, described cartridge one end is connected with described centerbody, and the other end is placed in described axial fuel passage, and described cartridge is connected with the body seal of described centerbody.
Wherein, the link of described cartridge and described centerbody is 5-25mm along the distance of described centerbody axis direction and described radial fuel passage.
Wherein, described cartridge is placed in the distance of one end in described centerbody and described tip plate is 4-10mm.
Wherein, the one end being placed in the described centerbody in described centerbody is arc-shaped.
Wherein, described centerbody two ends inwall is provided with multiple first heat exchange fin, described first heat exchange fin is distributed on described centerbody respectively.
Wherein, the height of described first heat exchange fin is 2 ~ 4mm, and wide is 1 ~ 3mm, and the spacing between adjacent two described first heat exchange fins is 3 ~ 10mm.
Wherein, described flange is provided with air intlet, described tip plate is provided with air outlet slit, be provided with one end in described axial fuel passage and be communicated with described air intlet, the air hose that the other end is communicated with described air outlet slit.
Wherein, described air hose outer wall is provided with the second heat exchange fin.
Wherein, the height of described second heat exchange fin is 2 ~ 4mm, and wide is 1 ~ 3mm, and the spacing between adjacent two described second heat exchange fins is 3 ~ 10mm.
(3) beneficial effect
Technique scheme tool of the present utility model has the following advantages: the centerbody one end in the gas turbine pre-mixing nozzle that the utility model provides is connected with tip plate through cyclone, the other end and Flange joint, flange is provided with fuel inlet, the axial fuel passage be communicated with fuel inlet is provided with in centerbody, cyclone is provided with swirl vane, swirl vane is provided with the radial fuel passage be communicated with axial fuel passage, radial fuel passage is provided with fuel outlet, centerbody inwall is provided with heat exchange fin, axial fuel passage is divided into the cartridge of inner-layer channel and outer layer channel by the axis being provided with centrally body in axial fuel passage.By introducing cartridge in the gas turbine pre-mixing nozzle that the utility model provides, axial fuel passage is divided into inner-layer channel and outer layer channel.Fuel flow to nozzle tip by inner-layer channel and cools it, and when can reduce tempering, high-temperature fuel gas is for the damage of nozzle head.Outer casing inner wall face is arranged the first heat exchange fin, the heating of air to fuel can be strengthened, reduce the temperature difference of air and fuel, thus reduce the thermal stress of cyclone and centerbody and cyclone junction, improve nozzle life.
Accompanying drawing explanation
Fig. 1 is the Facad structure schematic diagram of the utility model embodiment gas turbine pre-mixing nozzle;
Fig. 2 is the close-up schematic view of the utility model embodiment gas turbine pre-mixing nozzle.
In figure: 1: flange; 2: cyclone; 3: centerbody; 11: fuel inlet; 12: air intlet; 21: swirl vane; 22: radial fuel passage; 23: fuel outlet; 30: shell; 31: axial fuel passage; 32: the first heat exchange fins; 341: the second heat exchange fins; 33: cartridge; 311: inner-layer channel; 312: outer layer channel; 34: air hose; 35: air duct; 351: air outlet slit; 36: tip plate; 30: shell.
Detailed description of the invention
In description of the present utility model, except as otherwise noted, the implication of " multiple " is two or more; Orientation or the position relationship of the instruction such as term "left", "right", " interior ", " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of the machine of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.
In description of the present utility model, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and 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 the concrete meaning of above-mentioned term in the utility model can be understood.
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
As shown in Figures 1 and 2, the gas turbine pre-mixing nozzle that the utility model embodiment provides comprises flange 1, cyclone 2 and centerbody 3, described centerbody 3 one end is connected with tip plate 36 through described cyclone 2, the other end is connected with described flange 1, described flange 1 is provided with fuel inlet 11, the axial fuel passage 31 be communicated with described fuel inlet 11 is provided with in described centerbody 3, described cyclone 2 is provided with swirl vane 21, described swirl vane 21 is provided with the radial fuel passage 22 be communicated with described axial fuel passage 31, described radial fuel passage 22 is provided with fuel outlet 23, described centerbody 3 inwall is provided with heat exchange fin 32, axial fuel passage 31 is divided into the cartridge 33 of inner-layer channel 311 and outer layer channel 312 by the axis be provided with in described axial fuel passage 31 along described centerbody 3.
Mist is at nozzle fired downstream under normal circumstances.But owing to there are some destabilizing factors in combustion process, when flame propagation velocity is greater than the flow velocity of fuel-air mixture, flame upstream can be propagated from combustion zone.High-temperature fuel gas is the principal element causing nozzle to burn.The utility model is cooled nozzle tip by the fuel of low temperature, thus can reduce the nozzle burnout failure that tempering causes.
For the pre-mixing nozzle that fuel sprays from cyclone 2 blade, cyclone 2 and centerbody 3 are heavily stressed severely afflicated areas with cyclone 2 junction.This is because the change of these region geometry structures greatly, it is again the place of high temperature air and low temp fuel process simultaneously.The geometry of nozzle is very little with the pneumatic improvable space of design owing to burning, so the temperature difference reducing air and fuel reduces the optimal selection of these region high thermal stress.But the supply temperature of fuel limits by the ability to work of auxiliary system.When fuel supply temperature raises, fuel system needs extra thermal source, and heat dissipation is large in supply process.The combustion gas of high temperature occurs leaking in transportation, and burning, the possibility of the accidents such as blast is also larger.The utility model is by outside outer layer channel 312, namely shell 30 internal face arranges the first heat exchange fin 32, the heating of air to fuel can be strengthened, reduce the temperature difference of air and fuel, thus reduce the thermal stress of cyclone 2 and centerbody 3 and cyclone 2 junction, improve nozzle life.The utility model at utmost can reduce the supply temperature of fuel, thus greatly reduces economic loss that auxiliary system heating fuel brings and potential safety hazard.
Axial fuel passage 31, by introducing cartridge 33, is divided into inner-layer channel 311 and outer layer channel 312 by the gas turbine pre-mixing nozzle that the utility model provides.Fuel flow to nozzle tip 36 by inner-layer channel 311 and cools it, and when can reduce tempering, high-temperature fuel gas is for the damage of nozzle head.Then fuel flow to the radial fuel passage 22 be positioned on cyclone 2 again by outer layer channel 312, sprays at fuel outlet 23.By outside outer layer channel 312, namely shell 30 internal face arranges the first heat exchange fin 32, the heating of air to fuel can be strengthened, reduce the temperature difference of air and fuel, thus reduce the thermal stress of cyclone 2 and centerbody 3 and cyclone 2 junction, improve nozzle life.For the nozzle arranging air duct in nozzle center, also the second heat exchange fin 341 can be set at air hose outer wall, strengthen the heating to fuel further.
In order to ensure that fuel can flow into radial fuel passage 22 from outer layer channel 312 swimmingly, preferably, cartridge 33 front end is positioned at radial fuel passage 22 upstream, and the link of described cartridge 33 and described centerbody 3 is 5-25mm along the distance of described centerbody 3 axis direction and described radial fuel passage 22.Described cartridge 33 one end is connected with described centerbody 3, and the other end is placed in described axial fuel passage 31, and described cartridge 33 is tightly connected with the shell 30 of described centerbody 3.
In the present embodiment, the distance that described cartridge 33 is placed in one end in described centerbody 3 and described tip plate 36 is 4-10mm.The one end being placed in the described centerbody 3 in described centerbody 3 is arc-shaped.
Described centerbody 3 two ends inwall is provided with multiple first heat exchange fin 32, and described first heat exchange fin 32 is distributed on described centerbody 3 respectively.Shell 30 end segment internal face arranges the heat trnasfer that the first heat exchange fin 32 can be strengthened between low temp fuel and high temperature air, but the flowing of the first heat exchange fin 32 pairs of fuel has certain interference, in order to ensure that fuel is to enter into radial fuel passage 22 be stable and non-turbulent, preferably, first heat exchange fin 32 originates in shell 30 end, ends at shell 30 end upstream 50-150mm.
Described in the present embodiment, the height of the first heat exchange fin 32 is 2 ~ 4mm, and wide is 1 ~ 3mm, and the spacing between adjacent two described first heat exchange fins 32 is 3 ~ 10mm.
In order to flame under preventing normal running conditions adheres on nozzle tip end plate 36, described flange 1 is provided with air intlet 12, described tip plate 36 is provided with air outlet slit 351, be provided with one end in described axial fuel passage 31 to be communicated with described air intlet 12, the air hose 34 that the other end is communicated with described air outlet slit 351.Carry out air and flow through air duct 35 by air intlet 12, spray from air outlet slit 322, thus tip plate 36 is blown clearly.In order to strengthen the heating to fuel further, also the second heat exchange fin 341 can be provided with in air hose 34 outside wall surface.Second heat exchange fin 341 originates in shell 30 initiating terminal, ends at cartridge 33 front end face.Preferably, the high 2 ~ 4mm of the second heat exchange fin 341, wide 1 ~ 3mm, the spacing between two fins is 3 ~ 10mm.
Fig. 2 is the utility model nozzle tip section partial enlarged drawing.In the unsettled centering body 3 of cartridge 33 end.Captured area due to fuel channel design is the gross area of fuel outlet 23, and the area at inner-layer channel 311 and outer layer channel 312 turning must be greater than the gross area of fuel outlet 23.Preferably, be 4-10mm with the distance of tip plate 36.In order to ensure the patency of air current flow and reduce the pressure loss, preferably, cartridge 33 end is blunt body.The size and shape of the second heat exchange fin 341 is jointly determined by the width of radiating efficiency and outer layer channel 312.
When in the present embodiment, gas turbine pre-mixing nozzle uses, from the gaseous fuel of fuel inlet 11 on flange 1, flow to nozzle tip by inner-layer channel 311 and it is cooled, then fuel flow to the radial fuel passage 22 be positioned on cyclone 2 again by outer layer channel 312, spray at fuel outlet 23, be mixed into combustion chambers burn with the air coming from cyclone 2 upstream.
In sum, the utility model has the following advantages: the centerbody one end in the gas turbine pre-mixing nozzle that the utility model provides is connected with tip plate through cyclone, the other end and Flange joint, flange is provided with fuel inlet, the axial fuel passage be communicated with fuel inlet is provided with in centerbody, cyclone is provided with swirl vane, swirl vane is provided with the radial fuel passage be communicated with axial fuel passage, radial fuel passage is provided with fuel outlet, centerbody inwall is provided with heat exchange fin, axial fuel passage is divided into the cartridge of inner-layer channel and outer layer channel by the axis being provided with centrally body in axial fuel passage.By introducing cartridge in the gas turbine pre-mixing nozzle that the utility model provides, axial fuel passage is divided into inner-layer channel and outer layer channel.Fuel flow to nozzle tip by inner-layer channel and cools it, and when can reduce tempering, high-temperature fuel gas is for the damage of nozzle head.Outer casing inner wall face is arranged the first heat exchange fin, the heating of air to fuel can be strengthened, reduce the temperature difference of air and fuel, thus reduce the thermal stress of cyclone and centerbody and cyclone junction, improve nozzle life.
Also the second heat exchange fin can be set at air hose outer wall in the gas turbine pre-mixing nozzle that the utility model provides, strengthen the heating to fuel further.
Above embodiment only in order to the technical solution of the utility model to be described, is 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 (10)
1. a gas turbine pre-mixing nozzle, is characterized in that: comprise flange (1), cyclone (2) and centerbody (3), described centerbody (3) one end is connected with tip plate (36) through described cyclone (2), the other end is connected with described flange (1), described flange (1) is provided with fuel inlet (11), the axial fuel passage (31) be communicated with described fuel inlet (11) is provided with in described centerbody (3), described cyclone (2) is provided with swirl vane (21), described swirl vane (21) is provided with the radial fuel passage (22) be communicated with described axial fuel passage (31), described radial fuel passage (22) is provided with fuel outlet (23), described centerbody (3) inwall is provided with the first heat exchange fin (32), axial fuel passage (31) is divided into the cartridge (33) of inner-layer channel (311) and outer layer channel (312) by the axis be provided with in described axial fuel passage (31) along described centerbody (3).
2. gas turbine pre-mixing nozzle according to claim 1, it is characterized in that: described cartridge (33) one end is connected with described centerbody (3), the other end is placed in described axial fuel passage (31), and described cartridge (33) is tightly connected with the shell (30) of described centerbody (3).
3. gas turbine pre-mixing nozzle according to claim 1, is characterized in that: the link of described cartridge (33) and described centerbody (3) is 5-25mm along the distance of described centerbody (3) axis direction and described radial fuel passage (22).
4. gas turbine pre-mixing nozzle according to claim 1, is characterized in that: the distance that described cartridge (33) is placed in one end in described centerbody (3) and described tip plate (36) is 4-10mm.
5. gas turbine pre-mixing nozzle according to claim 1, is characterized in that: the one end being placed in the described centerbody (3) in described centerbody (3) is arc-shaped.
6. gas turbine pre-mixing nozzle according to claim 1, it is characterized in that: described centerbody (3) two ends inwall is provided with multiple first heat exchange fin (32), described first heat exchange fin (32) is distributed on described centerbody (3) respectively.
7. gas turbine pre-mixing nozzle according to claim 6, it is characterized in that: the height of described first heat exchange fin (32) is 2 ~ 4mm, wide is 1 ~ 3mm, and the spacing between adjacent two described first heat exchange fins (32) is 3 ~ 10mm.
8. gas turbine pre-mixing nozzle according to claim 1, it is characterized in that: described flange (1) is provided with air intlet (12), described tip plate (36) is provided with air outlet slit (351), be provided with one end in described axial fuel passage (31) to be communicated with described air intlet (12), the air hose (34) that the other end is communicated with described air outlet slit (351).
9. gas turbine pre-mixing nozzle according to claim 8, is characterized in that: described air hose (34) outer wall is provided with the second heat exchange fin (341).
10. gas turbine pre-mixing nozzle according to claim 9, it is characterized in that: the height of described second heat exchange fin (341) is 2 ~ 4mm, wide is 1 ~ 3mm, and the spacing between adjacent two described second heat exchange fins (341) is 3 ~ 10mm.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520173428.6U CN204717745U (en) | 2015-03-25 | 2015-03-25 | A kind of gas turbine pre-mixing nozzle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520173428.6U CN204717745U (en) | 2015-03-25 | 2015-03-25 | A kind of gas turbine pre-mixing nozzle |
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| CN204717745U true CN204717745U (en) | 2015-10-21 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018134058A1 (en) * | 2017-01-17 | 2018-07-26 | Siemens Aktiengesellschaft | Burner tip having an air channel structure and a fuel channel structure for a burner, and method for producing said burner tip |
| CN112460633A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing method for combustion chamber of gas turbine |
-
2015
- 2015-03-25 CN CN201520173428.6U patent/CN204717745U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018134058A1 (en) * | 2017-01-17 | 2018-07-26 | Siemens Aktiengesellschaft | Burner tip having an air channel structure and a fuel channel structure for a burner, and method for producing said burner tip |
| CN110177976A (en) * | 2017-01-17 | 2019-08-27 | 西门子股份公司 | Burner nozzle with air duct structure and fuel channel structures for burner and the method for manufacturing the burner nozzle |
| JP2020506356A (en) * | 2017-01-17 | 2020-02-27 | シーメンス アクティエンゲゼルシャフト | Burner chip having air flow path structure and fuel flow path structure for burner and method for manufacturing the burner chip |
| CN112460633A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing method for combustion chamber of 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 |
Denomination of utility model: Gas turbine is mixing nozzle in advance Effective date of registration: 20161104 Granted publication date: 20151021 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: 20151021 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 |