CN208920103U - The axially staged combustion chamber of gas turbine - Google Patents

The axially staged combustion chamber of gas turbine Download PDF

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Publication number
CN208920103U
CN208920103U CN201821454137.4U CN201821454137U CN208920103U CN 208920103 U CN208920103 U CN 208920103U CN 201821454137 U CN201821454137 U CN 201821454137U CN 208920103 U CN208920103 U CN 208920103U
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level
combustion chamber
nozzle
combustion
fuel
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熊燕
郑祥龙
朱子儒
曾洁玙
肖云汉
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Institute of Engineering Thermophysics of CAS
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Institute of Engineering Thermophysics of CAS
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Abstract

The utility model discloses a kind of axially staged combustion chambers of gas turbine comprising chamber structure component, level-one premixing jet nozzle assembly, level-one nozzle assembly on duty and second level premixing jet nozzle assembly.First-stage firing chamber baffle head and combustion box antetheca constitute head of combustion chamber, and the center of head of combustion chamber is arranged in level-one nozzle assembly on duty;Level-one premixing jet nozzle assembly be arranged in head of combustion chamber using head of combustion chamber center as on the circumference in the center of circle;Second level premixing jet nozzle assembly is located at secondary combustion chamber's baffle head using first-stage firing chamber burner inner liner axis as on the circumference in the center of circle.Axially staged combustion chamber provided by the utility model is injected by the classification of fuel, while guaranteeing efficiency of combustion, fuel is shortened in the residence time of high-temperature region, and realize the soft burning of two-stage, the discharged nitrous oxides of gas-turbine combustion chamber are greatly reduced, and can further improve combustor exit temperature.

Description

The axially staged combustion chamber of gas turbine
Technical field
The utility model relates to technical field of gas turbine more particularly to a kind of axially staged combustion chambers of gas turbine.
Background technique
In order to promote Gas Turbine Power cycle efficieny, and with the development of turbine material and cooling technology, combustion chamber goes out Mouth temperature is in the lowest temperature for having significant raising and the discharge of Step wise approximation thermal NO to sharply increase in recent decades.It is existing Studies have shown that when chamber temperature is more than 1800K, due to the rapid growth of thermal NO, the low NO of conventional combustion roomxDischarge Potentiality will be mined totally, therefore need to explore more advanced Combustion chamber design scheme, to realize higher combustor exit At a temperature of low NOxDischarge.
In addition, the emission performance of conventional gas turbine combustors showed generally under design conditions at full capacity compared with It is good, and under off-design behaviour, CO and NOxDischarge amount often has apparent increase.Therefore combustion chamber is in low- load conditions Combustion stability and emission performance also seem particularly significant.Conventional turbine engines combustion chamber is due to air body at low load Product flow is held essentially constant, the increase for being easy to cause combustion instability and CO to discharge, and if increase fuel nozzle ratio on duty, It will lead to NO againxThe rising of discharge.Therefore, how under the premise of guaranteeing combustion chamber low emissions levels, combustion is improved as much as possible Room outlet temperature is burnt, and widens the load regulation range of combustion chamber, is the key points and difficulties of gas-turbine combustion chamber design.
Utility model content
(1) technical problems to be solved
In view of this, being used for the main purpose of the utility model is to provide a kind of axially staged combustion chamber of gas turbine Realize stabilization of gas-turbine combustion chamber under the conditions of high outlet temperature, wide load range, the discharge of low pollution object.
(2) technical solution
The utility model provides a kind of axially staged combustion chamber of gas turbine, comprising: chamber structure component, level-one are pre- Jet mixing flow nozzle assembly, level-one nozzle assembly on duty and second level premixing jet nozzle assembly, wherein
Chamber structure component includes: secondary combustion chamber's burner inner liner, is fixed on a combustion box inner wall, second level combustion Room baffle head is burnt, secondary combustion chamber's flame tube head, a level-one combustion chamber flame drum, end and secondary combustion chamber are fixed on Baffle head is connected, a level-one head of combustion chamber baffle, is fixed on first-stage firing chamber burner inner liner input end, first-stage firing chamber fire Have several nozzle assemblies on flame cylinder input end, combustion box leading inlet connects compressor exhaust casing, a combustion chamber transition Duan Yiduan connection combustion chamber flame drum outlet end, the other end connect turbine import;
Level-one premixing jet nozzle assembly includes: N number of level-one premixing nozzle through primary fuel distribution ring cavity, and is met N >=3, N number of level-one premixing nozzle circumferentially uniformly across first-stage firing chamber baffle head and are inserted into certain depth H1, full Foot: 2R3≤H1≤R1, wherein R3For each level-one premixing nozzle internal diameter, R1For single-stage combustion area burner inner liner internal diameter;
Level-one nozzle assembly on duty is located at first-stage firing chamber baffle head center, comprising: outside air rotation on duty Flow nozzle and a center fuel nozzle on duty;
Second level premixing jet nozzle assembly includes: K second level premixing nozzle through a secondary fuel ring cavity, and circumferentially It is even to be distributed on secondary combustion chamber's baffle head, meet K >=6, while secondary fuel conduit connects secondary fuel ring cavity, for two The importing of grade fuel.
Further, the nozzle incident direction of each level-one premixing nozzle is axially parallel with combustion chamber.
Further, each level-one premixing nozzle wall surface is provided with two rows of circumferentially distributed teaseholes, the spacing L of two rounds1Depending on Depending on Actual combustion chamber size, every row's teasehole number is P, meets P >=4.
Further, radius of a circle R locating for N number of level-one premixing nozzle2Meet: R1/2≤R2≤5R1/6。
Further, the outside of level-one nozzle assembly on duty air swirl nozzle entrance on duty is equipped with radial swirler, should It is θ that radial swirler structure, which is with M swirl angle,1Eddy flow conduit, meet M >=4,30 °≤θ1≤ 60 °, outside sky on duty It is θ that cyclonic current jet expansion, which is equipped with subtended angle,2Cone cover, meet 30 °≤θ2≤ 45 °, and bore cover height H1Meet: 2R3≤H1≤R1
Further, level-one nozzle assembly on duty selects to install or do not install according to actual needs.
Further, second level premixing nozzle wall surface is provided with two rows of teaseholes.
Further, secondary fuel effluxvelocity is 100m/s-200m/s.
Further, the annular space that secondary combustion zone is surrounded by toroidal combustion chamber, the height H of the annular space2It is full Sufficient 3/2R1≤H2≤8R1
(3) beneficial effect
It can be seen from the above technical proposal that there is following beneficial effect in the axially staged combustion chamber of the gas turbine of the utility model Fruit:
(1) single-stage combustion area realizes soft burning in such a way that high-speed jet volume sucks back stream, so that fuel is burning It is preceding that strong blending occurs with flue gas, the oxygen concentration and peak flame temperature of flame zone are reduced, single-stage combustion is effectively reduced The nitrogen oxide emission in area.
(2) the high-speed jet Involving velocity of secondary combustion zone further increases smoke backflow ratio, meanwhile, secondary fuel It is directly injected into level-one incoming flow flue gas, higher flue-gas temperature can guarantee the igniting of secondary fuel and stablize conflagration. In addition, lower oxygen concentration and shorter residence time are but also the nitrogen oxide emission of secondary combustion zone has obtained effectively Control.
(3) it is injected by the classification of fuel, can both guarantee that level-one was burnt under lower equivalent proportion, so that its nitrogen oxidation Object discharge amount keeps reduced levels;Meanwhile combustor exit temperature, and second level are further improved further through secondary fuel is introduced The combustion atmospheres of combustion zone high-temperature low-oxygen and shorter residence time reduce the discharged nitrous oxides of secondary combustion zone.
(4) since secondary fuel directly burns in high-temperature flue gas, with higher combustion stability and wider equivalent Than the operating condition of range.When gas turbine load changes, combustion chamber heat can be realized by adjusting secondary fuel amount The quick response of load, and the high-temperature flue gas of level-one incoming flow can guarantee the combustion stability of secondary fuel.
(5) when this axially staged combustion chamber is designed with the use of double fuel road, different types of combustion is used by a second level Material can realize that stablizing for the poor fuel of combustion stability is burnt in second level.
Detailed description of the invention
Fig. 1 is the structural schematic diagram according to the axially staged combustion chamber of the utility model embodiment;
Fig. 2 is the left view of axially staged combustion chamber shown in FIG. 1;
Fig. 3 is the working state schematic representation of axially staged combustion chamber shown in FIG. 1;
Fig. 4 is the full structural schematic diagram of axially staged combustion chamber shown in FIG. 1;
Fig. 5 is the flow chart of the axially staged combustion chamber control method of the utility model embodiment.
In figure:
Axially staged combustion chamber 100
110 first-stage firing chamber baffle head 120 of combustion box
121 grades of head of combustion chamber baffles 130 of first-stage firing chamber burner inner liner
131 outside air swirl nozzle 140 on duty of secondary combustion chamber's burner inner liner
150 primary fuel of level-one premixing nozzle distributes ring cavity 151
160 secondary fuel conduit 161 of secondary fuel ring cavity
162 combustion chamber changeover portion 170 of second level premixing nozzle
Tangential swirl angle θ on duty1Bore cover half angle θ2
Bore the height H of cover1Secondary combustion zone ring cavity height H2
Teasehole is away from jet expansion distance L1Level-one burner inner liner radius R1
The enclosed radius of a circle R of level-one premixing nozzle2Level-one premixing nozzle radius R3
Specific embodiment
The utility model sucks back the forms such as stream by I and II high-speed jet volume, and portion forms two-stage height in the combustion chamber Low pressure loss reflux is imitated, the blending of unburning material and flue gas is promoted, so that combustion zone keeps high-temperature low-oxygen atmosphere and formation two-stage is soft And burning.To reduce fuel in the residence time of high-temperature region, discharged nitrous oxides are reduced.Simultaneously as second level is unburned Gas directly burns in high-temperature flue gas, has good combustion stability and burn-up efficiency, wider Load Regulation may be implemented Range.Therefore, the quick of after-flame load may be implemented under the premise of guaranteeing efficiency of combustion and combustion stability in the utility model Response, and extremely low discharged nitrous oxides can be realized in wider load range.
For the purpose of this utility model, technical solution and advantage is more clearly understood, below in conjunction with specific embodiment, and Referring to attached drawing, the utility model is described in further detail.
The utility model provides a kind of axially staged combustion chamber of gas turbine, comprising: chamber structure component, level-one are pre- Jet mixing flow nozzle assembly, level-one nozzle assembly on duty and second level premixing jet nozzle assembly, wherein chamber structure component packet Include: secondary combustion chamber's burner inner liner is fixed on a combustion box inner wall, and secondary combustion chamber's baffle head is fixed on second level Combustion chamber flame drum head, a level-one combustion chamber flame drum, end are connected with secondary combustion chamber's baffle head, a single-stage combustion Room baffle head is fixed on first-stage firing chamber burner inner liner input end, has several sprays on the first-stage firing chamber burner inner liner input end Nozzle assembly, combustion box leading inlet connect compressor exhaust casing, and a combustion chamber changeover portion one end connects combustion chamber flame drum Outlet end, the other end connect turbine import;
Referring to Figure 1 to Fig. 3, the utility model first embodiment provides a kind of axially staged combustion chamber 100, comprising: Chamber structure component and a secondary nozzle component;
In the present embodiment, chamber structure component includes: combustion box 110, first-stage firing chamber baffle head 120, one Grade combustion chamber flame drum 121, secondary combustion chamber's baffle head 130, secondary combustion chamber's burner inner liner 131 and combustion chamber changeover portion 170. Secondary combustion chamber's burner inner liner 131 is fixed on 110 inner wall of combustion box, and secondary combustion chamber's baffle head 130 is fixed on second level combustion 131 head of room burner inner liner is burnt, first-stage firing chamber burner inner liner 121 is connected in end with secondary combustion chamber baffle head 130, and level-one is fired It burns room baffle head 120 and is fixed on 121 input end of first-stage firing chamber burner inner liner, have several nozzle assemblies thereon.Combustion chamber machine 110 leading inlet of casket connects compressor exhaust casing, and changeover portion 170 one end in combustion chamber connects combustion chamber flame drum outlet end, another End connection turbine import.
Wherein, first-stage firing chamber burner inner liner 121 is cylinder type, and first-stage firing chamber baffle head 120 is round plate, Secondary combustion chamber's baffle head 130 is ring plate, and secondary combustion chamber's burner inner liner 131 is ring cavity structure, and above-mentioned component is adopted It is made of high-temperature alloy material, 110 antetheca of combustion box is made of stainless steel, and rest part uses carbon steel material system At.
In some embodiments, level-one nozzle assembly on duty is located at first-stage firing chamber baffle head center, including outside one Side air swirl nozzle on duty and center fuel nozzle on duty;
As shown in Fig. 2, nozzle assembly includes: level-one nozzle assembly on duty, level-one premixing jet nozzle sets in the present embodiment Part and second level premixing jet nozzle assembly.Wherein, outside air swirl nozzle 140 on duty is arranged in first-stage firing chamber baffle head Center, including cone cover, radial swirler, air conduit and fuel conductor.Air enters air through radial swirler and fuel is led The circular passage that pipe is surrounded, fuel contact with rotational flow air through the aperture outflow on fuel conductor head and diffusion combustion occur.
In some embodiments, level-one premixing jet nozzle assembly includes: N number of level-one premixing nozzle through a primary fuel point With ring cavity, and meet N >=3, which circumferentially uniformly across first-stage firing chamber baffle head and is inserted into certain Depth H1, meet: 2R3≤H1≤R1, wherein R3For each level-one premixing nozzle internal diameter, R1For single-stage combustion area burner inner liner internal diameter;
Secondary fuel premixing nozzle component includes: K second level premixing nozzle through a secondary fuel ring cavity, and circumferentially It is even to be distributed on secondary combustion chamber's baffle head, meet K >=6, while secondary fuel conduit connects secondary fuel ring cavity, for two The importing of grade fuel.
In some embodiments, the nozzle incident direction of each level-one premixing nozzle is axially parallel with combustion chamber.
In some embodiments, each level-one premixing nozzle wall surface is provided with two rows of circumferentially distributed teaseholes, the spacing of two rounds L1Depending on Actual combustion chamber size, every row's teasehole number is P, meets P >=4.
In the present embodiment, level-one premixing nozzle 150 passes through first-stage firing chamber baffle head 120 and is inserted into certain depth H1, wherein H1Meet: 2R3≤H1≤R1;Level-one premixing nozzle wall surface is provided with two rows of circumferentially distributed teaseholes, between two rounds Spacing L1Need to be depending on the size of Actual combustion room, every row's teasehole number is P, meets P >=4;Primary fuel distributes ring cavity 151 External primary fuel inlet ducts, fuel enters primary fuel distribution ring cavity 151 through inlet ducts, then vertical by teasehole Jet stream enters level-one premixing nozzle, and it is concurrent with parallel ATA pattern to enter single-stage combustion area after sufficiently premixing with incoming air Raw premixed combustion.Second level premixing nozzle 162 is the premixing nozzle compared with high equivalent weight than under, evenly distributed in the circumferential direction in second level On head of combustion chamber baffle 130, to guarantee that the temperature of secondary combustion zone is uniformly distributed, second level premixing nozzle 162 several K should expire Sufficient K >=6, while second level premixing nozzle 162 enters secondary combustion chamber with sufficiently high parallel jet speed, to suck back stream by volume Realize the abundant blending of secondary fuel and incoming flow high-temperature flue gas.
In some embodiments, radius of a circle R locating for N number of level-one premixing nozzle2Meet: R1/2≤R2≤5R1/6。
In some embodiments, the outside air eddy flow nozzle entrance on duty of level-one nozzle assembly on duty is equipped with radial vortex Device, it is θ which, which is with M swirl angle,1Eddy flow conduit, meet M >=4,30 °≤θ1It is≤60 °, described to be somebody's turn to do It is θ that outside air swirl jet expansion on duty, which is equipped with subtended angle,2Cone cover, meet 30 °≤θ2≤ 45 °, and bore cover height H1Meet: 2R3≤H1≤R1
In some embodiments, level-one nozzle assembly on duty selects to install or do not install according to actual needs.
In some embodiments, second level premixing nozzle wall surface is provided with two rows of teaseholes.
In some embodiments, secondary fuel effluxvelocity is 100m/s-200m/s.
In some embodiments, the annular space that secondary combustion zone is surrounded by toroidal combustion chamber, the height of the annular space H2Meet 3/2R1≤H2≤8R1
As shown in figure 3, the axially staged combustion chamber of the utility model first embodiment, to reduce discharged nitrous oxides, one Grade nozzle assembly on duty only works in ignition phase.When combustion chamber reaches predetermined operating condition, due to 150 high speed of level-one premixing nozzle The Involving velocity of jet stream forms strong interior recirculating zone in single-stage combustion district center position.The premix fuel and cigarette of jet exit The mixture that blending forms high-temperature low-oxygen occurs for gas, reduces flame combustion intensity, so that reaction zone be made to tend to disperse, is formed Level-one soft combustion zone.Meanwhile secondary fuel is emitted directly toward in level-one flue gas incoming flow, oxidizer composition is high-temperature low-oxygen Flue gas, atmosphere needed for can directly forming soft burning;And due to secondary fuel/air high-speed jet induced synthesis Strong interior recirculating zone, further reduced the oxygen concentration of backflow flue gas, to greatly suppress secondary combustion zone nitrogen oxides Formation.On the whole, it is injected, is may be implemented under identical combustor exit temperature by the classification of fuel, reduce single-stage combustion Area's temperature shortens fuel in the residence time of high-temperature region, so that combustion chamber while guaranteeing efficiency of combustion, reduces nitrogen oxides Discharge;And herein on basis, which can also further increase combustion chamber and go out in identical nitric oxide emission levels Mouth temperature, to improve the whole efficiency of thermal cycle of gas turbine.
The utility model second embodiment additionally provides a kind of control method of axially staged combustion chamber of gas turbine, is used for The burning of above-mentioned axially staged combustion chamber is controlled, as shown in Figure 5, comprising:
Step A:
Air enters outside air swirl nozzle 140 on duty and level-one premixing nozzle 150, supplies to center fuel nozzle on duty The range for the fuel quantity answered is the 5%-10% of total fuel quantity.
Step B:
The fuel quantity of the center that feeds fuel nozzle on duty is stepped up to maximum value, then gradually to level-one premixing nozzle 150 feed fuel, when the fuel quantity of level-one premixing nozzle 150 reach can independent stable operation predetermined load when, gradually subtract The fuel of small center fuel nozzle on duty is supplied, until being zero.
Step C:
150 fuel duty of level-one premixing nozzle need to be stepped up, until reaching the peak load in single-stage combustion area, level-one The greatest amount of fuel ratio of combustion zone is the 30%-50% of fuel quantity at full capacity.
Step D:
When primary fuel amount reaches the 50% of fuel quantity at full capacity, secondary fuel supply is opened, and incrementally increase second level Fuel quantity, until combustion chamber reaches oepration at full load.
Step E:
When combustion chamber load deviates rated load, secondary fuel supply should be adjusted first to respond load variations, this When keep primary fuel supply it is constant;When combustion chamber heat load is lower than 50%, secondary fuel supply is closed;If need to further drop Low combustion chamber thermic load needs to adjust primary fuel supply then to respond load variations.
Step F:
Secondary fuel supply should be closed when load reduction is to 50% during flame-out, then reduce the main combustion fuel confession of level-one Combustion engine load reduction should be made to 30%, feed 5% fuel to maintain to stablize burning, then to center fuel nozzle on duty at this time The main combustion fuel supply of level-one is gradually reduced and closed, fuel nozzle supply on duty is finally closed.
Wherein, a secondary fuel supply line, fuel supply conduit on duty are controlled by regulating valve respectively, to a secondary fuel Nozzle and center fuel nozzle on duty supply fuel, and air mass flow can be automatically adjusted with combustion chamber load.
In this embodiment, setting 150 speed of level-one premixing nozzle is 80m/s-160m/s, and primary fuel hole flow velocity is 100m/s-200m/s, outside 140 annular channel outlet speed 60m/s-120m/s of air swirl nozzle on duty;Level-one premix spray It is mixed again with fuel after mouth high speed injection high-temperature flue gas and therewith efficient blending, 1200 DEG C -1600 DEG C of formation temperature, oxygen concentration The non-burning mixt of 5%-10% realizes the soft combustion zone of level-one characterized by high temperature, hypoxemia;Secondary fuel effluxvelocity For 100m/s-200m/s, the second level that higher temperature is formed under the mixed atmosphere of level-one incoming flow flue gas and exteenal reflux flue gas is soft Combustion zone.
It should be noted that in attached drawing or specification text, the implementation for not being painted or describing is affiliated technology Form known to a person of ordinary skill in the art, is not described in detail in field.In addition, the above-mentioned definition to each element and not only limiting The various specific structures mentioned in embodiment, shape, those of ordinary skill in the art simply can be changed or be replaced to it It changes, such as:
(1) swirl nozzle on duty can also be using other constructions, as long as identical function can be completed;
(2) it can provide the demonstration of the parameter comprising particular value herein, but these parameters are worth without definite equal to corresponding, and It is that can be similar to analog value in acceptable error margin or design constraint;
(3) direction term mentioned in embodiment, such as "upper", "lower", "front", "rear", "left", "right" etc. are only ginsengs The direction of attached drawing is examined, is not used to limit the protection scope of the utility model;
(4) above-described embodiment can be based on the considerations of design and reliability, and the collocation that is mixed with each other uses or and other embodiments Mix and match uses, i.e., the technical characteristic in different embodiments can freely form more embodiments.
In conclusion axially staged combustion chamber provided by the utility model, sucks back stream by level-one high-speed jet volume first, Strong interior recirculating zone is formed in single-stage combustion district center position.The premix fuel of jet exit occurs blending with flue gas and forms The mixture of high-temperature low-oxygen reduces flame combustion intensity, so that reaction zone be made to tend to disperse, forms the soft burning of level-one Area.Meanwhile secondary fuel is emitted directly toward in level-one flue gas incoming flow, atmosphere needed for can directly meeting soft burning;And Due to the interior recirculating zone that secondary fuel/air high-speed jet induced synthesis is strong, the oxygen of backflow flue gas further reduced Concentration, to greatly suppress the formation of secondary combustion zone nitrogen oxides.Therefore, it is injected, be may be implemented by the classification of fuel Under identical combustor exit temperature, single-stage combustion area temperature is reduced, shortens fuel in the residence time of high-temperature region, so that combustion chamber While guaranteeing efficiency of combustion, discharged nitrous oxides are reduced;In identical nitric oxide emission levels, which can also be with By increasing secondary fuel amount, combustor exit temperature is further increased, to improve the whole thermodynamic cycle effect of gas turbine Rate.In addition, it is fast to realize that the combustion chamber can also be even switched off secondary fuel supply by reduction under the conditions of running on the lower load Fast, flexible load responding, and keep lower pollutant emission and higher efficiency of combustion and combustion chamber stability.
Particular embodiments described above has carried out into one the purpose of this utility model, technical scheme and beneficial effects Step is described in detail, it should be understood that the foregoing is merely specific embodiment of the utility model, are not limited to this reality With novel, within the spirit and principle of the utility model, any modification, equivalent substitution, improvement and etc. done should all include It is within the protection scope of the utility model.

Claims (9)

1. a kind of axially staged combustion chamber of gas turbine characterized by comprising chamber structure component, level-one premixing jet Nozzle assembly, level-one nozzle assembly on duty and second level premixing jet nozzle assembly, wherein
The chamber structure component includes: secondary combustion chamber's burner inner liner, is fixed on a combustion box inner wall, second level combustion Room baffle head is burnt, secondary combustion chamber's flame tube head, a level-one combustion chamber flame drum, end and described two are fixed on Grade head of combustion chamber baffle is connected, and a level-one head of combustion chamber baffle is fixed on the first-stage firing chamber burner inner liner input end, institute It states on first-stage firing chamber burner inner liner input end with several nozzle assemblies, the combustion box leading inlet connection compressor row Cylinder, a combustion chamber changeover portion one end connect combustion chamber flame drum outlet end, and the other end connects turbine import;
The level-one premixing jet nozzle assembly includes: N number of level-one premixing nozzle through primary fuel distribution ring cavity, and is met N >=3, N number of level-one premixing nozzle circumferentially uniformly across the first-stage firing chamber baffle head and are inserted into certain depth H1, meet: 2R3≤H1≤R1, wherein R3For each level-one premixing nozzle internal diameter, R1For single-stage combustion area burner inner liner internal diameter;
The level-one nozzle assembly on duty is located at first-stage firing chamber baffle head center, comprising: an outside sky on duty Cyclone flow nozzle and a center fuel nozzle on duty;
The second level premixing jet nozzle assembly includes: K second level premixing nozzle through a secondary fuel ring cavity, and circumferentially It is even to be distributed on secondary combustion chamber's baffle head, meet K >=6, while secondary fuel conduit connects secondary fuel ring cavity, For the importing of secondary fuel.
2. the axially staged combustion chamber of gas turbine according to claim 1, which is characterized in that each level-one premixing nozzle Nozzle incident direction it is axially parallel with combustion chamber.
3. the axially staged combustion chamber of gas turbine according to claim 1 or 2, which is characterized in that each level-one premix Nozzle wall surface is provided with two rows of circumferentially distributed teaseholes, the spacing L of two rounds1Depending on Actual combustion chamber size, every row's fuel Hole number is P, meets P >=4.
4. the axially staged combustion chamber of gas turbine according to claim 1, which is characterized in that N number of level-one premix spray Radius of a circle R locating for mouth2Meet: R1/2≤R2≤5R1/6。
5. the axially staged combustion chamber of gas turbine according to claim 1, which is characterized in that the level-one nozzle sets on duty The outside of part air swirl nozzle entrance on duty is equipped with radial swirler, and the radial swirler structure is with M swirl angle For θ1Eddy flow conduit, meet M >=4,30 °≤θ1≤ 60 °, the outside air swirl jet expansion on duty is equipped with subtended angle θ2Cone cover, meet 30 °≤θ2≤ 45 °, and bore cover height H1Meet: 2R3≤H1≤R1
6. the axially staged combustion chamber of gas turbine according to claim 1 or 5, which is characterized in that the level-one spray on duty Nozzle assembly selects to install or do not install according to actual needs.
7. the axially staged combustion chamber of gas turbine according to claim 1, which is characterized in that the second level premixing nozzle wall Face is provided with two rows of teaseholes.
8. the axially staged combustion chamber of gas turbine according to claim 1, which is characterized in that further include: secondary fuel is penetrated Flow velocity degree is 100m/s-200m/s.
9. the axially staged combustion chamber of gas turbine according to claim 1, which is characterized in that secondary combustion zone is annular combustion Burn the annular space that room is surrounded, the height H of the annular space2Meet 3/2R1≤H2≤8R1
CN201821454137.4U 2018-09-05 2018-09-05 The axially staged combustion chamber of gas turbine Active CN208920103U (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110631049A (en) * 2019-10-12 2019-12-31 中国科学院工程热物理研究所 Soft combustion chamber of gas turbine
CN111486453A (en) * 2020-04-16 2020-08-04 中国科学院工程热物理研究所 Heating and rectifying integrated device
CN112066371A (en) * 2020-09-02 2020-12-11 西安交通大学 Hydrogen mixes low NOx burner in advance based on flame on duty
CN113310071A (en) * 2021-06-16 2021-08-27 哈尔滨工程大学 Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110631049A (en) * 2019-10-12 2019-12-31 中国科学院工程热物理研究所 Soft combustion chamber of gas turbine
CN111486453A (en) * 2020-04-16 2020-08-04 中国科学院工程热物理研究所 Heating and rectifying integrated device
CN111486453B (en) * 2020-04-16 2022-02-25 中国科学院工程热物理研究所 Heating and rectifying integrated device
CN112066371A (en) * 2020-09-02 2020-12-11 西安交通大学 Hydrogen mixes low NOx burner in advance based on flame on duty
CN112066371B (en) * 2020-09-02 2021-06-22 西安交通大学 Hydrogen mixes low NOx burner in advance based on flame on duty
CN113310071A (en) * 2021-06-16 2021-08-27 哈尔滨工程大学 Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine

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