CN111473362A - Premixing nozzle of gas turbine combustor - Google Patents
Premixing nozzle of gas turbine combustor Download PDFInfo
- Publication number
- CN111473362A CN111473362A CN202010292812.3A CN202010292812A CN111473362A CN 111473362 A CN111473362 A CN 111473362A CN 202010292812 A CN202010292812 A CN 202010292812A CN 111473362 A CN111473362 A CN 111473362A
- Authority
- CN
- China
- Prior art keywords
- fuel
- nozzle
- lobe
- premixing
- channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention provides a premixing nozzle of a gas turbine combustor, comprising: the fuel nozzle comprises a central lobe type fuel nozzle, an outer side fuel distribution ring cavity and a premixing nozzle channel, wherein the central lobe type fuel nozzle is coaxially arranged at the central position inside the premixing nozzle channel and used for uniformly introducing fuel into the premixing nozzle channel; the central lobe type fuel nozzle comprises a hollow lobe structure formed by adjacent connection of M lobes, wherein M is more than or equal to 3; and the lobe structure is provided with a first fuel hole, the outer fuel distribution ring cavity is arranged between the central lobe type fuel nozzle and the outlet of the premixing nozzle channel, is coaxially arranged on the outer wall of the premixing nozzle channel and is communicated with the premixing nozzle channel, and is used for introducing secondary fuel into the premixing nozzle channel. The fuel/air mixing uniformity of the nozzle outlet can be improved, the combustion stability is improved while the emission of nitrogen oxides in the combustion chamber is reduced, and thermoacoustic oscillation is inhibited.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a premixing nozzle of a gas turbine combustor.
Background
In order to improve the efficiency of the gas turbine, the outlet temperature of the combustion chamber is higher and higher, and the emission of nitrogen oxides under the high-temperature condition is exponentially increased along with the increase of the outlet temperature of the combustion chamber. How to suppress the generation of nitrogen oxides under high temperature conditions is a key and difficult point of the current combustion chamber design. The unit nozzles are important components of the combustion chamber, and the structural design and layout of the unit nozzles play a decisive role in the performance and pollutant emission of the combustion chamber. In order to meet the increasingly stringent pollutant emission standards, it is necessary to perform a series of optimization designs on the unit nozzles, including increasing the blending uniformity, reducing the risk of backfire, etc., reducing NOx emissions and suppressing thermoacoustic oscillations while ensuring combustion efficiency.
The dry type lean premixed combustion technology is the mainstream combustion technology in the field of gas turbines at present. Under the condition of a certain temperature at the outlet of the combustion chamber, dry lean premixed combustion mainly reduces the generation of thermal NOx by reducing the peak temperature of flame, thereby reducing the overall NOx emission. The design of the premixing nozzle has the difficulty that the fuel and the air are rapidly mixed in a limited time and space, and the mixing quality has important influences on the combustion stability and the NOx emission. With the gradual reduction of pollutant emission standards, the nozzle structure of the existing dry lean premixed combustor still needs to be optimally designed to realize the stable, efficient and low-pollution operation of the combustion chamber of the gas turbine.
Disclosure of Invention
Technical problem to be solved
In view of the above, the main objective of the present invention is to provide a premixing nozzle for a gas turbine combustor, which is used to improve the uniformity of fuel/air mixing at the nozzle outlet, improve combustion stability and suppress thermo-acoustic oscillation while reducing the emission of nitrogen oxides in the combustor.
(II) technical scheme
In order to solve the above problems, the present invention provides a premixing nozzle for a gas turbine combustor, comprising: the fuel nozzle comprises a central lobe type fuel nozzle, an outer side fuel distribution ring cavity and a premixing nozzle channel, wherein the central lobe type fuel nozzle is coaxially arranged at the central position inside the premixing nozzle channel and used for uniformly introducing fuel into the premixing nozzle channel; the central lobe type fuel nozzle comprises a hollow lobe structure formed by adjacent connection of M lobes, wherein M is more than or equal to 3; and the lobe structure is provided with a first fuel hole, the outer fuel distribution ring cavity is arranged between the central lobe type fuel nozzle and the outlet of the premixing nozzle channel, is coaxially arranged on the outer wall of the premixing nozzle channel and is communicated with the premixing nozzle channel, and is used for introducing secondary fuel into the premixing nozzle channel.
Optionally, the central lobe fuel nozzle further comprises a hollow annular portion disposed at a front portion of the lobe structure, a central fuel conduit disposed at a front portion of the hollow annular portion for passing fuel; the cavity between the hollow annular part and the outer wall and the inner wall of the lobe structure forms a first channel for fuel to pass through, the tail end of the central fuel guide pipe is provided with P radial branch pipes, P is more than or equal to 3, and the radial branch pipes are communicated with the first channel; and the tail part of the lobe structure is provided with a first fuel hole communicated with the first channel.
Optionally, the first fuel holes are opened on the inner wall and the outer wall of the tail part of the lobe structure, and the first fuel holes are uniformly distributed along the circumferential direction of the lobe structure.
Optionally, the inner diameter D of the hollow annular portion2Satisfies the following conditions: d1/3≤D2≤3/4D1Wherein D is1Is the inner diameter of the premix nozzle passage.
Optionally, the distance L between the radial branch to the hollow annulus and lobe structure junction1Satisfies the following conditions: d2/2≤L1≤2D2Wherein D is2The inner diameter of the hollow annular portion.
Optionally, the lobe structure has an outer edge height H1Satisfies the following conditions: d2/4≤H1≤3/4D2(ii) a Height H of inner edge of the lobe structure2Satisfies the following conditions: d2/4≤H2≤3/4D2(ii) a The number N of the first fuel holes satisfies: n is more than or equal to 4M; wherein D is2The inner diameter of the hollow annular portion.
Optionally, the lobe structure has an outer lobe angle θ of the lobes1Theta is more than or equal to 10 degrees1Less than or equal to 30 degrees; inner lobe angle theta of lobe2Theta is more than or equal to 10 degrees2≤30(iv) DEG; the included angle theta between the lobe side wall and the connecting line of the lobe bottom and the axis3Satisfies the condition that 0.5 pi/M is not more than theta3≤2π/M。
Optionally, the second fuel holes in the outer fuel distribution ring cavity are two rows of holes uniformly distributed, the two rows of holes are distributed along the circumferential direction of the outer wall of the premix nozzle channel, the two rows of holes are staggered, the number K of each row of holes satisfies that K is greater than or equal to 6, and the distance L between the two rows of holes2Satisfies D1/4≤L2≤D1Wherein D is1Is the inner diameter of the premix nozzle passage.
Optionally, a shortest distance L between a second fuel hole in the outer fuel distribution annulus and the premix nozzle passage exit cross-section4Satisfies D1/2≤L4≤2D1。
Optionally, a distance L between an aft cross-section of the lobe structure and the premix nozzle passage outlet3Satisfy 2D1≤L3≤5D1Wherein D is1Is the inner diameter of the premix nozzle passage.
(III) advantageous effects
The invention has at least the following beneficial effects:
(1) when external air flows through the lobe type fuel nozzle provided by the invention, a complex vortex structure (such as a flow direction vortex, an orthogonal vortex, a horseshoe vortex and the like) can be formed at the trailing edge of the lobe, so that the mixing of downstream fuel and air is enhanced, and the fuel/air mixing uniformity at the outlet of the premixing nozzle is improved.
(2) Compared with the traditional swirl premixing nozzle, the premixing nozzle provided by the invention can realize more efficient mixing of fuel and air at the nozzle outlet, and the required premixing section length is shorter. Thereby reducing the peak temperature of the jet flame and inhibiting NOx emission;
(3) compared with the traditional fuel nozzle, the central fuel nozzle of the premixing nozzle adopts a lobe structure, so that the gas flow of an external flow field is smoother, the mixing efficiency is improved, and the pressure loss is reduced;
(4) the second fuel holes in the outer fuel distribution ring cavity are arranged in a double-row staggered manner, so that the mixing uniformity of fuel/air is further improved, and the occurrence of thermoacoustic oscillation is inhibited; meanwhile, under the working condition of low equivalence ratio, the fuel supply proportion of the outer side ring cavity is properly increased, the concentration of the fuel at the outer side of the jet flow can be properly improved, and the combustion stability is increased.
(5) The lobe type fuel nozzle provided by the invention has a compact structure, is flexible to adjust, and can effectively inhibit the formation of a local high-temperature area at the downstream of the nozzle, thereby reducing the emission of nitrogen oxides in a combustion chamber.
Drawings
FIG. 1 is a schematic illustration of a gas turbine combustor premix nozzle in accordance with an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a lobe configuration of the premix nozzle of the gas turbine combustor shown in FIG. 1;
FIG. 3 is a cross-sectional view of the central fuel conduit and its radial manifold configuration of the premix nozzle of the gas turbine combustor shown in FIG. 1;
FIG. 4 is a cross-sectional C-C view of a center lobe fuel nozzle of the premix nozzle for the gas turbine combustor shown in FIG. 1;
FIG. 5 is a cross-sectional view of the center lobe fuel nozzle of the premix nozzle of the gas turbine combustor shown in FIG. 1 taken along plane D-D;
FIG. 6 is a cross-sectional view of the outside fuel distribution annulus of the premix nozzle of the gas turbine combustor shown in FIG. 1 taken along plane E-E;
FIG. 7 is a cross-sectional view of the outside fuel distribution annulus of the premix nozzle of the gas turbine combustor shown in FIG. 1 taken along plane F-F.
Wherein the reference numerals are:
11-a central fuel conduit; 12-center lobe fuel nozzle;
21-an outer fuel distribution annulus fuel conduit; 22-outer fuel distribution annulus;
31-premix nozzle channel; 12 a-lobe configuration;
12 b-a hollow annular portion; 12c — a first channel;
12 d-first fuel orifice; 11 a-radial manifold;
22 a-second fuel orifice;
D1-premix nozzle channelAn inner diameter of the tract (31); d2-an inner diameter of the hollow annular portion;
L1distance between radial branch to junction of hollow annular portion and lobe structure L2Spacing of the two rows of second fuel holes in the outer fuel distribution annulus L3Distance between the tail section of the lobe structure and the premix nozzle channel outlet L4-the shortest distance between the second fuel holes in the outer fuel distribution annulus and the premix nozzle channel outlet cross-section;
H1-the outer edge height of the lobe structure; h2-the height of the inner edge of the lobe structure;
θ1-outer lobe angles of the lobe structure; theta2-inner lobe angle of lobe structure;
θ3the angle between the lobe side wall and the lobe bottom and the axis.
Detailed Description
Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the invention. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
An embodiment of the present invention provides a premixing nozzle for a gas turbine combustor, referring to fig. 1, including: the fuel nozzle comprises a central lobe type fuel nozzle 12, an outer side fuel distribution ring cavity 22 and a premixing nozzle channel 31, wherein the central lobe type fuel nozzle 12 is coaxially arranged at the central position inside the premixing nozzle channel 31 and used for uniformly introducing fuel into the premixing nozzle channel 31; the central lobe type fuel nozzle 12 comprises a hollow lobe structure 12a formed by adjacent connection of M lobes, wherein M is more than or equal to 3; providing a first fuel orifice 12d in the lobed structure 12 a; the lobe structure can widen the distribution range of the fuel holes in the radial space of the premixing channel, enhance disturbance and improve the mixing efficiency. The outer fuel distribution ring cavity 22 is disposed between the central lobe fuel nozzle 12 and the outlet of the premixing nozzle channel 31, and is coaxially disposed on the outer wall of the premixing nozzle channel 31 to communicate with the premixing nozzle channel 31, so as to introduce the secondary fuel into the premixing nozzle channel 31, further improve the premixing uniformity of fuel/air, and suppress the generation of thermoacoustic oscillation.
Therefore, the invention increases the distribution range of the fuel holes in the radial space in the channel by arranging the lobe type fuel nozzle in the premixing nozzle channel, namely, the M lobes are adjacently connected to form the hollow lobe structure 12a, and simultaneously, a complex vortex structure is induced and generated at the downstream of the lobe type fuel nozzle, thereby improving the mixing efficiency of fuel and air, reducing the mixing unevenness of the fuel and the air at the outlet section of the nozzle, inhibiting the formation of local hot spots in a combustion chamber and reducing the NOx emission. In addition, the fuel ring cavity arranged at the downstream of the lobe fuel nozzle supplies secondary fuel, so that combustion pulsation generated by different fuel incidence points is mutually offset, and the generation of thermoacoustic oscillation is inhibited; under low working condition, the combustion stability of the combustion chamber under low load can be improved by reasonably distributing the proportion of the fuel in the annular cavity. The premixing nozzle has a compact structure, and is suitable for burning natural gas, coal-made synthetic gas and other synthetic gas with medium and low calorific value.
Specifically, referring to fig. 1-7, the central lobe fuel nozzle 12 further includes a hollow annular portion 12b disposed in front of the lobe structure 12a, and a central fuel conduit 11 disposed in front of the hollow annular portion 12b for passing fuel; the cavity between the outer wall and the inner wall of the hollow annular part 12b and the lobe structure 12a forms a first channel 12c for fuel to pass through, in order to ensure that the central fuel is uniformly distributed in the hollow annular part 12b of the central lobe fuel nozzle 12 along the circumferential direction, the tail end of the central fuel guide pipe 11 is provided with P radial branch pipes 11a, P is more than or equal to 3, and the radial branch pipes 11a are communicated with the first channel 12 c; the tail part of the lobe structure 12a is provided with a first fuel hole 12d communicated with the first channel 12 c.
After entering from the front end of the central fuel conduit 11, the fuel enters the hollow annular part 12b and the cavity between the outer wall and the inner wall of the lobe structure 12a through the P radial branch pipes 11a to form a first channel 12c for the fuel to pass through, and then flows out through the first fuel hole 12d at the tail part of the lobe structure 12a and enters the premixing nozzle channel 31.
In order to ensure the mixing efficiency, the first fuel holes 12d are opened on the inner wall and the outer wall of the tail part of the lobe structure 12a, and the first fuel holes 12d are uniformly distributed along the circumferential direction of the lobe structure 12 a. And the inner diameter D of the hollow annular part 12b2Satisfies the following conditions: d1/3≤D2≤3/4D1Wherein D is1The inner diameter of the premix nozzle channel 31, the distance L between the radial branch 11a to the junction of the hollow annular portion 12b and the lobe 12a1Satisfies the following conditions: d2/2≤L1≤2D2The L1Is the distance the fuel flows within the hollow annulus.
In addition, in order to further ensure the blending efficiency, the height H of the outer edge of the lobe structure 12a1Satisfies the following conditions: d2/4≤H1≤3/4D2(ii) a Height H of the inner edge of the lobe structure 12a2Satisfies the following conditions: d2/4≤H2≤3/4D2(ii) a The number N of the first fuel holes 12d satisfies: n is more than or equal to 4M.
To improve the mixing efficiency, avoid flow separation, and reduce pressure loss of the center lobe fuel nozzle 12, the lobe configuration 12a has lobe angles θ1Theta is more than or equal to 10 degrees1Less than or equal to 30 degrees; inner lobe angle theta of lobe2Theta is more than or equal to 10 degrees2Less than or equal to 30 degrees; the included angle theta between the lobe side wall and the connecting line of the lobe bottom and the axis3Satisfies the condition that 0.5 pi/M is not more than theta3≤2π/M。
In order to suppress thermoacoustic oscillations during combustion, the second fuel holes 22a in the outer fuel distribution annulus 22 are two rows of evenly distributed holes along the premixed injectionThe outer wall of the nozzle channel 31 is circumferentially distributed, the two rows of holes are staggered, the number K of each row of holes meets the condition that K is more than or equal to 6, and the distance L between the two rows of holes2Satisfies D1/4≤L2≤D1Wherein D is1Inner diameter of the premix nozzle passage 31 to ensure uniformity of outlet fuel distribution, the shortest distance L between the second fuel holes 22a in the outer fuel distribution annulus 22 and the outlet cross-section of the premix nozzle passage 314Satisfies D1/2≤L4≤2D1. The secondary fuel is introduced into the outer fuel distribution annulus 22 from the outer fuel distribution annulus fuel conduit 21 and then enters the premix nozzle passage 31 through the second fuel orifices 22 a.
In order to ensure the uniformity of fuel/air distribution at the outlet section of the premixing nozzle channel 31 and prevent the turbulent flow of the lobe from generating excessive disturbance at the outlet of the channel so as to influence the stability of the flame at the outlet of the nozzle, the distance L between the tail section of the lobe structure 12a and the outlet of the premixing nozzle channel 313Satisfy 2D1≤L3≤5D1Wherein D is1Is the inner diameter of the premix nozzle passage 31.
In the embodiment, the outlet speed of the premixing nozzle is set to be 80-160 m/s, the jet speed of the first fuel hole of the central wave lobe type fuel nozzle is 20-60 m/s, and the jet speed of the second fuel hole of the outer fuel ring cavity is 40-100 m/s. Under the rated load condition, the lobe structure is efficiently mixed, so that the fuel and the air are quickly and uniformly mixed, the formation of local hot spots caused by nonuniform mixing is reduced, and the NOx emission is reduced. Meanwhile, the secondary fuel introduced into the fuel ring cavity inhibits the occurrence of thermoacoustic oscillation. At low load conditions, however, injection flow under fully premixed conditions can result in a decrease in combustion stability as the equivalence ratio decreases. At the moment, the fuel proportion of the outer side ring cavity is properly increased, so that the fuel concentration at the periphery of the jet flow is increased, the ignition delay time is reduced, and the combustion stability under the condition of low equivalence ratio is improved.
It should be noted that, in the drawings or the specification, experimental modes not shown or described are all the modes known to those skilled in the art, and are not described in detail. In addition, the above definitions of the components are not limited to the specific structures and shapes mentioned in the embodiments, and those skilled in the art may easily modify or replace them, for example:
(1) the second fuel holes of the outer fuel ring cavity can also adopt other forms or structures, and the number of the rows of the holes can also be multiple, so long as the same function can be achieved;
(2) the first fuel hole of the central lobe type fuel nozzle can also be inclined at a proper angle or arranged on the tail edge surface of the lobe to enable the jet flow direction to be parallel to the axis direction, so long as the mixing degree of fuel and air at the outlet of the nozzle can meet the requirement;
(3) examples of parameters that include particular values may be provided herein, but the parameters need not be exactly equal to the corresponding values, but may be approximated within acceptable error tolerances or design constraints;
(4) the directional terms used in the practice, such as "front", "back", etc., are used only in reference to the orientation of the drawings and are not intended to limit the scope of the present invention;
in conclusion, the premixing nozzle provided by the invention fully utilizes the characteristics of low pressure loss and high mixing efficiency of the lobe structure, and the mixing efficiency of fuel and air is greatly improved by adopting the central fuel nozzle with the lobe structure and reasonably setting the position of the fuel opening. Meanwhile, the downstream of the central lobe type fuel nozzle further adopts a fuel ring cavity to supply secondary fuel, so that the secondary fuel can be used for supplementing the shortage of mixing of the lobe type fuel nozzle at the edge of a flow channel under a rated working condition, and the uniformity of fuel air distribution at the outlet of the nozzle is improved, thereby reducing NOx emission; under the working condition of low equivalence ratio, the secondary fuel can be used for improving the concentration of jet edge fuel and increasing combustion stability. Meanwhile, the double-row fuel hole design of the annular cavity can also inhibit the generation of thermoacoustic oscillation, broadens the stable operation range of the combustion chamber and realizes the quick response of the combustion chamber to load. The premixing nozzle has the advantages of compact structure, flexible adjustment and high reliability, and can be suitable for the combustion of various gas fuels such as natural gas, coal-made synthetic gas and other low and medium calorific value synthetic gas.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A gas turbine combustor premix nozzle, comprising: a central lobe fuel nozzle (12), an outer fuel distribution annulus (22), and a premix nozzle passage (31),
the central lobe type fuel nozzle (12) is coaxially arranged at the central position in the premixing nozzle channel (31) and is used for uniformly introducing fuel into the premixing nozzle channel (31); the central lobe type fuel nozzle (12) comprises a hollow lobe structure (12a) formed by adjacent connection of M lobes, M is more than or equal to 3, and a first fuel hole (12d) is arranged on the lobe structure (12 a);
the outer fuel distribution ring cavity (22) is arranged between the central lobe type fuel nozzle (12) and an outlet of the premixing nozzle channel (31), is coaxially arranged on the outer wall of the premixing nozzle channel (31) and is communicated with the premixing nozzle channel (31) and is used for introducing secondary fuel into the premixing nozzle channel (31).
2. The combustor premix nozzle of claim 1, wherein said central lobe fuel nozzle (12) further comprises a hollow annular portion (12b) disposed forward of said lobe structure (12a), a central fuel conduit (11) disposed forward of hollow annular portion (12b) for passing fuel;
the hollow annular part (12b) and a cavity between the outer wall and the inner wall of the lobe structure (12a) form a first channel (12c) for fuel to pass through, P radial branch pipes (11a) are arranged at the tail end of the central fuel guide pipe (11), P is more than or equal to 3, and the radial branch pipes (11a) are communicated with the first channel (12 c); the tail part of the lobe structure (12a) is provided with a first fuel hole (12d) communicated with the first channel (12 c).
3. The combustor premix nozzle according to claim 2, wherein said first fuel holes (12d) open on the inner and outer walls of the aft portion of said lobed structure (12a), said first fuel holes (12d) being evenly distributed circumferentially along the lobed structure (12 a).
4. Premix nozzle according to claim 2, characterized in that the inner diameter D of the hollow annular portion (12b)2Satisfies the following conditions: d1/3≤D2≤3/4D1Wherein D is1Is the inner diameter of the premixing nozzle passage (31).
5. Premix nozzle according to claim 2, characterized in that the distance L between the radial branch (11a) to the junction of the hollow annular portion (12b) and the lobe structure (12a)1Satisfies the following conditions: d2/2≤L1≤2D2Wherein D is2Is the inner diameter of the hollow annular part (12 b).
6. The premix nozzle of claim 2, wherein the lobe structure (12a) has an outer rim height H1Satisfies the following conditions: d2/4≤H1≤3/4D2(ii) a The height H2 of the inner edge of the lobe structure (12a) satisfies: d2/4≤H2≤3/4D2(ii) a The number N of the first fuel holes (12d) satisfies: n is more than or equal to 4M; wherein D is2Is the inner diameter of the hollow annular part (12 b).
7. The premix nozzle of claim 1, wherein the lobe configuration (12a) has lobe angles θ1Theta is more than or equal to 10 degrees1Less than or equal to 30 degrees; inner lobe angle theta of lobe2Theta is more than or equal to 10 degrees2Less than or equal to 30 degrees; the included angle theta between the lobe side wall and the connecting line of the lobe bottom and the axis3Satisfies the condition that 0.5 pi/M is not more than theta3≤2π/M。
8. The premix nozzle of claim 1, wherein the outer portion is a portion of a fuel injectorThe second fuel holes (22a) in the side fuel distribution ring cavity (22) are two rows of holes which are uniformly distributed, the two rows of holes are distributed along the circumferential direction of the outer wall of the premixing nozzle channel (31), the two rows of holes are staggered, the number K of each row of holes meets the condition that K is more than or equal to 6, and the distance L between the two rows of holes2Satisfies D1/4≤L2≤D1Wherein D is1Is the inner diameter of the premixing nozzle passage (31).
9. The premix nozzle of claim 8, wherein a shortest distance L between a second fuel hole (22a) in said outer fuel distribution annulus (22) and an outlet cross-section of said premix nozzle passage (31)4Satisfies D1/2≤L4≤2D1。
10. The premix nozzle of claim 1, wherein a distance L between an aft cross-section of said lobe structure (12a) and an outlet of said premix nozzle passage (31)3Satisfy 2D1≤L3≤5D1Wherein D is1Is the inner diameter of the premixing nozzle passage (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010292812.3A CN111473362B (en) | 2020-04-14 | 2020-04-14 | Premixing nozzle of gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010292812.3A CN111473362B (en) | 2020-04-14 | 2020-04-14 | Premixing nozzle of gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111473362A true CN111473362A (en) | 2020-07-31 |
| CN111473362B CN111473362B (en) | 2021-11-16 |
Family
ID=71752043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010292812.3A Active CN111473362B (en) | 2020-04-14 | 2020-04-14 | Premixing nozzle of gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111473362B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114440214A (en) * | 2022-01-24 | 2022-05-06 | 上海应用技术大学 | Non-premixed air classification low NOx combustor |
| CN114688526A (en) * | 2020-12-31 | 2022-07-01 | 大连理工大学 | Pre-film type gas-assisted atomizing nozzle with petal-shaped outlet |
| CN114992675A (en) * | 2022-05-19 | 2022-09-02 | 沈阳航空航天大学 | Aeroengine combustion chamber and method for organizing combustion thereof |
| CN115264529A (en) * | 2021-04-29 | 2022-11-01 | 通用电气公司 | Fuel mixer |
| CN115355534A (en) * | 2022-09-05 | 2022-11-18 | 中国联合重型燃气轮机技术有限公司 | Gas turbine fuel mixing system and gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5622054A (en) * | 1995-12-22 | 1997-04-22 | General Electric Company | Low NOx lobed mixer fuel injector |
| CN105637206A (en) * | 2013-06-28 | 2016-06-01 | 埃克森美孚上游研究公司 | Clusters of polynomials for data points |
| CN106123031A (en) * | 2015-05-08 | 2016-11-16 | 安萨尔多能源瑞士股份公司 | Mixing system |
| CN106196173A (en) * | 2015-04-15 | 2016-12-07 | 通用电气公司 | For controlling the dynamic system and method for burning in combustion system |
| CN107208894A (en) * | 2015-01-29 | 2017-09-26 | 西门子能源公司 | The fuel injector including lobed mixer and blade for spraying alternative fuel in combustion gas turbine |
-
2020
- 2020-04-14 CN CN202010292812.3A patent/CN111473362B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5622054A (en) * | 1995-12-22 | 1997-04-22 | General Electric Company | Low NOx lobed mixer fuel injector |
| CN105637206A (en) * | 2013-06-28 | 2016-06-01 | 埃克森美孚上游研究公司 | Clusters of polynomials for data points |
| CN107208894A (en) * | 2015-01-29 | 2017-09-26 | 西门子能源公司 | The fuel injector including lobed mixer and blade for spraying alternative fuel in combustion gas turbine |
| CN106196173A (en) * | 2015-04-15 | 2016-12-07 | 通用电气公司 | For controlling the dynamic system and method for burning in combustion system |
| CN106123031A (en) * | 2015-05-08 | 2016-11-16 | 安萨尔多能源瑞士股份公司 | Mixing system |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114688526A (en) * | 2020-12-31 | 2022-07-01 | 大连理工大学 | Pre-film type gas-assisted atomizing nozzle with petal-shaped outlet |
| CN115264529A (en) * | 2021-04-29 | 2022-11-01 | 通用电气公司 | Fuel mixer |
| CN114440214A (en) * | 2022-01-24 | 2022-05-06 | 上海应用技术大学 | Non-premixed air classification low NOx combustor |
| CN114992675A (en) * | 2022-05-19 | 2022-09-02 | 沈阳航空航天大学 | Aeroengine combustion chamber and method for organizing combustion thereof |
| CN115355534A (en) * | 2022-09-05 | 2022-11-18 | 中国联合重型燃气轮机技术有限公司 | Gas turbine fuel mixing system and gas turbine |
| CN115355534B (en) * | 2022-09-05 | 2024-03-12 | 中国联合重型燃气轮机技术有限公司 | Gas turbine fuel mixing system and gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111473362B (en) | 2021-11-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111473362B (en) | Premixing nozzle of gas turbine combustor | |
| EP2500641B1 (en) | Recirculating product injection nozzle | |
| JP4906689B2 (en) | Burner, combustion device, and method for modifying combustion device | |
| JP5850900B2 (en) | Reheat burner arrangement | |
| US7757491B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| JP5772245B2 (en) | Fuel injection device | |
| JP3860952B2 (en) | Gas turbine combustor | |
| CN109404967B (en) | Combustion chamber of gas turbine and gas turbine | |
| CN110686275B (en) | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation | |
| CN111059574B (en) | Swirl cup type dual-fuel air atomizing nozzle structure | |
| CN111396927B (en) | Two-dimensional array low-pollution combustion device without traditional swirler | |
| JP5372815B2 (en) | Gas turbine combustor | |
| JP5926635B2 (en) | Gas turbine combustor | |
| CN112128800A (en) | Low-swirl direct-injection combustor for low emission of gas turbine | |
| CN213746853U (en) | Low-swirl direct-injection combustor for low emission of gas turbine | |
| CN109708148B (en) | Gas turbine combustor doublestage radial swirler | |
| CN111829007A (en) | Axial staged combustion chamber based on flame tube concave cavity structure | |
| CN104791847A (en) | Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine | |
| US11619388B2 (en) | Dual fuel gas turbine engine pilot nozzles | |
| CN108019749A (en) | A kind of swirl-flow premixed nozzle of radial grading | |
| CN114992671B (en) | Combined gas turbine combustion chamber | |
| JPH0343535B2 (en) | ||
| JP6092007B2 (en) | Gas turbine combustor | |
| JP5241906B2 (en) | Burner and burner operation method | |
| CN113606608A (en) | On-duty fuel nozzle tip, fuel nozzle and gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |