CN107620979B - Gas turbine - Google Patents
Gas turbine Download PDFInfo
- Publication number
- CN107620979B CN107620979B CN201710792489.4A CN201710792489A CN107620979B CN 107620979 B CN107620979 B CN 107620979B CN 201710792489 A CN201710792489 A CN 201710792489A CN 107620979 B CN107620979 B CN 107620979B
- Authority
- CN
- China
- Prior art keywords
- fuel
- air
- distributor
- gas turbine
- distribution
- 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.)
- Active
Links
Abstract
The invention discloses a gas turbine, which comprises a nozzle, wherein the nozzle comprises a fuel-air mixer, the fuel-air mixer comprises an air distributor and a fuel distributor, and the outer peripheral surface of the air distributor is provided with a plurality of air grooves which extend along the axial direction of the air distributor and penetrate through the air distributor; the fuel distributor body is internally provided with a fuel channel, a premixing distribution channel communicated with the fuel channel and a jet hole communicated with the premixing distribution channel, and the fuel distributor is connected with the air distributor so that the premixing distribution channel is communicated with the air groove. The invention has simple structure, can finish the micro-mixing of the fuel and the air in a small-scale space, improves the mixing effect of the fuel and the air, and effectively reduces the emission of pollutants.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine with a fuel-air mixer.
Background
The mixture of compressed air and fuel is combusted in a combustor of the gas turbine, producing high temperature flue gases that push the turbine to do work, wherein the combustor mixes and injects the fuel and air through its nozzles (also commonly referred to as fuel nozzles) into the combustion zone. In the related art, a mixing tube, an air distribution manifold or a fuel distribution manifold is arranged in the fuel nozzle, and fuel and air are premixed through the mixing tube, the air distribution manifold or the fuel distribution manifold and then injected into a combustion area, so that pollutant emission is reduced. However, the fuel nozzle cannot achieve a lower pollutant emission level to meet environmental protection standards after the combustion temperature is further increased. Thus, there is a need to control pollutant emissions during the mixing of fuel and air.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
Therefore, the invention provides the gas turbine, the fuel-air mixer of the gas turbine has a simple structure, micro-mixing of fuel and air can be completed in a small-scale space, the mixing effect of the fuel and the air is improved, and the emission of pollutants is effectively reduced.
According to an embodiment of the invention, a gas turbine comprises a nozzle comprising a fuel-air mixer, the fuel-air mixer comprising: the air distributor is characterized in that a plurality of air grooves are formed in the outer peripheral surface of the air distributor, the air grooves are distributed at intervals along the circumferential direction of the air distributor, and the air grooves extend in the axial direction of the air distributor and penetrate through the air distributor; the fuel distributor is internally provided with a fuel channel, a premixing distribution channel and a jet hole for ejecting the mixture of fuel and air from the premixing distribution channel, the premixing distribution channel is communicated with the fuel channel, the jet hole is communicated with the premixing distribution channel, the fuel channel and the premixing distribution channel respectively extend from the rear end face of the fuel distributor to the front end face of the fuel distributor, the jet hole extends from the front end face of the fuel distributor to the rear end face of the fuel distributor, and the fuel distributor is connected with the air distributor so that the premixing distribution channel is communicated with the air groove.
According to the gas turbine, the fuel-air mixer is simple in structure, micro-mixing of fuel and air can be completed in a small-scale space through the arrangement of the air distributing body and the fuel distributing body, the mixing effect of the fuel and the air is improved, and the emission of pollutants is effectively reduced.
In some embodiments, the air channels extend in a direction offset from the center of the air distributor in a cross-section of the air distributor.
In some embodiments, a plurality of the air slots are evenly spaced around the center of the air distributor body.
In some embodiments, the number of the air grooves is four, and the extending directions of two adjacent air grooves are orthogonal to each other in the cross section of the air distributor.
In some embodiments, the air distribution body has a central passage therein extending in an axial direction of the air distribution body and through the air distribution body, the central passage communicating with the fuel passage.
in some embodiments, the fuel passage is coaxial with the central passage.
In some embodiments, the fuel passage is centrally located in the fuel distribution body, and the premix distribution passages are spaced around the fuel passage.
In some embodiments, the premix distribution passage extends in a radial direction of the fuel dispensing body in a cross-section of the fuel dispensing body.
In some embodiments, adjacent two premix distribution channels differ in length along the radial extension of the fuel distribution body.
in some embodiments, the jet holes include an inner ring jet hole and an outer ring jet hole, the inner ring jet hole is divided into a plurality of rows distributed at intervals in a circumferential direction around the fuel channel on the front end surface of the fuel distributor, the outer ring jet hole is divided into a plurality of rows distributed at intervals around the inner ring jet hole, each row of the inner ring jet hole is arranged at intervals in a radial direction of the fuel distributor, and the two rows of the outer ring jet hole correspond to a region between two adjacent rows of the inner ring jet hole.
In some embodiments, the air distributor and the fuel distributor are both cylinders.
In some embodiments, the air distributor has a diameter less than or equal to the diameter of the fuel distributor.
In some embodiments, the air and fuel dispensers are disposed in close proximity.
In some embodiments, the air and fuel ligands are welded by brazing.
In some embodiments, the air distribution body and the fuel distribution body are integrally formed.
In some embodiments, the gas turbine further comprises a compressor in communication with a combustor comprising the nozzle, the combustor in communication with the turbine, and a turbine in communication with the compressor.
Drawings
FIG. 1 is a schematic diagram of the composition of a gas turbine according to an embodiment of the invention.
FIG. 2 is a schematic view of a combustor of a gas turbine according to an embodiment of the present invention;
FIG. 3 is an overall schematic view of a fuel-air mixer according to an embodiment of the invention;
FIG. 4 is a cross-sectional view of an air distributor of a fuel-air mixer according to an embodiment of the present invention;
FIG. 5 is a schematic illustration of an aft end face of a fuel dispensing body of a fuel-air mixer according to an embodiment of the present invention;
FIG. 6 is a schematic illustration of a front face of a fuel dispensing body of a fuel-air mixer according to an embodiment of the present invention;
Reference numerals:
The fuel-air mixer 100, the air distributor 1, the fuel distributor 2, the rear end face 21 of the fuel distributor, the front end face 22 of the fuel distributor, the air grooves 3, the fuel channels 4, the premixing distribution channels 5, the first group of premixing distribution channels 51, the second group of premixing channels 52, the jet holes 6, the inner ring jet holes 61, the outer ring jet holes 62, the central channel 7, the fuel pipes 8, the mounting flange 9, the air 10, the fuel 11, the external air 12, the high-pressure gas 13, the compressor 14, the turbine 15, the generator 16, the nozzle 200, the combustor 300 and the gas turbine 400.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1-6, in accordance with a gas turbine 400 according to an embodiment of the present invention, the gas turbine 400 includes a combustor 300, the combustor 300 includes a nozzle 200 (shown in fig. 2), the nozzle 200 includes a fuel-air mixer 100, and the fuel-air mixer 100 includes an air distribution body 1 and a fuel distribution body 2.
A plurality of air grooves 3 are provided on the outer peripheral surface of the air distributor 1, the air grooves 3 are distributed at intervals in the circumferential direction of the air distributor 2, and the air grooves 3 extend through the air distributor 1 in the axial direction (the left-right direction shown in fig. 3) of the air distributor 1. In other words, each air groove 3 is formed over the entire length of the air distributing body 1, and as shown in fig. 3, the air groove 3 extends from the left end face of the air distributing body 1 to the right end face of the air distributing body 1.
The fuel distributor body 2 has therein a fuel passage 4, a premix distribution passage 5, and a jet hole 6, wherein the fuel passage 4 and the premix distribution passage 5 extend from a rear end face 21 (a left end face of the fuel distributor body 2 in fig. 3) of the fuel distributor body 2 toward a front end face 22 (a right end face of the fuel distributor body 2 in fig. 3) of the fuel distributor body 2, respectively (here, "front" refers to an injection direction of a mixture of fuel and air, and a direction from left to right as viewed in fig. 3 is rear). The jet hole 6 extends from the front end face 22 of the fuel dispensing body 2 toward the rear end face 21 of the fuel dispensing body 2, in other words, as shown in fig. 3, the jet hole 6 extends from the right end face of the fuel dispensing body 2 toward the left end face of the fuel dispensing body 2.
The premixing distribution channel 5 is communicated with the fuel channel 4, the jet hole 6 is communicated with the premixing distribution channel 5, the mixture of fuel and air is sprayed out from the premixing distribution channel 5 through the jet hole 6, the fuel distributor 2 is connected with the air distributor 1 so that the premixing distribution channel 5 is communicated with the air groove 3, the premixing distribution channel 5 is communicated with the air groove 3 and the fuel channel 4, the air 10 in the air groove 3 and the fuel 11 in the fuel channel 4 can respectively enter the premixing distribution channel 5, and the mixing of the air and the fuel is completed in the premixing distribution channel 5.
In other words, as shown in fig. 3, the air distributor 1 is provided on the left side of the fuel distributor 2, and the premix distribution passage 5 extends rightward from the left end face of the fuel distributor 2 in order to facilitate communication between the air grooves 3 in the air distributor 1 and the premix distribution passage 5; to facilitate injection of the mixture of fuel 11 and air 10 in the premix distribution channel 5 to the right combustion zone, the jet holes 6 extend to the left from the right end face of the fuel distribution body 2, whereby the mixture of fuel 11 and air 10 is injected into the combustion zone through the jet holes 6 on the right end face of the fuel distribution body 2.
It will be appreciated that by means of the air distributor 1 provided with air slots 3 and the fuel distributor 2 provided with premixing distribution channels 5 and fuel channels 4, a mixing of fuel 11 and air 10 is achieved, which in the case of small radial dimensions of the premixing distribution channels 5 or short distances of the premixing distribution channels 5 extending from left to right is also sufficiently mixed to achieve a micromixing of fuel 11 and air 10 in a small-scale space. Here, "micro" in "micro mixing" means that a mixing space of fuel and air is small, and micro mixing of fuel 11 and air 10 can be achieved, whereby the fuel-air mixer of the gas turbine according to the embodiment of the present invention is a micro mixer.
The fuel-air mixer of the gas turbine has a simple structure, and the micro-mixing of the fuel and the air in the small-scale space can be realized through the air distributor and the fuel distributor, so that the mixing effect of the fuel and the air is improved, and the emission of pollutants is effectively reduced.
In some embodiments, in the cross section of the air distributing body 1, the extending direction of the air grooves 3 is deviated from the center of the air distributing body 1, for example, in the cross section shown in fig. 4, the extending direction of each air groove 3 from the outer circumferential surface of the air distributing body 1 to the inside of the air distributing body 1 is deviated from the center of the air distributing body 1, so that the air forms a rotational flow after entering the air grooves 3 on the air distributing body 1, and the mixing uniformity of the air 10 and the fuel 11 is further improved.
In some embodiments, a plurality of air slots 3 are evenly spaced around the center of the air distributor body 1.
In some embodiments, as shown in fig. 4, there are four air slots 3, and in the cross section of the air distributor 1, the extending directions of two adjacent air slots 3 are orthogonal to each other, so that the air 10 enters the four air slots 3 respectively to form a rotational flow, it is understood that the present invention is not limited thereto, for example, there are six air slots 3, as long as the air 10 enters the air slots 3 to form a rotational flow.
in some embodiments, the air distributing body 1 has a central channel 7 therein, which is communicated with the fuel channel 4, and the central channel 7 extends along the axial direction of the air distributing body 1 and penetrates through the air distributing body 1, in other words, the central channel 7 is located at the center of the air distributing body 1 and extends from the left end face of the air distributing body 1 to the right end face of the air distributing body 1 to be communicated with the fuel channel 4 on the fuel distributing body 2 at the right side of the air distributing body 1, so as to supply fuel into the fuel channel 4.
In some embodiments, the fuel channel 4 is located in the center of the fuel dispensing body 2, and the fuel channel 4 is coaxial with the central channel 7, in other words, the air dispensing body 1 and the fuel dispensing body 2 are coaxial because the central channel 7 and the fuel channel 4 are located in the center of the air dispensing body 1 and the center of the fuel dispensing body 2, respectively.
In some embodiments, the premix distribution passage 5 is provided in plurality, and the plurality of premix distribution passages 5 are arranged at intervals around the fuel passage 4. In other words, there may be a plurality of premix distribution channels 5 (a plurality is here intended to mean at least two, e.g. two, three, etc.) within the fuel distribution body 2, the plurality of premix distribution channels 5 communicating with the fuel channels 4 being arranged at intervals around the circumference of the fuel channels 4, the fuel and air being mixed at multiple locations within the fuel distribution body 2, increasing the blending effect of the fuel 11 and the air 10.
In some embodiments, the premix distribution passage 5 extends in the radial direction of the fuel dispensing body 2 in the cross section of the fuel dispensing body 2, as shown in fig. 5, one end of the premix distribution passage 5 communicates with the fuel passage 4, and the other end of the premix distribution passage 5 extends radially outward of the fuel dispensing body 2.
In some embodiments, the two adjacent premixing distribution channels 5 have different lengths along the radial extension of the fuel distributing body 2, and the premixing distribution channels 5 having different lengths along the radial extension may be respectively applied to different combustion loads.
Further, as shown in fig. 5, the premix distribution passage 5 includes a first group of premix distribution passages 51 and a second group of premix distribution passages 52, and the length of the second group of premix distribution passages 52 extending in the radial direction of the fuel dispensing body 2 is longer than the length of the first group of premix distribution passages 51 extending in the radial direction of the fuel dispensing body 2. First and second sets of premix distribution passages 51 and 52, respectively, communicate with fuel passage 4, and fuel and air may be premixed in first and second sets of premix distribution passages 51 and 52, respectively, to accommodate different combustion loads.
Further, the first group of premix distribution passages 51 and the second group of premix distribution passages 52 are respectively provided with a plurality of passages, preferably, the first group of premix distribution passages 51 and the second group of premix distribution passages 52 are respectively provided with four passages, and one of the first group of premix distribution passages 51 is provided between two adjacent ones of the second group of premix distribution passages 52. It is to be understood that the present invention is not limited thereto, and the number and arrangement of the premix distribution passages 55 may be selected according to actual needs.
In some embodiments, the jet holes 6 include multiple sets of jet holes 6 in one-to-one correspondence with multiple premix distribution channels 5 to inject the mixture of fuel 11 and air 10 within different premix distribution channels 5 into the combustion zone. Further, as shown in fig. 6, the jet holes 6 include inner ring jet holes 61 and outer ring jet holes 62, the inner ring jet holes 61 are divided into a plurality of rows that are circumferentially spaced around the fuel passage 4 on the front end face 22 of the fuel partitioning body 2, the outer ring jet holes 62 are divided into a plurality of rows that are circumferentially spaced around the inner ring jet holes 61, each row of the inner ring jet holes 61 is radially spaced along the fuel partitioning body 1, and two rows of the outer ring jet holes 62 correspond to regions between two adjacent rows of the inner ring jet holes 61.
In other words, the jet holes 6 include two groups, one group of the jet holes is located outside the other group of the jet holes in the radial direction of the fuel distribution plate 2, and then the one group of the jet holes is the outer ring jet hole 62, the other group of the jet holes is the inner ring jet hole 61, the inner ring jet hole 61 and the outer ring jet hole 62 are respectively divided into a plurality of rows distributed at intervals in the circumferential direction around the fuel passage 4, and the two rows of the outer ring jet holes 62 correspond to the regions between the two adjacent rows of the inner ring jet holes 61, it can be understood that the two rows of the outer ring jet holes 62 are in the regions between the outward extensions of the two adjacent rows of the inner ring jet.
Further, inner ring jet bore 61 may be in communication with first set of premix distribution passages 51 and outer ring jet bore 62 may be in communication with second set of premix distribution passages 52 to inject fuel 11 and air 10 premixed in first set of premix distribution passages 51 and second set of premix distribution passages 52, respectively, into the combustion zone. It is understood that the present invention is not limited thereto, and the arrangement form of the jet holes 6 may be specifically selected according to actual needs, and the communication form of different jet holes 6 and different premixing distribution channels 5 may also be specifically selected according to actual needs.
In some embodiments, as shown in fig. 4-6, the air distributor 1 and the fuel distributor 2 are both cylindrical bodies, and further, the diameter of the air distributor 1 is less than or equal to the diameter of the fuel distributor 2.
In some embodiments, the air distributor 1 and the fuel distributor 2 are closely fitted, and as shown in fig. 3, the right end face of the air distributor 1 is closely fitted to the left end face 21 of the fuel distributor 2, so as to facilitate the communication between the central passage 7 and the fuel passage 4 and the communication between the air grooves 3 and the premixing distribution passage 5. It is understood that, in order to achieve close fitting of the air distributor 1 and the fuel distributor 2, the air distributor 1 and the fuel distributor 2 are welded by brazing, or the air distributor 1 and the fuel distributor 2 are integrally formed, for example, by 3D printing technology.
In some embodiments, as shown in FIG. 1, the gas turbine 400 further includes a compressor 14 and a turbine 15, the compressor 14 being in communication with the combustor 300, the combustor 300 being in communication with the turbine 15, and the turbine 15 being in communication with the compressor 14. External air 12 is compressed into high-pressure air 10 in a compressor 14 through a nearly adiabatic process, the high-pressure air 10 enters a nozzle 200 of a combustor 300 to be mixed with fuel 11 and combusted, high-temperature and high-pressure gas 13 generated after combustion enters a turbine 15 to do work, a part of the generated work drives the compressor 14, and the other part of the generated work is output outwards, for example, the generated work drives a generator 16 to output power as shown in fig. 1.
a gas turbine 400 according to a specific embodiment of the present invention is described below with reference to fig. 1-6.
As shown in fig. 1 to 6, a gas turbine 400 according to an embodiment of the present invention includes a combustor 300, a compressor 14, a turbine 15, and a generator 16, the combustor 300 including a nozzle 200, the nozzle 200 including a fuel-air mixer 100. The compressor 14 is communicated with the combustor 300, the combustor 300 is communicated with the turbine 15, external air 12 is compressed into high-pressure air 10 in the compressor 14 through a nearly adiabatic process, the high-pressure air 10 enters the nozzle 200 of the combustor 300 to be mixed with fuel 11 and combusted, high-temperature and high-pressure gas 13 generated after combustion enters the turbine 15 to do work, one part of the generated work drives the compressor 14, and the other part of the generated work is output outwards, for example, the power is output by driving the generator 16 shown in fig. 6.
The fuel-air mixer 100 comprises an air distributor 1 and a fuel distributor 2. The left side of the air distributing body 1 is connected and closely attached to the fuel distributing body 2, the air distributing body 1 and the fuel distributing body 2 are both cylindrical, and the diameter of the air distributing body 1 is smaller than that of the fuel distributing body 2, and preferably, the air distributing body 1 and the fuel distributing body 2 are coaxially connected to each other.
The peripheral surface of the air distributing body 1 is provided with four air grooves 3, the four air grooves 3 are uniformly arranged at intervals along the circumferential direction of the air distributing body 2 and around the center of the air distributing body 1, the air grooves 3 extend along the axial direction of the air distributing body 1 and penetrate through the air distributing body 1, on the cross section of the air distributing body 1, the extending directions of the air grooves 3 deviate from the center of the air distributing body 1, the extending directions of two adjacent air grooves 3 are orthogonal to each other, and air 10 enters the four air grooves 3 respectively to form rotational flow. The air distributor 1 has a central passage 7 therein, and the central passage 7 extends in the axial direction of the air distributor 1 and penetrates the air distributor 1.
The fuel distributor 2 has therein a fuel passage 4 communicating with the central passage 7, a premix distribution passage 5 communicating with the air groove 3, and a jet hole 6 communicating with the premix distribution passage, wherein the fuel passage 4 and the premix distribution passage 5 extend from a rear end face (left end face) 21 of the fuel distributor 2 toward a front end face 22 (right end face) of the fuel distributor 2, respectively, and the jet hole 6 extends from the front end face (right end face) 22 of the fuel distributor 2 toward the rear end face (left end face) 21 of the fuel distributor 2.
The fuel passage 4 is located at the center of the fuel dispensing body 2, the premix distribution passages 5 include a first group of premix distribution passages 51 and a second group of premix distribution passages 52, the first group of premix distribution passages 51 and the second group of premix distribution passages 52 are respectively arranged at regular intervals around the circumference of the fuel passage 4, and the length of the second group of premix distribution passages 52 extending in the radial direction of the fuel dispensing body 2 is longer than the length of the first group of premix distribution passages 51 extending in the radial direction of the fuel dispensing body 2. The first and second sets of premix distribution passages 51 and 52 are four in number, and one of the first set of premix distribution passages 51 is disposed between adjacent ones of the second set of premix passages 52.
The jet holes 6 comprise inner ring jet holes 61 communicated with the first group of premixing distribution channels 51 and outer ring jet holes 62 communicated with the second group of premixing distribution channels 52, on the front end surface 22 of the fuel distributor 2, the inner ring jet holes 61 are divided into eight rows distributed at intervals in the circumferential direction around the fuel channel 4, the outer ring jet holes 62 are divided into sixteen rows distributed at intervals around the inner ring jet holes 61, the inner ring jet holes 61 of each row are arranged at intervals in the radial direction of the fuel distributor 1, and the two rows of outer ring jet holes 62 correspond to the area between the two adjacent rows of inner ring jet holes 61.
The nozzle 200 further comprises a fuel tube 8, the fuel tube 8 extending through a central passage 7 in the air distribution body 1 into the fuel passage 4 in the fuel distribution body 2 for supplying fuel 11 into the fuel distribution body 2.
The left end of the fuel pipe 8 is provided with a mounting flange 9 to facilitate mounting of the nozzle 200 within a combustor 300 of a gas turbine.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (16)
1. A gas turbine engine comprising a nozzle including a fuel-air mixer, the fuel-air mixer comprising:
The air distributor is characterized in that a plurality of air grooves are formed in the outer peripheral surface of the air distributor, the air grooves are distributed at intervals along the circumferential direction of the air distributor, and the air grooves extend in the axial direction of the air distributor and penetrate through the air distributor;
The fuel distributor is internally provided with a fuel channel, a premixing distribution channel and a jet hole for ejecting the mixture of fuel and air from the premixing distribution channel, the premixing distribution channel is communicated with the fuel channel, the jet hole is communicated with the premixing distribution channel, the fuel channel and the premixing distribution channel respectively extend from the rear end face of the fuel distributor to the front end face of the fuel distributor, the jet hole extends from the front end face of the fuel distributor to the rear end face of the fuel distributor, and the fuel distributor is connected with the air distributor so that the premixing distribution channel is communicated with the air groove.
2. The gas turbine according to claim 1, wherein the air groove extends in a direction offset from a center of the air distributor in a cross section of the air distributor.
3. the gas turbine of claim 2, wherein a plurality of said air slots are evenly spaced about a center of said air distributor body.
4. The gas turbine according to claim 3, wherein the number of the air grooves is four, and the extending directions of two adjacent air grooves are orthogonal to each other in the cross section of the air distributing body.
5. The gas turbine of claim 1, wherein said air distributor body has a central passage therein extending in an axial direction of said air distributor body and through said air distributor body, said central passage communicating with said fuel passage.
6. The gas turbine of claim 5, wherein said fuel passage is coaxial with said central passage.
7. the gas turbine of claim 1, wherein said fuel passage is centrally located in said fuel distributor block, and said premix distribution passages are plural and are spaced around said fuel passage.
8. The gas turbine of claim 7, wherein said premix distribution passage extends in a radial direction of said fuel distribution body in a cross-section of said fuel distribution body.
9. The gas turbine of claim 8, wherein adjacent two premix distribution passages differ in length along a radial extension of the fuel distribution body.
10. The gas turbine according to any one of claims 1 to 9, wherein the jet holes include an inner ring jet hole and an outer ring jet hole, the inner ring jet hole being divided into a plurality of rows that are circumferentially spaced around the fuel passage on the front end face of the fuel distributor, the outer ring jet hole being divided into a plurality of rows that are circumferentially spaced around the inner ring jet hole, each row of the inner ring jet hole being radially spaced along the fuel distributor, two rows of the outer ring jet hole corresponding to a region between adjacent two rows of the inner ring jet hole.
11. A gas turbine according to any one of claims 1 to 9, wherein the air distributor body and the fuel distributor body are both cylindrical bodies.
12. The gas turbine of claim 11, wherein the air distributor body has a diameter less than or equal to a diameter of the fuel distributor body.
13. A gas turbine according to any of claims 1 to 9, wherein the air distributor body and the fuel distributor body are arranged in close proximity.
14. The gas turbine of claim 13, wherein said air distributor body and said fuel distributor body are welded by brazing.
15. The gas turbine of claim 13, wherein said air distributor body and said fuel distributor body are integrally formed.
16. The gas turbine of any of claims 1-9, further comprising a compressor in communication with a combustor comprising the nozzle, the combustor in communication with the turbine, and a turbine in communication with the compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710792489.4A CN107620979B (en) | 2017-09-05 | 2017-09-05 | Gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710792489.4A CN107620979B (en) | 2017-09-05 | 2017-09-05 | Gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107620979A CN107620979A (en) | 2018-01-23 |
| CN107620979B true CN107620979B (en) | 2019-12-06 |
Family
ID=61088375
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710792489.4A Active CN107620979B (en) | 2017-09-05 | 2017-09-05 | Gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107620979B (en) |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6418726B1 (en) * | 2001-05-31 | 2002-07-16 | General Electric Company | Method and apparatus for controlling combustor emissions |
| CN104566473B (en) * | 2014-12-30 | 2018-02-09 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of dual fuel nozzle of gas-turbine combustion chamber |
| CN204438195U (en) * | 2014-12-30 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of fuel-air blender and gas turbine |
-
2017
- 2017-09-05 CN CN201710792489.4A patent/CN107620979B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN107620979A (en) | 2018-01-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5528756B2 (en) | Tubular fuel injector for secondary fuel nozzle | |
| US10415832B2 (en) | Multi-swirler fuel/air mixer with centralized fuel injection | |
| EP2589877B1 (en) | Annular combustor with multipoint fuel injection arrangements | |
| US8511092B2 (en) | Dimpled/grooved face on a fuel injection nozzle body for flame stabilization and related method | |
| CN101793408B (en) | Combustor nozzle | |
| US7891190B2 (en) | Combustion chamber of a turbomachine | |
| US8528338B2 (en) | Method for operating an air-staged diffusion nozzle | |
| US20090077972A1 (en) | Toroidal ring manifold for secondary fuel nozzle of a dln gas turbine | |
| US20090199561A1 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| CN102213426A (en) | Segmented annular ring-manifold quaternary fuel distributor | |
| JPH07190372A (en) | Combustion equipment for gas turbine | |
| CN103822228A (en) | Fuel nozzle and method of assembling the same | |
| KR20190025497A (en) | Premixing fuel injectors and methods of use in gas turbine combustor | |
| CN113091094A (en) | Gas turbine combustor nozzle and method of premixing fuel and air in the nozzle | |
| CN105705863A (en) | Liquid fuel cartridge for a fuel nozzle | |
| US20170204785A1 (en) | Multi-functional fuel nozzle with a dual-orifice atomizer | |
| CN107631323B (en) | Nozzle for gas turbine | |
| CN107620979B (en) | Gas turbine | |
| CN107631324B (en) | Fuel-air mixer | |
| US20220268213A1 (en) | Dual pressure fuel nozzles | |
| CN111630320A (en) | Burner device and multi-tube once-through boiler device | |
| US11525403B2 (en) | Fuel nozzle with integrated metering and flashback system | |
| EP2613092B1 (en) | Combustor of a turbomachine | |
| CN108061308B (en) | Post-flame fuel injection device for gas turbine | |
| CN108224474B (en) | Back flame fuel injection device of 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 |