CN218269162U - Gas turbine rotational flow combustion device and gas turbine - Google Patents
Gas turbine rotational flow combustion device and gas turbine Download PDFInfo
- Publication number
- CN218269162U CN218269162U CN202221683247.4U CN202221683247U CN218269162U CN 218269162 U CN218269162 U CN 218269162U CN 202221683247 U CN202221683247 U CN 202221683247U CN 218269162 U CN218269162 U CN 218269162U
- Authority
- CN
- China
- Prior art keywords
- gas turbine
- rotational flow
- column
- upstream
- swirl
- 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
Images
Abstract
The application discloses gas turbine cyclone combustion device and gas turbine. The gas turbine rotational flow combustion device comprises a rotational flow channel first side wall, a rotational flow channel second side wall and rotational flow blades, wherein the number of the rotational flow blades is multiple, and the rotational flow blades are annularly arranged; the first side and the second side of the rotational flow blade are respectively provided with a first discharge hole and a second discharge hole; a first upstream flow disturbing column and a first downstream flow disturbing column are arranged on the first side of the swirl vane and are respectively positioned on two sides of the first discharge hole along the length direction of the swirl vane; and a second upstream turbulence column and a second downstream turbulence column are arranged on the second side of the swirl blade and are respectively positioned on two sides of the second discharge hole along the length direction of the swirl blade. The utility model provides a gas turbine whirl burner, fuel and air mix the homogeneity height in advance, and inside temperature distribution is even, can realize reducing the nitrogen oxide emission.
Description
Technical Field
The application relates to the technical field of gas turbines, in particular to a gas turbine cyclone combustion device and a gas turbine.
Background
The combustion pollution emission is receiving a lot of attention due to the increasing serious harm to human health and environment, and certain requirements are put forward for the pollution emission problem of the micro gas turbine. The combustion products of the micro gas turbine contain NOx (nitrogen oxides), which mainly contain NO and NO2, and technical measures are taken to reduce the NOx emission of the micro gas turbine as much as possible.
In a gas turbine, NOx is mainly thermal NOx generated by high combustion temperature, and the key point is to control the temperature in the combustion chamber to a low level (typically 1700K-1900K, which affects the combustion efficiency) and to make the temperature distribution in the combustion chamber uniform. This requires a very uniform fuel distribution in the combustion zone, minimizing the occurrence of localized high fuel concentrations. How to distribute the gas uniformly in the premixing section of the combustor becomes the key point of research in the industry.
SUMMERY OF THE UTILITY MODEL
The embodiment of the application provides a gas turbine rotational flow combustion device and a gas turbine, so as to reduce the emission of nitrogen oxides of the gas turbine.
On one hand, the embodiment of the application provides a gas turbine rotational flow combustion device, which comprises a rotational flow channel first side wall, a rotational flow channel second side wall and rotational flow blades, wherein the rotational flow channel first side wall and the rotational flow channel second side wall are arranged on two sides of the rotational flow blades respectively, the number of the rotational flow blades is multiple, and the rotational flow blades are annularly arranged; a feeding hole is formed in the first side wall of the rotational flow channel, a feeding channel is arranged in the rotational flow blade and communicated with the feeding hole, a first discharging hole and a second discharging hole are respectively formed in the first side and the second side of the rotational flow blade and communicated with the feeding channel; a first upstream turbulence column and a first downstream turbulence column are arranged on the first side of the swirl vane, and the first upstream turbulence column and the first downstream turbulence column are respectively positioned on two sides of the first discharge hole along the length direction of the swirl vane; and a second upstream turbulence column and a second downstream turbulence column are arranged on the second side of the swirl vane and are respectively positioned on two sides of the second discharge hole along the length direction of the swirl vane.
According to an aspect of an embodiment of the present application, the swirl vanes are bent in a length direction.
According to an aspect of the embodiment of the present application, the number of the first discharge holes is multiple, and the multiple first discharge holes are arranged along the width direction of the swirl vane; the number of the first upstream turbulence columns is multiple, and the multiple first upstream turbulence columns are arranged along the width direction of the swirl vanes; the number of the first downstream turbulence columns is plural, and the plural first downstream turbulence columns are arranged along the width direction of the swirl vane.
According to an aspect of the embodiment of the present application, the number of the second discharging holes is plural, and the plural second discharging holes are arranged along the width direction of the swirl vane; the number of the second upstream turbulence columns is multiple, and the multiple second upstream turbulence columns are arranged along the width direction of the swirl vanes; the number of the second downstream turbulence columns is multiple, and the multiple second downstream turbulence columns are arranged along the width direction of the swirl vanes.
According to an aspect of an embodiment of the present application, the first upstream turbulence column is shaped as a polygonal prism, a cylinder or an elliptic cylinder; the shapes of the first downstream turbulence column, the second upstream turbulence column and the second downstream turbulence column are the same as the shape of the first upstream turbulence column.
According to an aspect of an embodiment of the present application, the height of the first downstream turbulence column is H, and the height of the second downstream turbulence column is H, where H > H; the first discharging hole and the second discharging hole are equal in aperture and r, wherein H = 0.4-2.5 r, and H = 0.2-1.5 r.
According to an aspect of the embodiment of the present application, a bore diameter of the first discharging hole is R, and a projection width of the first downstream turbulence column in the width direction of the swirl vane is R, where R =1 to 1.5R; the distance between the first downstream turbulence column and the first discharge hole is L1, wherein L1= 3-8 r.
According to an aspect of the embodiment of the present application, the height of the first upstream turbulence column is H1, the height of the second upstream turbulence column is H1, and the aperture of the first discharging hole is equal to that of the second discharging hole and is r, where H1= 0.3-1 r.
According to an aspect of the embodiment of the present application, the aperture of the first discharging hole is R, and the width of the projection of the first upstream turbulence column in the width direction of the swirl vane is R1, where R1= 1-1.5R; the distance between the first upstream turbulence column and the first discharge hole is L2, wherein L2= 2-6 r.
In another aspect, the present embodiment provides a gas turbine including the gas turbine swirling combustion apparatus as described above.
The embodiment of the application provides a gas turbine cyclone burner, the air passage that fuel was spouted to a plurality of swirl blades and is constituteed each other by swirl blade's first discharge opening and second discharge opening, fuel distributes evenly in burner circumference, the setting of upper reaches vortex post and low reaches vortex post has improved air turbulence intensity, the fuel jet depth has been increased, make the fuel disperse to in bigger region, strengthen the mixture of adherence fuel and air, reduce near regional fuel concentration in the wall, improve and premix the homogeneity, thereby make the temperature distribution in the burner even, realize reducing the nitrogen oxide emission.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments of the present application will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a gas turbine cyclone combustion device provided by an embodiment of the present application;
FIG. 2 is a schematic diagram of a half-section structure of a gas turbine cyclone combustion device provided by an embodiment of the application;
FIG. 3 is a schematic cross-sectional structural view of a swirl vane of a gas turbine swirl burner provided by an embodiment of the present application;
FIG. 4 is a schematic cross-sectional structural view of a swirl vane of a gas turbine swirl burner provided by an embodiment of the present application;
FIG. 5 is a schematic structural diagram of a swirl vane of a gas turbine swirl combustion device provided by an embodiment of the application at a certain viewing angle;
FIG. 6 is a schematic structural diagram of a turbulence column of a gas turbine swirl flow combustion device provided by an embodiment of the application;
FIG. 7 is a schematic structural diagram of a turbulence column of a gas turbine swirl flow combustion device provided by an embodiment of the application;
FIG. 8 is a schematic structural diagram of a turbulence column of a gas turbine swirl flow combustion device provided by an embodiment of the application;
FIG. 9 is a schematic structural diagram of a turbulence column of a gas turbine swirl flow combustion device according to an embodiment of the present application.
Reference numerals:
1-a first side wall of a rotational flow channel, 2-a second side wall of the rotational flow channel, 3-rotational flow blades, 4-a second discharge hole, 5-a feed channel, 6-a second downstream turbulence column, 7-a second upstream turbulence column, 8-a first downstream turbulence column, 9-a first upstream turbulence column, 10-a first discharge hole, 11-a feed inlet, and 12-an expansion section.
Detailed Description
Embodiments of the present application will be described in further detail below with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the application and are not intended to limit the scope of the application, i.e., the application is not limited to the described embodiments.
In the description of the present application, it is noted that, unless otherwise indicated, the terms "first" and "second," etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; "plurality" means two or more; the terms "inner," "top," "bottom," and the like, as used herein, refer to an orientation or positional relationship based on that shown in the drawings for ease of description and simplicity of description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present application.
Referring to fig. 1, 2 and 3, an embodiment of the present application provides a gas turbine swirl flow combustion apparatus, which includes a swirl passage first sidewall 1, a swirl passage second sidewall 2 and swirl vanes 3. The first side wall 1 and the second side wall 2 of the swirl channel are respectively arranged at two sides of the swirl blade 3, namely the swirl blade 3 is connected between the first side wall 1 and the second side wall 2 of the swirl channel. The swirl channel second side wall 2 has an outlet and an expansion section 12 is formed at the outlet to expand the flame. Swirl vane 3 is a plurality of, and a plurality of swirl vane 3 are the annular and arrange. A plurality of swirl vanes 3 may be provided around the outlet of the swirl channel second side wall 2.
The first side wall 1 of the rotational flow channel is provided with a feed inlet 11, the rotational flow blades 3 are internally provided with feed channels 5, the feed channels 5 are communicated with the feed inlet 11, the first side and the second side of each rotational flow blade 3 are respectively provided with a first discharge hole 10 and a second discharge hole 4, and the first discharge hole 10 and the second discharge hole 4 are respectively communicated with the feed channels 5. The fuel enters the feeding channel 5 inside the swirl vane 3 from the feeding hole 11, is sprayed out from the first discharging hole 10 and the second discharging hole 4 of the swirl vane 3 and vertically flows into the air, so that the fuel is ensured to be uniformly distributed in the circumferential direction of the combustion device.
A first upstream turbulence column 9 and a first downstream turbulence column 8 are arranged on the first side of the swirl blade 3, and the first upstream turbulence column 9 and the first downstream turbulence column 8 are respectively positioned on two sides of the first discharge hole 10 along the length direction of the swirl blade 3; and a second upstream turbulence column 7 and a second downstream turbulence column 6 are arranged on the second side of the swirl blade 3, and the second upstream turbulence column 7 and the second downstream turbulence column 6 are respectively positioned on two sides of the second discharge hole 4 along the length direction of the swirl blade 3. The length direction of the swirl vanes 3 is from the bottom end to the top end. The arrangement of the first upstream turbulence column 9 and the second upstream turbulence column 7 can increase the turbulence of the incoming air, create turbulence, and improve the uniformity of the mixing of the fuel and the air. The first downstream turbulence column 8 and the second downstream turbulence column 6 are located on the flow track of the fuel flowing along the wall, as shown in fig. 5, the fuel flowing along the wall collides with the fuel and bypasses and turns over, thereby generating vortex, increasing the depth of fuel jet, wherein the depth of jet can reach the middle area of an air channel formed by a plurality of swirl blades 3, namely the fuel can be dispersed in a larger space area without approaching the wall surface of the swirl blades 3, improving the distribution uniformity of the fuel, and further increasing the turbulence after the fuel and the air collide with the fuel, and enhancing the mixing effect.
In this embodiment, the fuel is by swirl blade 3's first discharge opening 10 and second discharge opening 4 blowout to the air passage that a plurality of swirl blade 3 are constituteed each other, the fuel distributes evenly in burner circumference, the setting up of upper reaches turbulence post and low reaches turbulence post has improved air turbulence intensity, fuel jet depth has been increased, make the fuel disperse to in bigger region, strengthen the mixture of adherence fuel and air, reduce near regional fuel concentration in the wall, improve and mix the homogeneity in advance, thereby make temperature distribution even in the burner, realize reducing the nitrogen oxide emission. In addition, the upstream turbulence column and the downstream turbulence column do not excessively shield the air channel, so that the influence on the main air in the air channel of the combustion device is small, the air flow can be kept stable, and the pressure loss is not increased.
As a possible embodiment, the swirl vanes 3 are bent in the longitudinal direction. The first side of the swirl vane 3 is a pressure surface (concave surface), and the second side is a suction surface (convex surface). The tips of the swirl blades 3 are deflected by an angle α to the pressure surface, thereby generating a swirl, where α = 10-20 °.
In practical application, whether the turbulence column is arranged on the side surface of the swirl vane 3 can be determined according to specific conditions of the combustion device, for example, when the pressure surface of the swirl vane 3 is well mixed with the fuel and the air, the turbulence column can be arranged only on the suction surface. Whether the turbulence column is arranged at the upstream and the downstream of the discharge hole can be determined according to the specific situation of the combustion device, for example, only the upstream or the downstream turbulence column can be arranged.
In specific implementation, the number of the first discharging holes 10 is multiple, and the multiple first discharging holes 10 are arranged along the width direction of the swirl vanes 3, so that the uniform mixing degree of the fuel in the circumferential direction and the radial direction of the combustion device is improved. The width direction of the swirl vanes 3 is perpendicular to the length direction. The number of the first discharging holes 10 may be 2 to 5, and a plurality of the first discharging holes 10 may be arranged parallel to the axis of the feeding passage 5. The increase of the number of the first discharge holes 10 reduces the flow velocity of a single hole, so that after the fuel airflow is ejected from the first discharge holes 10, the jet depth cannot reach the middle area of the air channel, but tends to be close to the wall surface of the swirl vane 3, as shown in fig. 4. The arrangement of the first downstream turbulence column 8 and the first upstream turbulence column 9 enables the fuel gas flow flowing adherent to each other to generate vortex, the depth of the fuel jet is increased, and the middle area of the air channel can be reached. The number of the first upstream turbulence columns 9 is plural, the plural first upstream turbulence columns 9 are arranged along the width direction of the swirl vane 3, and the plural first upstream turbulence columns 9 may be parallel to the plural first discharge holes 10. The number of the first downstream turbulence columns 8 is plural, the plural first downstream turbulence columns 8 are arranged in the width direction of the swirl blade 3, and the plural first downstream turbulence columns 8 may be parallel to the plural first discharge holes 10.
In specific implementation, the number of the second discharge holes 4 is multiple, and the multiple second discharge holes 4 are arranged along the width direction of the swirl vanes 3, so that the uniform mixing degree of the fuel in the circumferential direction and the radial direction of the combustion device is improved. Similarly, the number of the second discharging holes 4 may be 2 to 5, and a plurality of the second discharging holes 4 may be arranged parallel to the axis of the feeding passage 5. The number of the second upstream turbulence columns 7 is plural, the plural second upstream turbulence columns 7 are arranged along the width direction of the swirl vane 3, and the plural second upstream turbulence columns 7 may be parallel to the plural second discharge holes 4. The number of the second downstream turbulence columns 6 is plural, the plural second downstream turbulence columns 6 are arranged along the width direction of the swirl vane 3, and the plural second downstream turbulence columns 6 may be parallel to the plural second discharge holes 4.
As a possible embodiment, in conjunction with fig. 6, the shape of the first upstream turbulence column 9 is a polygonal prism, such as a triangular prism, a quadrangular prism, or the like, or the shape of the first upstream turbulence column 9 is a cylinder or an elliptic cylinder. The shape of the first downstream turbulence column 8, the second upstream turbulence column 7, the second downstream turbulence column 6 may be the same as the shape of the first upstream turbulence column 9. During specific implementation, the turbulence column can be integrated with the swirl blade 3, namely, the side surface of the swirl blade 3 is provided with a protrusion which is used as the turbulence column.
Referring to fig. 7, 8 and 9, when the downstream turbulence columns are specifically provided, considering that the fuel injected from the first discharge holes 10 on the pressure surface of the swirl vanes 3 is closer to the wall surface of the swirl vanes 3 under the action of air impact, and the fuel injected from the second discharge holes 4 on the suction surface of the swirl vanes 3 is farther from the wall surface of the swirl vanes 3, the height of the first downstream turbulence columns 8 on the pressure surface of the swirl vanes 3 is set to be H, and the height of the second downstream turbulence columns 6 on the suction surface of the swirl vanes 3 is set to be H, so that H > H, and therefore, the turbulence columns not only can play the above-mentioned role, but also can simplify the structure. In order to avoid completely blocking the fuel jet flow by making the height of the turbulent flow column too high, if the diameters of the first discharge hole 10 and the second discharge hole 4 are equal and r, H =0.4 to 2.5r, and H =0.2 to 1.5r.
Specifically, when the width of the first downstream turbulence column 8 projected in the width direction of the swirl blade 3 is set to R, R =1 to 1.5R. When the distance between the wall surface of the first downstream turbulence column 8 and the axis of the first discharge hole 10 is set to L1, L1=3 to 8r. This makes it possible to more effectively exhibit the function of the turbulent flow column. The width of the second downstream turbulence column 6 and the distance between the second downstream turbulence column 6 and the second discharge hole 4 can be referred to the first downstream turbulence column 8.
When the upstream turbulence column is specifically arranged, if the height of the first upstream turbulence column 9 is set to H1 and the height of the second upstream turbulence column 7 is set to H1, then H1=0.3 to 1r. When the width of the first upstream turbulence column 9 projected in the width direction of the swirl blade 3 is R1, R1=1 to 1.5R. The distance between the first upstream turbulence column 9 and the first discharge hole 10 is L2, and then L2=2 to 6r. Thereby accommodating the effect of the upstream turbulence column. The width of the second upstream turbulence column 7 and the distance between the second upstream turbulence column 7 and the second discharge hole 4 can be referred to the first upstream turbulence column 9.
It can be understood that the arrangement of the turbulence columns can be considered together with other parts of the gas turbine, and the shapes, the sizes and the positions are taken as references, so that the design is reasonably carried out, the oscillation frequency is avoided, and the normal work of the gas turbine is ensured.
The embodiment of the application also provides a gas turbine, which comprises the gas turbine swirl combustion device of the embodiment, the discharge amount of nitrogen oxides of the gas turbine is lower, the structure is simpler, the operation is stable and reliable, and the gas turbine swirl combustion device is safe and environment-friendly.
It should be understood by those skilled in the art that the foregoing is only illustrative of the present invention, and is not intended to limit the scope of the present invention. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. The gas turbine rotational flow combustion device is characterized by comprising a rotational flow channel first side wall, a rotational flow channel second side wall and rotational flow blades, wherein the rotational flow channel first side wall and the rotational flow channel second side wall are arranged on two sides of the rotational flow blades respectively, the rotational flow blades are multiple, and the rotational flow blades are annularly arranged;
a feeding hole is formed in the first side wall of the rotational flow channel, a feeding channel is arranged in the rotational flow blade and communicated with the feeding hole, a first discharging hole and a second discharging hole are respectively formed in the first side and the second side of the rotational flow blade and communicated with the feeding channel;
a first upstream turbulence column and a first downstream turbulence column are arranged on the first side of the swirl vane, and the first upstream turbulence column and the first downstream turbulence column are respectively positioned on two sides of the first discharge hole along the length direction of the swirl vane; and a second upstream turbulence column and a second downstream turbulence column are arranged on the second side of the swirl blade and are respectively positioned on two sides of the second discharge hole along the length direction of the swirl blade.
2. The gas turbine cyclone burner of claim 1, wherein the swirl vanes are bent in a length direction.
3. The gas turbine cyclone burner of claim 1, wherein the first discharge holes are plural, and the plural first discharge holes are arranged in the width direction of the cyclone blade;
the number of the first upstream turbulence columns is multiple, and the multiple first upstream turbulence columns are arranged along the width direction of the swirl vanes;
the number of the first downstream turbulence columns is plural, and the plural first downstream turbulence columns are arranged along the width direction of the swirl vane.
4. The gas turbine cyclone burner of claim 1, wherein the second discharge holes are plural, and the plural second discharge holes are arranged in the width direction of the cyclone blade;
the number of the second upstream turbulence columns is multiple, and the second upstream turbulence columns are arranged along the width direction of the swirl vane;
the second downstream turbulence columns are multiple and are arranged along the width direction of the swirl vanes.
5. The gas turbine cyclone combustion device of claim 1 wherein the first upstream turbulence column is in the shape of a polygonal prism, cylinder or elliptical cylinder;
the shapes of the first downstream turbulence column, the second upstream turbulence column and the second downstream turbulence column are the same as the shape of the first upstream turbulence column.
6. The gas turbine cyclonic combustion apparatus of claim 1, wherein the first downstream turbulence column has a height H and the second downstream turbulence column has a height H, wherein H > H;
the first discharging hole and the second discharging hole are equal in aperture and r, wherein H = 0.4-2.5 r, and H = 0.2-1.5 r.
7. The gas turbine swirling combustion apparatus according to claim 1 or 6, wherein the aperture of the first discharge hole is R, and the width of the first downstream turbulence column projected in the width direction of the swirling vane is R, where R =1 to 1.5R;
the distance between the first downstream turbulence column and the first discharge hole is L1, wherein L1= 3-8 r.
8. The gas turbine swirling combustion device according to claim 1, wherein the height of the first upstream turbulence column is H1, the height of the second upstream turbulence column is H1, the aperture of the first discharge hole and the aperture of the second discharge hole are equal and r, and H1= 0.3-1 r.
9. The gas turbine swirling combustion apparatus according to claim 1 or 8, wherein the aperture of the first discharge hole is R, and the width of the first upstream turbulence column projected in the width direction of the swirling vane is R1, where R1= 1-1.5R;
the distance between the first upstream turbulence column and the first discharge hole is L2, wherein L2= 2-6 r.
10. A gas turbine comprising the gas turbine cyclone combustion apparatus according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221683247.4U CN218269162U (en) | 2022-06-30 | 2022-06-30 | Gas turbine rotational flow combustion device and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221683247.4U CN218269162U (en) | 2022-06-30 | 2022-06-30 | Gas turbine rotational flow combustion device and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218269162U true CN218269162U (en) | 2023-01-10 |
Family
ID=84759549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221683247.4U Active CN218269162U (en) | 2022-06-30 | 2022-06-30 | Gas turbine rotational flow combustion device and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218269162U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116293801A (en) * | 2023-03-06 | 2023-06-23 | 哈尔滨工程大学 | Premixing grade fuel and air reinforced mixing structure and shaft type cyclone |
-
2022
- 2022-06-30 CN CN202221683247.4U patent/CN218269162U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116293801A (en) * | 2023-03-06 | 2023-06-23 | 哈尔滨工程大学 | Premixing grade fuel and air reinforced mixing structure and shaft type cyclone |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6880340B2 (en) | Combustor with turbulence producing device | |
| JP5746091B2 (en) | Robe swirler | |
| JP4959620B2 (en) | Combustor and fuel supply method for combustor | |
| EP0500256B1 (en) | Air fuel mixer for gas turbine combustor | |
| US4265615A (en) | Fuel injection system for low emission burners | |
| KR101586214B1 (en) | Axial swirler | |
| US4590769A (en) | High-performance burner construction | |
| JP2013190201A (en) | System for enhancing mixing in multi-tube fuel nozzle | |
| US4941617A (en) | Airblast fuel nozzle | |
| CN109539314A (en) | A kind of novel radial swirler with wave blade | |
| CN106016364B (en) | A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) | |
| JP2019536976A (en) | Swirler, combustor assembly and gas turbine with improved fuel / air mixing | |
| CN218269162U (en) | Gas turbine rotational flow combustion device and gas turbine | |
| JP2010060189A (en) | Burner, and method for supplying fuel and method for modifying fuel nozzle in burner | |
| JP4066658B2 (en) | Gas turbine combustor, gas turbine combustor premixing device, and gas turbine combustor premixing method | |
| CN205825112U (en) | A kind of two points of swirl-flow premixed burner noz(zle)s of gas turbine dry low pollution combustor unit | |
| CN110440290B (en) | Micro-mixing nozzle for gas turbine | |
| CN113464982A (en) | Center staged combustion chamber based on self-excitation sweep oscillation fuel nozzle | |
| CN104791847A (en) | Low-rotational-flow multi-nozzle combustor structure applicable to low-pollution combustion chamber of gas turbine | |
| CN115451431B (en) | Fuel nozzle premixing system for combustion chamber of gas turbine | |
| CN107525096B (en) | Multi-tube late lean injector | |
| CN215175236U (en) | Center staged combustion chamber based on self-excitation sweep oscillation fuel nozzle | |
| CN113719859A (en) | Combustor and premixed air inlet type backflow annular combustion chamber | |
| JPH09170716A (en) | Fuel premixing device and gas turbine combustion device | |
| JP2020122629A (en) | Burner, and combustor and gas turbine with the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |