A convection vortex wall-cooled burner

Abstract

The present invention relates to the technical field of burners, and discloses a convection vortex wall-cooled burner, comprising a main shell, a combustion chamber is arranged inside the main shell; a front shell, an air inlet cavity is arranged inside the front shell; a first swirler, a first combustion cavity is arranged inside the first swirler; an igniter, the igniter extends into the first combustion cavity; a second swirler, an air inlet passage connected to the air inlet cavity is formed between the outer side of the second swirler and the inner wall of the main shell, a second combustion cavity is arranged inside the second swirler, and the second combustion cavity is respectively connected to the first combustion cavity and the combustion chamber; an air swirler, the air swirler is provided with a through hole connected to the combustion chamber, a rear end air inlet hole of the air swirler, the axis of the air inlet hole respectively forms an angle with the axial direction and radial direction of the air swirler, and the axis of the plurality of air inlet holes are in the same inclination direction relative to the axial direction and radial direction of the air swirler. The present invention has good cooling effect and high combustion efficiency.

Description

Technical Field

[0001] The invention relates to the technical field of burners, and in particular to a convection vortex wall-cooled burner. Background Art

[0002] Gas turbines have a series of advantages such as fast start-up, high power density, good maneuverability and high reliability. As one of the three major components of a gas turbine, the combustion chamber is not only the component that directly affects the performance of the gas turbine, but also the component with the highest average temperature of the gas turbine. Fuel and air burn in the combustion chamber, and the combustion temperature is usually above 2000℃. However, the conventional temperature resistance of the metal materials currently selected for the combustion chamber is around 1300℃. Therefore, due to the temperature resistance limit of metal materials, cooling technology must be used to protect the combustion chamber, so as to reduce the working environment temperature of the combustion chamber and extend the working life of the combustion chamber.

[0003] At present, in order to improve the temperature resistance of the combustion chamber wall and extend the life of the combustion chamber, the cooling methods adopted by the gas turbine combustion chamber mainly include air film cooling, divergent cooling, impact divergent combined cooling, and layer cooling. The basic principle is to introduce a part of the air from the outer annular cavity of the combustion chamber into the flame tube to form an air film on the inner wall of the flame tube. This part of the gas cools the flame tube wall on the one hand and isolates the hot combustion gas on the other hand. In order to obtain a better cooling effect, a large amount of air must be introduced, but the air entering the combustion chamber is extremely limited. If a large amount of air is used for cooling, it will inevitably reduce the amount of air for organizing combustion, which is in conflict with the development of modern advanced gas turbines.

[0004] At present, in order to obtain high power, high cycle efficiency and high combustion efficiency, gas turbines often require a large amount of air to enter the flame tube from the head of the combustion chamber, participate in and organize the combustion field, control the flame temperature, increase the temperature ratio of the gas turbine, thereby improving the overall performance of the gas turbine, and even reducing NOx emissions. From this, it can be seen that, on the one hand, the design of advanced gas turbines requires more air to participate in combustion, which inevitably reduces the air used for cooling; on the other hand, higher gas temperatures bring further challenges to the cooling of the combustion chamber, requiring more air to cool and protect the combustion chamber. This contradiction in air distribution makes it difficult for existing cooling methods to meet the cooling needs of advanced gas turbines. Therefore, there is an urgent need for a new combustion chamber structure with more suitable air distribution and better cooling effect. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a convection vortex wall-cooled burner with high combustion efficiency and good cooling effect, which can solve the problem of distribution of cooling air and combustion air in the combustion chamber.

[0006] In order to achieve the above object, the present invention provides a convection vortex wall-cooled burner, comprising:

[0007] A main shell, wherein a combustion chamber is provided inside the main shell;

[0008] A front shell, the front shell is arranged at the front end of the main shell, and an air intake cavity is arranged inside the front shell;

[0009] A first swirler, the first swirler is arranged in the air inlet cavity, and a first combustion cavity is arranged inside the first swirler;

[0010] an igniter, the igniter being disposed at a front end of the first swirler and extending into the first combustion chamber;

[0011] a second swirler, the second swirler being arranged at the front end of the combustion chamber, an air intake passage communicating with the air intake chamber being formed between the outer side of the second swirler and the inner wall of the main shell, a second combustion chamber being arranged inside the second swirler, and the second combustion chamber being communicated with the first combustion chamber and the combustion chamber respectively;

[0012] An air swirler, wherein the air swirler is arranged at the rear end of the main shell, a through hole connected to the combustion chamber is provided in the middle of the air swirler, and a plurality of air inlet holes connected to the combustion chamber are provided at the rear end of the air swirler, the plurality of air inlet holes are evenly distributed along the circumference of the air swirler, the axes of the air inlet holes respectively form angles with the axial direction and radial direction of the air swirler, and the axes of the plurality of air inlet holes are in the same inclination direction relative to the axial direction and radial direction of the air swirler.

[0013] As a preferred embodiment of the present invention, the angle between the axis of the air inlet hole and the axial direction of the air cyclone is 30° to 60°, and the angle between the axis of the air inlet hole and the radial direction of the air cyclone is 30° to 60°.

[0014] As a preferred solution of the present invention, the air cyclone is further provided with a cooling channel, one end of the cooling channel is communicated with the side of the air inlet hole, and the other end of the cooling channel is communicated with the side of the through hole.

[0015] As a preferred solution of the present invention, the diameter of the air inlet hole gradually decreases from the rear end to the front end.

[0016] As a preferred embodiment of the present invention, the first swirler is provided with a first air inlet, a first fuel inlet and a plurality of first swirl blades, the plurality of first swirl blades are respectively arranged around the first combustion chamber, the first air inlet is connected to the air intake chamber, the second swirler is provided with a second air inlet, a second fuel inlet and a plurality of second swirl blades, the plurality of swirl blades are respectively arranged around the second combustion chamber, and the inclination direction of the axis of the air intake hole relative to the radial direction of the air swirler is opposite to the spiral direction of the first swirl blades and the second swirl blades.

[0017] As a preferred embodiment of the present invention, there is a gap between the outer side of the second swirler and the inner wall of the main shell, the outer side of the second swirler is provided with a flange connected to the inner wall of the main shell, the flange is provided with an air inlet connected to the air inlet cavity, the gap and the air inlet form the air inlet channel, and the number of the air inlets is equal to the number of the first swirling blades.

[0018] As a preferred solution of the present invention, the second air inlet is arranged at the rear end of the second cyclone.

[0019] As a preferred embodiment of the present invention, it also includes a fuel chamber shell, which is arranged at the front end of the front shell, and a partition plate is provided inside the fuel chamber shell. The partition plate divides the interior of the fuel chamber shell into a first fuel chamber and a second fuel chamber, the first fuel chamber is connected to the first fuel inlet, and the second fuel chamber is connected to the second fuel inlet.

[0020] As a preferred embodiment of the present invention, it also includes a front flange of the casing, and the front flange of the casing is provided with a first fuel joint and a second fuel joint, the first fuel joint is connected to the first fuel cavity, and the second fuel joint is connected to the second fuel cavity.

[0021] The embodiment of the present invention is a convection vortex wall-cooled burner. Compared with the prior art, its beneficial effects are as follows: fuel is respectively delivered to the first swirler and the second swirler to realize staged combustion of fuel. The first swirler and the second swirler promote premixed combustion of fuel and air, thereby ensuring combustion efficiency, controlling the temperature of the combustion field, avoiding the generation of local high-temperature areas, and reducing the emission of thermal NOx; during the propagation of high-temperature combustion gas in the combustion chamber, due to the presence of a cooling air film on the inner wall of the main shell, the high-temperature combustion gas after fuel combustion is prevented from directly contacting the main shell, thereby achieving the purpose of cooling the main shell; the cooling air film is used to form a cooling air film at the main shell. All the air in the membrane will enter the first cyclone and the second cyclone to participate in the combustion. The air used for cooling is not allocated separately, but all the air is first used for cooling and then all participates in the combustion, which ensures the cooling effect while ensuring the organization of the combustion field, can improve the overall cycle efficiency of the gas turbine, and solves the problem of the distribution of cooling air and combustion air in the combustion chamber. The cooling effect is good and the combustion efficiency is high. In addition, the temperature of the air used for cooling will inevitably be increased under the action of high-temperature combustion gas. When this part of the heated air is mixed with the fuel under the first cyclone, the high-temperature mixed air is conducive to ignition, ensuring the success of ignition. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of a convection vortex wall-cooled burner provided by the present invention;

[0023] Figure 2 yes Figure 1 Left view of;

[0024] Figure 3 yes Figure 1 A left side view of the second cyclone in FIG.

[0025] Figure 4 yes Figure 1 A cross-sectional view of the second cyclone in FIG.

[0026] Figure 5 yes Figure 1 A left side view of the air cyclone in FIG.

[0027] Figure 6 yes Figure 5 AA cross-sectional view of the air cyclone in FIG.

[0028] In the figure, 1, main shell; 11, combustion chamber; 2, front shell; 21, air inlet cavity; 3, first swirler; 31, first combustion chamber; 4, igniter; 5, second swirler; 51, second combustion chamber; 52, flange; 53, air inlet; 54, second air inlet; 55, second fuel inlet; 56, air inlet channel; 6, air swirler; 61, through hole; 62, air inlet hole; 63, cooling channel; 7, fuel chamber shell; 71, partition plate; 72, first fuel chamber; 73, second fuel chamber; 8, casing front flange; 81, first fuel joint; 82, second fuel joint. DETAILED DESCRIPTION

[0029] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0030] In the description of the present invention, it should be understood that the present invention adopts the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like to indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0031] like Figure 1-6 As shown, the preferred embodiment of the present invention provides a convection vortex wall-cooled burner, comprising

[0032] A main housing 1, wherein a combustion chamber 11 is provided inside the main housing 1;

[0033] A front housing 2, which is disposed at the front end of the main housing 1, and an air inlet cavity 21 is disposed inside the front housing 2;

[0034] A first swirler 3, the first swirler 3 is arranged in the air inlet cavity 21, and a first combustion cavity 31 is arranged inside the first swirler 3;

[0035] An igniter 4, which is disposed at the front end of the first swirler 3 and extends into the first combustion chamber 31;

[0036] The second swirler 5 is disposed at the front end of the combustion chamber 11. An air intake passage 56 communicating with the air intake chamber 21 is formed between the outer side of the second swirler 5 and the inner wall of the main shell 1. A second combustion chamber 51 is disposed inside the second swirler 5. The second combustion chamber 51 is communicated with the first combustion chamber 31 and the combustion chamber 11 respectively. The space (capacity) of the second combustion chamber 51 is larger than that of the first combustion chamber 31, so that the flame can expand and spread, and the high-temperature combustion gas after combustion enters the combustion chamber 11 and spreads;

[0037] The air swirler 6 is arranged at the rear end of the main housing 1. A through hole 61 communicating with the combustion chamber is arranged in the middle of the air swirler 6. A plurality of air inlet holes 62 communicating with the combustion chamber 11 are arranged at the rear end of the air swirler 6. The plurality of air inlet holes 62 are evenly distributed along the circumference of the air swirler 6. The axes of the air inlet holes 62 respectively form angles with the axial direction and the radial direction of the air swirler 6. The axes of the plurality of air inlet holes 62 are in the same inclination direction relative to the axial direction and the radial direction of the air swirler 6. See Figure 1 and Figure 5 There is an angle a1 between the axis of the air inlet hole 62 and the axial direction of the air cyclone 6, which specifically refers to the angle between the axis of the air inlet hole 62 and the axial plane of the air cyclone 6. There is an angle a2 between the axis of the air inlet hole 62 and the radial direction of the air cyclone 6 (the diameter of the air cyclone 6 passing through the front end center of the air inlet hole 62), which specifically refers to the angle between the axis of the air inlet hole 62 and the radial plane passing through the front end center of the air inlet hole 62. The axial direction of the air cyclone 6 is the Y axis, the vertical direction is the Z axis, and the direction perpendicular to the Y axis and the Z axis is the X axis. The axial plane of the air cyclone 6 is the XY plane, the radial plane of the air cyclone 6 is the plane determined by the diameter of the air cyclone 6 and the Y axis, and the radial plane passing through the center of the front end of the air inlet hole 62 is the plane determined by the diameter of the center of the front end of the air inlet hole 62 and the Y axis.

[0038] The working principle of this embodiment is as follows: since the rear end of the air inlet 62 gradually extends outward in a clockwise or counterclockwise direction to the front end of the air inlet 62, when the outside air enters the combustion chamber 11 through the air inlet 62, it will rotate and propagate from the rear end to the front end of the combustion chamber 11 in a clockwise or counterclockwise direction. When the air rotates and propagates, under the action of centrifugal force, the air will cling to the inner wall of the main shell 1 to form a cooling air film. When the air propagates and contacts the second swirler 5, most of the air will enter the second swirler 5 and be mixed with the fuel entering the second swirler 5 before being transported to the second swirler 5. Second combustion chamber 51, a small part of the air will be transported to the air intake chamber 21 through the air inlet 53, and then enter the first swirler 3 to be mixed with the fuel entering the first swirler 3 and transported to the first combustion chamber 31, the igniter 4 ignites the fuel in the first combustion chamber 31, the flame propagates to the second combustion chamber 51, ignites the fuel in the second combustion chamber 51, and the high-temperature combustion gas after combustion enters the combustion chamber 11 and propagates from the front end to the rear end. Since the fuel swirls through the swirler, the high-temperature combustion gas will rotate when it propagates, and the high-temperature combustion gas finally enters the turbine through the through hole 61 of the air swirler 6 to perform work.

[0039] The fuel is transported to the first swirler 3 and the second swirler 5 respectively to realize staged combustion of the fuel. The first swirler 3 and the second swirler 5 promote premixed combustion of the fuel and air, ensure combustion efficiency, control the temperature of the combustion field, avoid the generation of local high-temperature areas, and reduce the emission of thermal NOx. During the propagation of the high-temperature combustion gas in the combustion chamber 11, due to the presence of a cooling air film on the inner wall of the main shell 1, the high-temperature combustion gas after the fuel combustion is blocked from directly contacting the main shell 1, thereby achieving the purpose of cooling the main shell 1. The air used to form the cooling air film at the main shell 1 will all enter the first swirler 3 and the second swirler 5. The second cyclone 5 participates in the combustion, and the air used for cooling is not allocated separately. Instead, all the air is first used for cooling and then all participates in the combustion, which ensures the cooling effect while ensuring the organization of the combustion field, can improve the overall cycle efficiency of the gas turbine, and solves the problem of distribution of cooling air and combustion air in the combustion chamber 11. The cooling effect is good and the combustion efficiency is high. In addition, the temperature of the air used for cooling is bound to be increased under the action of high-temperature combustion gas. When this part of the heated air is mixed with the fuel under the first cyclone 3, the high-temperature mixed air is conducive to ignition, thereby ensuring the success of ignition.

[0040] Exemplarily, the angle between the axis of the air inlet hole 62 and the axial direction of the air cyclone 6 is 30° to 60°, and the angle between the axis of the air inlet hole 62 and the radial direction of the air cyclone 6 is 30° to 60°. This inclination angle range allows the air to have a greater speed and centrifugal force after passing through the air inlet hole 62, ensuring that the air can rotate and transmit in close contact with the inner wall of the main shell 1.

[0041] Exemplarily, the first swirler 3 is provided with a first air inlet, a first fuel inlet and a plurality of first swirl blades, the plurality of first swirl blades are respectively arranged around the first combustion chamber 31, the first air inlet is connected to the air intake chamber 21, and the working principle of the first swirler 3 is as follows: air enters the interior of the first swirler 3 through the first air inlet, and the fuel enters the interior of the first swirler 3 through the first fuel inlet, the air and fuel entering the first swirler 3 are respectively swirled through the first swirl blades, and are mixed and transported to the first combustion chamber 31; the second swirler 5 is provided with a second air inlet 54, a second fuel inlet 55 and a plurality of second swirl blades, the plurality of swirl blades are respectively arranged around the second combustion chamber 51, and the working principle of the second swirler 5 is the same as that of the first swirler 3, and the air enters the interior of the second swirler 5 through the second air inlet 54 The fuel enters the second swirler 5 through the second fuel inlet. The air and fuel entering the second swirler 5 are swirled through the second swirl blades respectively and are mixed and transported to the second combustion chamber 51. The inclination direction of the axis of the air inlet hole relative to the radial direction of the air swirler is opposite to the spiral direction of the first swirl blade and the second swirl blade respectively. In this embodiment, looking from the rear end to the front end of the air swirler 6, the axis of the air inlet hole 62 is inclined clockwise relative to the radial direction of the air swirler, so that the air rotates clockwise after passing through the air inlet hole 62, while the rotation direction of the first swirl blade and the second swirl blade is counterclockwise, so that the high-temperature combustion gas after combustion rotates counterclockwise in the combustion chamber 11, and the cooling air rotates clockwise in the combustion chamber 11, which improves the convective heat transfer efficiency and promotes the cooling effect.

[0042] Exemplarily, there is a gap between the outer side of the second swirler 5 and the inner wall of the main shell 1. The outer side of the second swirler 5 is provided with a flange 52 connected to the inner wall of the main shell 1. The flange 52 is provided with an air inlet 53 connected to the air inlet cavity 21. The gap and the air inlet 53 form an air inlet channel 56. The number of the air inlet 53 is equal to the number of the first swirl blades, so as to match the fuel and air entering the first swirler 3 and promote mixing between the two.

[0043] Exemplarily, the second air inlet 54 is disposed at the rear end of the second swirler 5. After the air enters the combustion chamber 11 through the air inlet 62, it is transported from the rear end to the front end in a vortex manner. When the air contacts the rear end of the second swirler 5, most of the air will directly enter the second swirler 5 through the second air inlet 54, ensuring that the fuel entering the second swirler 5 is fully burned after contacting with sufficient air.

[0044] Exemplarily, the present embodiment also includes a fuel chamber shell 7, which is disposed at the front end of the front shell 2. A partition plate 71 is disposed inside the fuel chamber shell 7. The partition plate 71 divides the interior of the fuel chamber shell 7 into a first fuel chamber 72 and a second fuel chamber 73. The first fuel chamber 72 is connected to the first fuel inlet, and the second fuel chamber 73 is connected to the second fuel inlet 55, so as to facilitate staged combustion of the fuel. In the present embodiment, the first fuel inlet is disposed at the front end of the first swirler 3 to facilitate the connection of the first fuel chamber 72, and the second fuel inlet 55 is disposed at the front end of the second swirler 5. A fuel cavity is disposed between the front end surfaces of the front shell 2 and the second swirler 5. A fuel channel is disposed inside the first swirl blade, one end of the fuel channel is connected to the second fuel chamber 73, and the other end of the fuel channel is connected to the fuel cavity, so that the second fuel chamber 73 is connected to the second fuel inlet 55.

[0045] Exemplarily, the present embodiment also includes a front flange 8 of the casing, and the front flange 8 of the casing is provided with a first fuel connector 81 and a second fuel connector 82. The first fuel connector 81 is connected to the first fuel chamber 72 to provide fuel to the first fuel chamber 72, and the second fuel connector 82 is connected to the second fuel chamber 73 to provide fuel to the second fuel chamber 73. In the present embodiment, the igniter 4 is installed in the middle of the front flange 8 of the casing, and the igniter 4 extends into the first combustion chamber 31 through the fuel chamber housing 7. Two first fuel connectors 81 and second fuel connectors 82 are respectively provided, and the first fuel connector 81 and the second fuel connector 82 are arranged around the igniter 4. This arrangement facilitates assembly and connection.

[0046] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principles of the present invention. These improvements and substitutions should also be regarded as the scope of protection of the present invention.

Claims

1. A convection vortex wall-cooled burner, characterized in that: include A main shell, wherein a combustion chamber is provided inside the main shell; A front shell, the front shell is arranged at the front end of the main shell, and an air intake cavity is arranged inside the front shell; A first swirler, the first swirler is arranged in the air inlet cavity, and a first combustion cavity is arranged inside the first swirler; an igniter, the igniter being disposed at a front end of the first swirler and extending into the first combustion chamber; a second swirler, the second swirler being arranged at the front end of the combustion chamber, an air intake passage communicating with the air intake chamber being formed between the outer side of the second swirler and the inner wall of the main shell, a second combustion chamber being arranged inside the second swirler, the second combustion chamber being communicated with the first combustion chamber and the combustion chamber respectively, and a space of the second combustion chamber being larger than a space of the first combustion chamber; An air swirler, wherein the air swirler is arranged at the rear end of the main shell, a through hole connected to the combustion chamber is provided in the middle of the air swirler, a plurality of air inlet holes connected to the combustion chamber are provided at the rear end of the air swirler, the plurality of air inlet holes are evenly distributed along the circumference of the air swirler, the axes of the air inlet holes respectively form angles with the axial direction and radial direction of the air swirler, and the axes of the plurality of air inlet holes are inclination direction consistent with the axial direction and radial direction of the air swirler, and the air inlet holes gradually extend outward from the rear end to the front end.

2. The convection vortex wall-cooled burner according to claim 1, characterized in that: The included angle between the axis of the air inlet hole and the axial direction of the air cyclone is 30° to 60°, and the included angle between the axis of the air inlet hole and the radial direction of the air cyclone is 30° to 60°.

3. The convection vortex wall-cooled burner according to claim 1, characterized in that: The air cyclone is further provided with a cooling channel, one end of which is communicated with the side of the air inlet hole, and the other end of which is communicated with the side of the through hole.

4. The convection vortex wall-cooled burner according to claim 1, characterized in that: The diameter of the air inlet gradually decreases from the rear end to the front end.

5. The convection vortex wall-cooled burner according to claim 1, characterized in that: The first swirler is provided with a first air inlet, a first fuel inlet and a plurality of first swirl blades, the plurality of first swirl blades are respectively arranged around the first combustion chamber, the first air inlet is connected to the air intake chamber, the second swirler is provided with a second air inlet, a second fuel inlet and a plurality of second swirl blades, the plurality of swirl blades are respectively arranged around the second combustion chamber, and the inclination direction of the axis of the air intake hole relative to the radial direction of the air swirler is opposite to the spiral direction of the first swirl blade and the second swirl blade.

6. The convection vortex wall-cooled burner according to claim 5, characterized in that: There is a gap between the outer side of the second swirler and the inner wall of the main shell. The outer side of the second swirler is provided with a flange connected to the inner wall of the main shell. The flange is provided with an air inlet connected to the air inlet cavity. The gap and the air inlet form the air inlet channel. The number of the air inlets is equal to the number of the first swirling blades.

7. The convection vortex wall-cooled burner according to claim 5, characterized in that: The second air inlet is arranged at the rear end of the second cyclone.

8. The convection vortex wall-cooled burner according to claim 5, characterized in that: It also includes a fuel chamber shell, which is arranged at the front end of the front shell, and a partition plate is provided inside the fuel chamber shell. The partition plate divides the interior of the fuel chamber shell into a first fuel chamber and a second fuel chamber, the first fuel chamber is connected to the first fuel inlet, and the second fuel chamber is connected to the second fuel inlet.

9. The convection vortex wall-cooled burner according to claim 8, characterized in that: It also includes a front flange of the casing, and the front flange of the casing is provided with a first fuel joint and a second fuel joint, the first fuel joint is connected to the first fuel cavity, and the second fuel joint is connected to the second fuel cavity.

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