Combustion chamber nozzle structure and working method thereof

Abstract

The present invention relates to the technical field of gas turbines, and in particular to a combustion chamber nozzle structure and a working method thereof. The combustion chamber nozzle structure comprises: a first tube body, a second tube body, a third tube body, a fourth tube body and a fifth tube body arranged coaxially; wherein, a secondary air supply flow channel is formed between the third tube body and the second tube body along the radial interval; a secondary hydrogen supply flow channel is formed between the fifth tube body and the fourth tube body along the radial interval; an annular cavity is formed between the fourth tube body and the third tube body along the radial interval; a mixing cavity is formed downstream of the annular cavity along the axial direction; a second air jet hole is provided on the third tube body; a second hydrogen jet hole is provided on the fourth tube body; a plurality of main swirl blades are provided in the middle and downstream of the mixing cavity; each main swirl blade is provided with a third air jet hole and a third hydrogen jet hole. The combustion chamber nozzle structure provided by the present invention can avoid the occurrence of coking and improve the mixing and combustion efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a combustion chamber nozzle structure and a working method thereof. Background Art

[0002] Currently, light-duty gas turbines are widely used as power plants in aviation, marine, and other fields, while heavy-duty gas turbines are used in power generation. During gas turbine operation, liquid fuels often suffer from problems such as incomplete combustion, coking, and high pollutant emissions, but their risk is relatively low, so they are mostly used in aviation and marine fields. Gaseous fuels, on the other hand, are more dangerous and require more stringent storage conditions, so they are often used in heavy-duty gas turbines for power generation. In recent years, environmental protection requirements have become increasingly stringent both domestically and internationally, and gas turbines are facing severe challenges. Hydrogen, due to its clean, environmentally friendly, and sustainable advantages, has rapidly developed and is currently widely used in transportation, chemical industry, and other fields. If hydrogen energy is applied to gas turbine combustion, it can significantly reduce pollutant emissions.

[0003] However, during operation, the liquid fuel in the combustion chamber nozzle of a gas turbine that mixes hydrogen with liquid fuel is prone to coking, and the mixing and combustion efficiency is low. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defects in the existing gas turbine combustion chamber nozzle of the prior art that the liquid fuel is prone to coking during operation and has low mixing and combustion efficiency, thereby providing a combustion chamber nozzle structure and its working method that can avoid the coking phenomenon and improve the mixing and combustion efficiency.

[0005] In order to solve the above technical problems, the present invention provides a combustion chamber nozzle structure, comprising:

[0006] A first tube body, a second tube body, a third tube body, a fourth tube body and a fifth tube body are coaxially arranged;

[0007] A secondary air supply channel is formed radially between the inner circumferential wall of the third tube body and the outer circumferential wall of the second tube body; a secondary hydrogen supply channel is formed radially between the inner circumferential wall of the fifth tube body and the outer circumferential wall of the fourth tube body; and an annular cavity is formed radially between the inner circumferential wall of the fourth tube body and the outer circumferential wall of the third tube body.

[0008] The annular cavity forms a mixing cavity downstream along the axial direction;

[0009] The third tube body is provided with a second air jet hole, one end of which is connected to the secondary air supply channel and the other end is connected to the mixing chamber; the fourth tube body is provided with a second hydrogen jet hole, one end of which is connected to the secondary hydrogen supply channel and the other end is connected to the mixing chamber;

[0010] A plurality of main swirl blades are provided in the middle and downstream of the mixing chamber, and the plurality of main swirl blades are suitable for forming a main swirler; each of the main swirl blades is provided with a third air jet hole and a third hydrogen jet hole, and the third air jet hole is suitable for introducing the air in the secondary air supply channel into the mixing chamber, and the third hydrogen jet hole is suitable for introducing the hydrogen in the secondary hydrogen supply channel into the mixing chamber.

[0011] Optionally, the angle between the central axis of the second air jet hole and the central axis of the combustion chamber nozzle structure and the angle between the central axis of the second hydrogen jet hole and the central axis of the combustion chamber nozzle structure are both β, and the value range of β is 30°≤β≤90°.

[0012] Optionally, each of the primary swirl blades includes an inner cavity wall and an outer cavity wall; the inner cavity wall is suitable for enclosing an inner cavity, the inner cavity is connected to the secondary air supply channel via an air delivery hole, and the air delivery hole is provided on the third tube body; the outer cavity wall is suitable for enclosing an outer cavity, the outer cavity is connected to the secondary hydrogen supply channel via a hydrogen delivery hole, and the hydrogen delivery hole is provided on the fourth tube body; and the outer cavity and the inner cavity are not connected to each other;

[0013] The third air jet holes are evenly and densely opened on the inner cavity wall, one end of the third air jet holes is connected to the inner chamber, and the other end is connected to the mixing chamber; the third hydrogen jet holes are evenly and densely opened on the outer cavity wall, one end of the third hydrogen jet holes is connected to the outer chamber, and the other end is connected to the mixing chamber.

[0014] Optionally, the inner peripheral wall of the first tube body is surrounded to form a primary hydrogen supply channel; a first hydrogen jet hole is provided at the end of the first tube body, and the first hydrogen jet hole is connected to the primary hydrogen supply channel;

[0015] A primary air supply channel is formed radially between the inner circumferential wall of the second tube body and the outer circumferential wall of the first tube body; a plurality of secondary swirl blades are provided at the end of the primary air supply channel, and the plurality of secondary swirl blades are suitable for forming a secondary swirler.

[0016] Optionally, there are multiple first hydrogen jet holes, one of which is coaxially arranged with the central axis of the combustion chamber nozzle structure, and the remaining first hydrogen jet holes are arranged around the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the remaining first hydrogen jet holes and the central axis of the combustion chamber nozzle structure is α, and the value range of α is 30°≤α≤60°.

[0017] Optionally, a plurality of liquid fuel supply pipes are provided upstream of the annular cavity in the axial direction, and the plurality of liquid fuel supply pipes are evenly arranged circumferentially around the third tube body; one end of the liquid fuel supply pipe is axially connected to the mixing cavity;

[0018] A pressure nozzle is provided at one end of the liquid fuel supply pipe close to the mixing chamber, and the pressure nozzle is suitable for atomizing the liquid fuel.

[0019] Optionally, the combustion chamber nozzle structure also includes a support plate, which is connected to the end of the liquid fuel supply pipe, and one radial side of the support plate is connected to the third tube body, and the other side is connected to the fourth tube body; a plurality of first air jet holes are provided on the support plate, and the first air jet holes are evenly distributed on the support plate, for supplying most of the air required for liquid fuel combustion.

[0020] The working method of the combustion chamber nozzle structure provided by the present invention is applied to the combustion chamber nozzle structure as described above, and the working method of the combustion chamber nozzle structure includes:

[0021] A hydrogen source supplies diffused hydrogen to the primary hydrogen supply channel, causing the diffused hydrogen to be ejected through the first hydrogen ejection hole. Simultaneously, a compressor supplies diffused air to the primary air supply channel, causing the diffused air to generate a swirl after passing through the secondary swirler, creating a recirculation zone at the nozzle outlet and quickly and evenly mixing with the diffused hydrogen. The mixed air is ignited by the igniter, causing it to quickly form diffuse combustion, thereby forming a stable ignition source.

[0022] Premixed hydrogen is supplied from a hydrogen source to the secondary hydrogen supply flow channel, and premixed air is supplied to the secondary air supply flow channel through a compressor, so that part of the premixed hydrogen is directly ejected into the mixing chamber through the second hydrogen jet hole, and the remaining premixed hydrogen enters the main swirl blade through the hydrogen delivery hole and then is ejected into the mixing chamber through the third hydrogen jet hole. At the same time, part of the premixed air is directly ejected into the mixing chamber through the second air jet hole, and the remaining premixed air enters the main swirl blade through the air delivery hole and then is ejected into the mixing chamber through the third air jet hole.

[0023] Liquid fuel is supplied from a liquid fuel source into the liquid fuel supply pipe, so that the liquid fuel is atomized into droplets under the action of the pressure nozzle, and is quickly mixed with premixed hydrogen and premixed air in the mixing chamber, and generates a swirl when flowing through the main swirler. After being transmitted from the outlet of the mixing chamber, it is quickly ignited by the diffusion flame. With the continuous supply of fresh fuel and air, diffusion combustion and premixed combustion can continue.

[0024] Optionally, the amount of the premixed hydrogen in the mixing chamber is always less than 10% of the total amount of the premixed hydrogen and the liquid fuel in the mixing chamber.

[0025] Optionally, the hydrogen flow rate and / or the liquid fuel flow rate are adjustable, and the local equivalence ratio and the mixing ratio of hydrogen and liquid fuel are changed by adjusting the hydrogen flow rate and the liquid fuel flow rate.

[0026] The technical solution of the present invention has the following advantages:

[0027] 1. The combustion chamber nozzle structure provided by the present invention has a plurality of second air jet holes evenly and densely formed on the third tube body, a plurality of second hydrogen jet holes evenly and densely formed on the fourth tube body, and a plurality of third air jet holes and a plurality of third hydrogen jet holes evenly and densely formed on the main swirl blades. Air is continuously ejected into the mixing chamber through the second air jet holes and the third air jet holes, and hydrogen is continuously ejected into the mixing chamber through the second hydrogen jet holes and the third hydrogen jet holes. This not only prevents liquid fuel from contacting high-temperature wall surfaces in a high-temperature environment, thereby avoiding the occurrence of coking, but also enables the ejected air and hydrogen to be premixed with the atomized liquid fuel in the mixing chamber, thereby improving the mixing efficiency and further improving the combustion efficiency.

[0028] 2. In the combustion chamber nozzle structure provided by the present invention, the angle between the central axis of the second air jet hole and the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the second hydrogen jet hole and the central axis of the combustion chamber nozzle structure are both β, and the value range of the angle β is 30°≤β≤90°. On the one hand, it ensures that the jet penetration of the second air jet hole and / or the second hydrogen jet hole is at a high level, thereby improving the mixing efficiency. On the other hand, it avoids the reversal of the jet direction, enhances the fluidity of the fuel, and enhances the mixing effect.

[0029] 3. In the combustion chamber nozzle structure provided by the present invention, one of the first hydrogen jet holes is coaxially arranged with the central axis of the combustion chamber nozzle structure, thereby being able to directly inject hydrogen to increase the average flow rate, thereby drawing the surrounding gas toward the center to improve the mixing effect. The remaining first hydrogen jet holes are arranged around the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the remaining first hydrogen jet holes and the central axis of the combustion chamber nozzle structure is α, and the value range of the angle α satisfies 30°≤α≤60°. On the one hand, it can enhance the collision mixing effect of the hydrogen jet and air, improve the jet penetration, and thus enhance the mixing effect. On the other hand, it can avoid deceleration of another fluid mixed with the hydrogen jet, enhance the fluidity of the fluid, and thus enhance the mixing effect.

[0030] 4. The combustion chamber nozzle structure provided by the present invention is provided with a pressure nozzle at one end of the liquid fuel supply pipe close to the mixing chamber. One end of the pressure nozzle is connected to the liquid fuel supply pipe, and the other end is connected to the mixing chamber, so that the liquid fuel is atomized by the pressure nozzle to form atomized droplets. The atomized liquid fuel can absorb the heat generated by the diffusion combustion of hydrogen after being discharged from the outlet of the mixing chamber, which can make the atomized droplets absorb heat and evaporate, which is beneficial to the mixing and full combustion of liquid fuel and improve combustion efficiency. At the same time, it can significantly reduce the temperature during hydrogen diffusion combustion, thereby reducing the generation of thermal nitrogen oxides.

[0031] 5. The operating method of the combustion chamber nozzle structure provided by the present invention not only prevents liquid fuel from contacting high-temperature wall surfaces in a high-temperature environment, thereby avoiding the occurrence of coking, but also allows the jetted hydrogen and air to be premixed with the atomized liquid fuel and the air ejected from the first air jet hole in the mixing chamber, thereby improving the mixing effect and facilitating sufficient combustion and combustion temperature control. During this period, the amount of premixed hydrogen in the mixing chamber must always be less than 10% of the total amount of premixed hydrogen and liquid fuel in the mixing chamber, thereby ensuring that the flame front always remains in the normal position during liquid fuel combustion and preventing excessive hydrogen from causing the flame front to move upstream of the nozzle and causing backfire. At the same time, the lower hydrogen amount can maintain a lean burn combustion state, thereby controlling the flame surface temperature and reducing the production of thermal nitrogen oxides, thereby achieving efficient mixing and combustion of hydrogen and liquid fuel. During this period, the local equivalence ratio and the mixing ratio of hydrogen and liquid fuel can also be changed by adjusting the hydrogen flow rate and liquid fuel flow rate to facilitate the control of pollutant emissions and combustion stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0033] Figure 1 It is a schematic diagram of the overall structure of the combustion chamber nozzle structure of the present invention;

[0034] Figure 2 Schematic diagram of the cross-sectional structure of the combustion chamber nozzle structure of the present invention;

[0035] Figure 3 for Figure 2 Enlarged view of point A in the middle;

[0036] Figure 4 for Figure 2 Schematic diagram of the cross-sectional structure of the middle BB section;

[0037] Figure 5 for Figure 2 Enlarged view of point C in the middle;

[0038] Figure 6 for Figure 1 Left view of .

[0039] Description of reference numerals:

[0040] 10. First tube body; 100. Primary hydrogen supply channel; 101. First hydrogen jet hole;

[0041] 20. Second tube body; 200. Primary air supply channel;

[0042] 30. Third tube; 300. Secondary air supply channel; 301. Second air jet hole; 302. Air delivery hole;

[0043] 40, fourth tube body; 400, annular cavity; 4000, mixing cavity; 401, second hydrogen jet hole; 402, hydrogen delivery hole;

[0044] 50. Fifth tube body; 500. Secondary hydrogen supply channel;

[0045] 60, main swirl blade; 601, third air jet hole; 602, third hydrogen jet hole; 61, inner cavity wall; 610, inner chamber; 62, outer cavity wall; 620, outer chamber;

[0046] 70. Auxiliary swirl blades;

[0047] 80. Liquid fuel supply pipe;

[0048] 90. Support plate; 901. First air jet hole. DETAILED DESCRIPTION

[0049] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0050] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0051] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0052] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0053] Example 1

[0054] Combine Figures 1-6 As shown, this embodiment provides a combustion chamber nozzle structure, including:

[0055] A first tube body 10, a second tube body 20, a third tube body 30, a fourth tube body 40 and a fifth tube body 50 are coaxially arranged;

[0056] A secondary air supply channel 300 is formed radially between the inner circumferential wall of the third tube body 30 and the outer circumferential wall of the second tube body 20; a secondary hydrogen supply channel 500 is formed radially between the inner circumferential wall of the fifth tube body 50 and the outer circumferential wall of the fourth tube body 40; and an annular cavity 400 is formed radially between the inner circumferential wall of the fourth tube body 40 and the outer circumferential wall of the third tube body 30.

[0057] The annular cavity 400 forms a mixing cavity 4000 downstream in the axial direction;

[0058] The third tube body 30 is provided with a second air jet hole 301, one end of which is connected to the secondary air supply channel 300 and the other end is connected to the mixing chamber 4000; the fourth tube body 40 is provided with a second hydrogen jet hole 401, one end of which is connected to the secondary hydrogen supply channel 500 and the other end is connected to the mixing chamber 4000;

[0059] A plurality of main swirl blades 60 are provided in the middle and downstream of the mixing chamber 4000, and the plurality of main swirl blades 60 are suitable for forming a main swirler; each of the main swirl blades 60 is provided with a third air jet hole 601 and a third hydrogen jet hole 602, and the third air jet hole 601 is suitable for introducing the air in the secondary air supply channel 300 into the mixing chamber 4000, and the third hydrogen jet hole 602 is suitable for introducing the hydrogen in the secondary hydrogen supply channel 500 into the mixing chamber 4000.

[0060] Please note that, see Figure 1 As shown, the combustion chamber nozzle structure includes a coaxially arranged first tube body 10, a second tube body 20, a third tube body 30, a fourth tube body 40 and a fifth tube body 50, and any adjacent two of the first tube body 10, the second tube body 20, the third tube body 30, the fourth tube body 40 and the fifth tube body 50 are arranged radially spaced apart. Figure 1 and Figure 2As shown, a secondary air supply channel 300 is formed radially between the inner circumferential wall of the third tube body 30 and the outer circumferential wall of the second tube body 20, and the end of the secondary air supply channel 300 is closed; a secondary hydrogen supply channel 500 is formed radially between the inner circumferential wall of the fifth tube body 50 and the outer circumferential wall of the fourth tube body 40, and the end of the secondary hydrogen supply channel 500 is closed; an annular cavity 400 is formed radially between the inner circumferential wall of the fourth tube body 40 and the outer circumferential wall of the third tube body 30, and the upstream of the annular cavity 400 is suitable for accommodating a liquid fuel supply pipe 80, and the liquid fuel supply pipe 80 is suitable for supplying liquid fuel to the mixing cavity 4000; a mixing cavity 4000 is formed axially downstream of the annular cavity 400, and the mixing cavity 4000 is connected to the liquid fuel supply pipe 80, and the mixing cavity 4000 is suitable for mixing atomized liquid fuel, air and hydrogen.

[0061] It should be noted that, see Figure 2 As shown, the third tube body 30 is uniformly and densely provided with a plurality of second air jet holes 301, through which the secondary air supply channel 300 is connected to the mixing chamber 4000, so that the air is continuously ejected from the secondary air supply channel 300 through the second air jet holes 301 into the mixing chamber 4000; the fourth tube body 40 is uniformly and densely provided with a plurality of second hydrogen jet holes 401, through which the secondary hydrogen supply channel 500 is connected to the mixing chamber 4000, so that the hydrogen is continuously ejected from the secondary hydrogen supply channel 500 into In the mixing chamber 4000, the continuous jetting of the second air jet hole 301 and the second hydrogen jet hole 401 can, on the one hand, prevent the atomized liquid fuel from directly contacting the wall of the mixing chamber 4000, thereby avoiding coking on the wall of the mixing chamber 4000 under a high temperature environment; on the other hand, the air ejected by the second air jet hole 301, the hydrogen ejected by the second hydrogen jet hole 401 and the atomized liquid fuel, as well as the air ejected by the first air jet hole 901 can be premixed in the mixing chamber 4000, thereby improving the mixing effect, contributing to full combustion and combustion temperature control, and improving combustion efficiency.

[0062] It should be noted that, see Figure 2As shown, a plurality of main swirl blades 60 are provided in the middle and downstream of the mixing chamber 4000, and the plurality of main swirl blades 60 are suitable for forming a main swirler; each of the main swirl blades 60 is provided with a third air jet hole 601 and a third hydrogen jet hole 602, and the air in the secondary air supply channel 300 is introduced into the mixing chamber 4000 through the third air jet hole 601, and the hydrogen in the secondary hydrogen supply channel 500 is introduced into the mixing chamber through the third hydrogen jet hole 602. 4000, on the one hand, it can prevent the atomized liquid fuel from directly contacting the main swirl blade 60, thereby avoiding coking on the surface of the main swirl blade 60 under high temperature environment; on the other hand, it can make the hydrogen ejected by the third hydrogen jet hole 602 and the air ejected by the third air jet hole 601 generate swirl in the mixing chamber 4000, so that the atomized liquid fuel, air and hydrogen are quickly mixed in the mixing chamber 4000, further improving the mixing efficiency and then improving the combustion efficiency.

[0063] Optionally, there are eight main swirl blades 60 , and the eight main swirl blades 60 form a main swirler, so that the gas entering the mixing chamber 4000 generates a swirl.

[0064] In this embodiment, by uniformly and densely opening a plurality of second air jet holes 301 on the third tube body 30, and uniformly and densely opening a plurality of second hydrogen jet holes 401 on the fourth tube body 40, and by uniformly and densely opening a plurality of third air jet holes 601 and a plurality of third hydrogen jet holes 602 on the main swirl blade 60, air is continuously ejected into the mixing chamber 4000 through the second air jet holes 301 and the third air jet holes 601, and hydrogen is continuously ejected into the mixing chamber 4000 through the second hydrogen jet holes 401 and the third hydrogen jet holes 602. This not only prevents the liquid fuel from contacting the high-temperature wall surface in a high-temperature environment, thereby avoiding the occurrence of coking, but also enables the ejected air and hydrogen to be premixed with the atomized liquid fuel in the mixing chamber 4000, thereby improving the mixing efficiency and further improving the combustion efficiency.

[0065] Specifically, the angle between the central axis of the second air jet hole 301 and the central axis of the combustion chamber nozzle structure and the angle between the central axis of the second hydrogen jet hole 401 and the central axis of the combustion chamber nozzle structure are both β, and the value range of β is 30°≤β≤90°.

[0066] Please note that, see Figure 3As shown, the angle between the central axis of the second air jet hole 301 and the central axis of the combustion chamber nozzle structure and the angle between the central axis of the second hydrogen jet hole 401 and the central axis of the combustion chamber nozzle structure are both β. The angle β cannot be too small, otherwise it will easily lead to low jet penetration of the second air jet hole 301 and / or the second hydrogen jet hole 401, which is not conducive to mixing. Therefore, the angle β should satisfy β≥30°; however, the angle β cannot be too large, otherwise it will cause the jet direction to be reversed, which is not conducive to mixing or fuel flow. Therefore, the angle β should satisfy β≤90°; in this embodiment, the value range of the angle β is 30°≤β≤90°, which on the one hand ensures that the jet penetration of the second air jet hole 301 and / or the second hydrogen jet hole 401 is at a high level and improves the mixing efficiency, and on the other hand avoids the reversal of the jet direction, enhances the fluidity of the fuel, and enhances the mixing effect.

[0067] Optionally, the angle β is set to 90°, which is beneficial to improving the mixing effect of premixed hydrogen and air.

[0068] Specifically, each of the primary swirl blades 60 includes an inner cavity wall 61 and an outer cavity wall 62; the inner cavity wall 61 is adapted to enclose an inner cavity 610, the inner cavity 610 being connected to the secondary air supply channel 300 via an air delivery hole 302, the air delivery hole 302 being provided on the third tube body 30; the outer cavity wall 62 is adapted to enclose an outer cavity 620, the outer cavity 620 being connected to the secondary hydrogen supply channel 500 via a hydrogen delivery hole 402, the hydrogen delivery hole 402 being provided on the fourth tube body 40; and the outer cavity 620 and the inner cavity 610 are not connected to each other;

[0069] The third air jet holes 601 are evenly and densely opened on the inner cavity wall 61, one end of the third air jet holes 601 is connected to the inner chamber 610, and the other end is connected to the mixing chamber 4000; the third hydrogen jet holes 602 are evenly and densely opened on the outer cavity wall 62, one end of the third hydrogen jet holes 602 is connected to the outer chamber 620, and the other end is connected to the mixing chamber 4000.

[0070] Please note that, see Figure 4 and Figure 6 As shown, due to the limitation of the annular or fan-shaped cross-sectional structure and its size, the number of the first air jet holes 901 on the support plate 90 gradually decreases from the fourth tube body 40 to the third tube body 30 in the radial direction. Figure 4As shown, the inner chamber 610 is provided on the side of the main swirl blade 60 close to the third tube 30, and the inner chamber 610 is connected to the secondary air supply channel 300 through the air delivery hole 302, thereby increasing the air volume in the inner area of ​​the mixing chamber 4000. At the same time, the outer chamber 620 is provided on the side of the main swirl blade 60 close to the fourth tube 40, and the outer chamber 620 is connected to the secondary hydrogen supply channel 500 through the hydrogen delivery hole 402, thereby balancing the air volume of the first air jet hole 901 on the support plate 90, improving the uniformity of air distribution in the mixing chamber 4000, improving the mixing effect, optimizing the distribution of the combustible mixture equivalence ratio in the mixing chamber 4000, and facilitating the complete combustion of the fuel. Figure 2 As shown, the second air jet hole 301 is provided on the third tube body 30, and the second hydrogen jet hole 401 is provided on the fourth tube body 40. This increases the air volume in the inner region of the mixing chamber 4000, further balancing the air volume in the first air jet hole 901 on the support plate 90, improving the uniformity of air distribution in the mixing chamber 4000, enhancing the mixing effect, and optimizing the distribution of the combustible mixture equivalence ratio in the mixing chamber 4000, thereby facilitating sufficient combustion of the fuel. The inner region refers to the region radially adjacent to the third tube body 30 within the mixing chamber 4000.

[0071] Please note that, see Figure 4 As shown, the third air jet hole 601 is opened on the inner cavity wall 61, one end of the third air jet hole 601 is connected to the inner chamber 610, and the other end is connected to the mixing chamber 4000, thereby providing the air required for combustion into the mixing chamber 4000; the third hydrogen jet hole 602 is opened on the outer cavity wall 62, one end of the third hydrogen jet hole 602 is connected to the outer chamber 620, and the other end is connected to the mixing chamber 4000, thereby providing the hydrogen required for combustion into the mixing chamber 4000; the third air jet holes 601 are evenly and densely arranged on the inner cavity wall 61, and the third hydrogen jet holes 602 are evenly and densely arranged on the outer cavity wall 62, so that the gas jet is ejected from the densely distributed holes, thereby preventing the atomized liquid fuel from directly contacting the main swirl blade 60, avoiding the coking phenomenon on the blade surface under high temperature environment.

[0072] Specifically, the inner peripheral wall of the first tube body 10 surrounds and forms a primary hydrogen supply channel 100; a first hydrogen jet hole 101 is provided at the end of the first tube body 10, and the first hydrogen jet hole 101 is connected to the primary hydrogen supply channel 100;

[0073] A primary air supply channel 200 is formed radially between the inner circumferential wall of the second tube body 20 and the outer circumferential wall of the first tube body 10; a plurality of secondary swirl blades 70 are provided at the end of the primary air supply channel 200, and the plurality of secondary swirl blades 70 are suitable for forming a secondary swirler.

[0074] Specifically, there are multiple first hydrogen jet holes 101, one of which is coaxially arranged with the central axis of the combustion chamber nozzle structure, and the remaining first hydrogen jet holes 101 are arranged around the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the remaining first hydrogen jet holes 101 and the central axis of the combustion chamber nozzle structure is α, and the value range of α is 30°≤α≤60°.

[0075] Please note that, see Figure 5 As shown, the end of the first tube 10 is provided with a plurality of first hydrogen jet holes 101, which are suitable for connecting the primary hydrogen supply channel 100 with the outside of the combustion chamber nozzle structure. One of the first hydrogen jet holes 101 is coaxially arranged with the central axis of the combustion chamber nozzle structure, so that hydrogen can be directly injected to increase the average flow rate, thereby attracting the surrounding gas to the center to improve the mixing effect. The remaining first hydrogen jet holes 101 are arranged around the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the remaining first hydrogen jet holes 101 and the central axis of the combustion chamber nozzle structure is α. The angle α cannot be too small, otherwise it is easy to cause the radial component velocity of the hydrogen jet to be too small and the axial component velocity to be too large, which is not conducive to collision and mixing with air, and the jet penetration is low, which is not conducive to mixing. Therefore, the angle α must satisfy α≥30°; the angle α cannot be too large, otherwise it is easy to cause the radial component velocity of the hydrogen jet to be too large and the axial component velocity to be too large. If the radial flow velocity is too small, the other fluid mixed with it will be decelerated, which is not conducive to flow and easily weakens the mixing effect. Therefore, the angle α needs to satisfy α≤60°; by making the value range of the angle α between the central axis of the remaining first hydrogen jet hole 101 and the central axis of the combustion chamber nozzle structure satisfy 30°≤α≤60°, on the one hand, the collision mixing effect of the hydrogen jet and the air can be enhanced, the jet penetration can be improved, thereby enhancing the mixing effect; on the other hand, the deceleration of the other fluid mixed with the hydrogen jet can be avoided, the fluidity of the fluid can be enhanced, thereby enhancing the mixing effect.

[0076] Optionally, the angle α is set to 60°, which is beneficial to improving the mixing effect of diffused hydrogen and air.

[0077] Specifically, a plurality of liquid fuel supply pipes 80 are provided upstream of the annular cavity 400 in the axial direction. The plurality of liquid fuel supply pipes 80 are evenly arranged circumferentially around the third tube body 30 ; one end of the liquid fuel supply pipe 80 is axially connected to the mixing cavity 4000 ;

[0078] A pressure nozzle is provided at one end of the liquid fuel supply pipe 80 close to the mixing chamber 4000 , and the pressure nozzle is suitable for atomizing the liquid fuel.

[0079] It should be noted that, in specific implementations, the pressure nozzle (not shown) is generally a finished part and operates in essentially the same manner. Therefore, in this embodiment, only the location of the pressure nozzle is specifically defined, and the specific structure of the pressure nozzle is not further described. Since hydrogen diffusion combustion cannot adjust the ratio of hydrogen to air, it is impossible to reduce the flame temperature. However, the flame temperature of hydrogen combustion is significantly higher than the temperature at which thermal nitrogen oxides are generated. In this embodiment, a pressure nozzle is provided at one end of the liquid fuel supply pipe 80 near the mixing chamber 4000. One end of the pressure nozzle communicates with the liquid fuel supply pipe 80, and the other end communicates with the mixing chamber 4000. This allows the liquid fuel to be atomized by the pressure nozzle to form atomized droplets. The atomized liquid fuel, upon exiting the outlet of the mixing chamber 4000, absorbs the heat generated by the hydrogen diffusion combustion, causing the atomized droplets to absorb heat and evaporate, thereby facilitating liquid fuel mixing and sufficient combustion, improving combustion efficiency, and significantly reducing the temperature during hydrogen diffusion combustion, thereby reducing the generation of thermal nitrogen oxides.

[0080] Optionally, eight liquid fuel supply pipes 80 are provided upstream of the annular cavity 400 in the axial direction. The eight liquid fuel supply pipes 80 are evenly arranged circumferentially around the third tube body 30 , and the pressure nozzle is provided at the outlet of each liquid fuel supply pipe 80 .

[0081] Specifically, the combustion chamber nozzle structure also includes a support plate 90, which is connected to the end of the liquid fuel supply pipe 80. One radial side of the support plate 90 is connected to the third tube body 30, and the other side is connected to the fourth tube body 40; a plurality of first air jet holes 901 are provided on the support plate 90, and the first air jet holes 901 are evenly distributed on the support plate 90, for supplying most of the air required for liquid fuel combustion.

[0082] Example 2

[0083] This embodiment provides a method for operating a combustion chamber nozzle structure, which is applied to the combustion chamber nozzle structure described above. The method for operating the combustion chamber nozzle structure includes:

[0084] A hydrogen source supplies diffused hydrogen to the primary hydrogen supply channel 100, causing the diffused hydrogen to be ejected through the first hydrogen ejection hole 101. Simultaneously, a compressor supplies diffused air to the primary air supply channel 200, causing the diffused air to generate a swirl after passing through the secondary swirler, creating a recirculation zone at the nozzle outlet and rapidly and evenly mixing with the diffused hydrogen. The mixed air is ignited by the igniter, causing rapid diffusion combustion to form a stable ignition source.

[0085] Premixed hydrogen is supplied from a hydrogen source to the secondary hydrogen supply channel 500, and premixed air is supplied to the secondary air supply channel 300 through a compressor, so that part of the premixed hydrogen is directly ejected into the mixing chamber 4000 through the second hydrogen jet hole 401, and the remaining premixed hydrogen enters the main swirl blade 60 through the hydrogen delivery hole 402, and then is ejected into the mixing chamber 4000 through the third hydrogen jet hole 602. At the same time, part of the premixed air is directly ejected into the mixing chamber 4000 through the second air jet hole 301, and the remaining premixed air enters the main swirl blade 60 through the air delivery hole 302, and then is ejected into the mixing chamber 4000 through the third air jet hole 601.

[0086] Liquid fuel is supplied from a liquid fuel source into the liquid fuel supply pipe 80, so that the liquid fuel is atomized into droplets under the action of the pressure nozzle, and is rapidly mixed with the premixed hydrogen and premixed air in the mixing chamber 4000 to form a mixed gas, and a swirl is generated when flowing through the main swirler. After the mixed gas is discharged from the outlet of the mixing chamber 4000, it is quickly ignited by the diffusion flame. With the continuous supply of fresh fuel and air, diffusion combustion and premixed combustion can continue.

[0087] Please note that, see Figure 2 and Figure 5 As shown, the inner peripheral wall of the first tube body 10 is surrounded to form a primary hydrogen supply channel 100; a first hydrogen jet hole 101 is provided at the end of the first tube body 10, thereby forming a hydrogen diffusion combustion zone at the central axis of the combustion chamber nozzle structure to serve as a stable ignition source, thereby continuously igniting the mixture of atomized liquid fuel, air and hydrogen; at the same time, hydrogen diffusion combustion will not backfire, thereby ensuring the safety of the nozzle.

[0088] Specifically, the amount of the premixed hydrogen in the mixing chamber 4000 is always less than 10% of the total amount of the premixed hydrogen and the liquid fuel in the mixing chamber 4000 .

[0089] It should be noted that the amount of premixed hydrogen in the mixing chamber 4000 must always be less than 10% of the total amount of premixed hydrogen and liquid fuel in the mixing chamber 4000, so as to ensure that the flame front always remains in the normal position during liquid fuel combustion, and prevent the flame front from moving upstream of the nozzle due to excessive hydrogen content, thereby avoiding backfire. Even if signs of backfire occur under certain unstable conditions, due to the presence of a large number of atomized droplets in the fuel, the combustion rate of the liquid fuel is much slower than that of hydrogen, and is far lower than the flow rate of the fuel in the mixing chamber 4000, so backfire will not occur. At the same time, the lower amount of hydrogen can keep it in a lean combustion state to control the flame surface temperature and reduce the production of thermal nitrogen oxides, thereby achieving efficient mixing and combustion of hydrogen and liquid fuel.

[0090] Specifically, the hydrogen flow rate and / or the liquid fuel flow rate are adjustable, and the local equivalence ratio and the mixing ratio of hydrogen and liquid fuel are changed by adjusting the hydrogen flow rate and the liquid fuel flow rate.

[0091] The working method of the combustion chamber nozzle structure of the present invention is described below in a unified manner:

[0092] In the hydrogen diffusion combustion zone, the diffused hydrogen is ejected through the first hydrogen jet hole 101, and the diffused air flows in from the primary air supply channel 200 and generates a swirl after passing through the secondary swirler. The diffused air generates a recirculation zone at the nozzle outlet and is quickly and evenly mixed with the diffused hydrogen. The igniter ignites the mixed air to quickly form a diffusion combustion, thereby forming a stable ignition source. At the same time, in the premixed combustion zone, part of the premixed hydrogen is directly ejected into the mixing chamber 4000 through the second hydrogen jet hole 401, and the remaining premixed hydrogen enters the main swirl blade 60 through the hydrogen delivery hole 402. Then it is ejected into the mixing chamber 4000 through the third hydrogen jet hole 602; part of the premixed air is directly ejected into the mixing chamber 4000 through the second air jet hole 301, and the remaining premixed air enters the main swirl blade 60 through the air delivery hole 302, and then is ejected into the mixing chamber 4000 through the third air jet hole 601; the liquid fuel is atomized into droplets under the action of the pressure nozzle, and is quickly mixed with the premixed hydrogen and premixed air in the mixing chamber 4000 to form a mixed gas, and a swirl is generated when it flows through the main swirler. After the mixed gas is discharged from the outlet of the mixing chamber 4000, it is quickly diffused and burned. Flame ignition, with the continuous supply of fresh fuel and air, diffusion combustion and premixed combustion can be carried out continuously. Through the above-mentioned setting, not only can the liquid fuel be prevented from contacting the high-temperature wall in a high-temperature environment, thereby avoiding the occurrence of coking, but the jet hydrogen and air and the atomized liquid fuel and the air ejected from the first air jet hole 901 can be premixed in the mixing chamber 4000, thereby improving the mixing effect, contributing to full combustion and combustion temperature control. During this period, the amount of premixed hydrogen in the mixing chamber 4000 must always be less than the amount of premixed hydrogen and liquid fuel in the mixing chamber 4000. 10% of the total amount in the mixing chamber 4000, thereby ensuring that the flame front always remains in the normal position during liquid fuel combustion, preventing excessive hydrogen content from causing the flame front to move upstream of the nozzle and causing backfire; at the same time, a lower hydrogen content can keep it in a lean-burn combustion state to control the flame surface temperature and reduce the production of thermal nitrogen oxides, thereby achieving efficient mixing and combustion of hydrogen and liquid fuel; during this period, the local equivalence ratio and the mixing ratio of hydrogen and liquid fuel can also be changed by adjusting the hydrogen flow rate and liquid fuel flow rate, so as to control pollutant emissions and combustion stability.

[0093] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A combustion chamber nozzle structure, characterized in that: include: A first tube body (10), a second tube body (20), a third tube body (30), a fourth tube body (40), and a fifth tube body (50) are coaxially arranged; The inner peripheral wall of the third tube body (30) and the outer peripheral wall of the second tube body (20) are spaced radially to form a secondary air supply flow channel (300); the inner peripheral wall of the fifth tube body (50) and the outer peripheral wall of the fourth tube body (40) are spaced radially to form a secondary hydrogen supply flow channel (500); and the inner peripheral wall of the fourth tube body (40) and the outer peripheral wall of the third tube body (30) are spaced radially to form an annular cavity (400); The annular cavity (400) forms a mixing cavity (4000) downstream in the axial direction; The third tube (30) is provided with a second air jet hole (301), one end of the second air jet hole (301) is connected to the secondary air supply channel (300), and the other end is connected to the mixing chamber (4000); the fourth tube (40) is provided with a second hydrogen jet hole (401), one end of the second hydrogen jet hole (401) is connected to the secondary hydrogen supply channel (500), and the other end is connected to the mixing chamber (4000); A plurality of main swirl blades (60) are provided in the middle and downstream of the mixing chamber (4000), and the plurality of main swirl blades (60) are suitable for forming a main swirler; each of the main swirl blades (60) is provided with a third air jet hole (601) and a third hydrogen jet hole (602); the third air jet hole (601) is suitable for introducing the air in the secondary air supply channel (300) into the mixing chamber (4000), and the third hydrogen jet hole (602) is suitable for introducing the hydrogen in the secondary hydrogen supply channel (500) into the mixing chamber (4000); Each of the main swirl blades (60) includes an inner cavity wall (61) and an outer cavity wall (62); the inner cavity wall (61) is suitable for enclosing an inner cavity (610), the inner cavity (610) is connected to the secondary air supply channel (300) through an air delivery hole (302), and the air delivery hole (302) is provided on the third tube body (30); the outer cavity wall (62) is suitable for enclosing an outer cavity (620), the outer cavity (620) is connected to the secondary hydrogen supply channel (500) through a hydrogen delivery hole (402), and the hydrogen delivery hole (402) is provided on the fourth tube body (40); and the outer cavity (620) and the inner cavity (610) are not connected to each other; The third air jet holes (601) are uniformly and densely arranged on the inner cavity wall (61), one end of the third air jet holes (601) is connected to the inner cavity (610), and the other end is connected to the mixing cavity (4000); the third hydrogen jet holes (602) are uniformly and densely arranged on the outer cavity wall (62), one end of the third hydrogen jet holes (602) is connected to the outer cavity (620), and the other end is connected to the mixing cavity (4000).

2. The combustion chamber nozzle structure according to claim 1, characterized in that: The angle between the central axis of the second air jet hole (301) and the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the second hydrogen jet hole (401) and the central axis of the combustion chamber nozzle structure are both β, and the value range of β is 30°≤β≤90°.

3. The combustion chamber nozzle structure according to claim 1, characterized in that: The inner peripheral wall of the first tube body (10) surrounds and forms a primary hydrogen supply channel (100); a first hydrogen jet hole (101) is provided at the end of the first tube body (10), and the first hydrogen jet hole (101) is connected to the primary hydrogen supply channel (100); A primary air supply channel (200) is formed between the inner peripheral wall of the second tube body (20) and the outer peripheral wall of the first tube body (10) along a radial interval; a plurality of auxiliary swirl blades (70) are provided at the end of the primary air supply channel (200), and the plurality of auxiliary swirl blades (70) are suitable for forming an auxiliary swirler.

4. The combustion chamber nozzle structure according to claim 3, characterized in that: The number of the first hydrogen jet holes (101) is multiple, one of the first hydrogen jet holes (101) is coaxially arranged with the central axis of the combustion chamber nozzle structure, and the remaining first hydrogen jet holes (101) are arranged around the central axis of the combustion chamber nozzle structure, and the angle between the central axis of the remaining first hydrogen jet holes (101) and the central axis of the combustion chamber nozzle structure is α, and the value range of α is 30°≤α≤60°.

5. The combustion chamber nozzle structure according to any one of claims 1 to 4, characterized in that: A plurality of liquid fuel supply pipes (80) are provided upstream of the annular cavity (400) in the axial direction, and the plurality of liquid fuel supply pipes (80) are uniformly arranged circumferentially around the third tube body (30); one end of the liquid fuel supply pipe (80) is axially connected to the mixing cavity (4000); A pressure nozzle is provided at one end of the liquid fuel supply pipe (80) close to the mixing chamber (4000), and the pressure nozzle is suitable for atomizing the liquid fuel.

6. The combustion chamber nozzle structure according to claim 5, characterized in that: The combustion chamber nozzle structure further includes a support plate (90), the support plate (90) being connected to the end of the liquid fuel supply pipe (80), one radial side of the support plate (90) being connected to the third tube body (30), and the other radial side being connected to the fourth tube body (40); a plurality of first air jet holes (901) are provided on the support plate (90), and the first air jet holes (901) are evenly distributed on the support plate (90) and are used to supply most of the air required for liquid fuel combustion.

7. A method for operating a combustion chamber nozzle structure, characterized in that: Applied to the combustion chamber nozzle structure according to any one of claims 5-6, the operating method of the combustion chamber nozzle structure includes: A hydrogen source supplies diffused hydrogen to the primary hydrogen supply channel (100), so that the diffused hydrogen is ejected through the first hydrogen jet hole (101). Simultaneously, a compressor supplies diffused air to the primary air supply channel (200), so that the diffused air generates a swirl after passing through the secondary swirler, generates a recirculation zone at the nozzle outlet, and is quickly and evenly mixed with the diffused hydrogen. The mixed air is ignited by the igniter to quickly form diffuse combustion, thereby forming a stable ignition source. Premixed hydrogen is supplied to the secondary hydrogen supply channel (500) from a hydrogen source, and premixed air is supplied to the secondary air supply channel (300) through a compressor, so that part of the premixed hydrogen is directly ejected into the mixing chamber (4000) through the second hydrogen jet hole (401), and the remaining premixed hydrogen enters the main swirl blade (60) through the hydrogen delivery hole (402), and then is ejected into the mixing chamber (4000) through the third hydrogen jet hole (602). At the same time, part of the premixed air is directly ejected into the mixing chamber (4000) through the second air jet hole (301), and the remaining premixed air enters the main swirl blade (60) through the air delivery hole (302), and then is ejected into the mixing chamber (4000) through the third air jet hole (601); Liquid fuel is supplied from a liquid fuel source into the liquid fuel supply pipe (80), so that the liquid fuel is atomized into droplets under the action of a pressure nozzle, and is quickly mixed with premixed hydrogen and premixed air in the mixing chamber (4000), and generates a swirl when flowing through the main swirler. After being transmitted from the outlet of the mixing chamber (4000), it is quickly ignited by the diffusion flame. With the continuous supply of fresh fuel and air, diffusion combustion and premixed combustion can continue.

8. The operating method of the combustion chamber nozzle structure according to claim 7, characterized in that: The amount of premixed hydrogen in the mixing chamber (4000) is always less than 10% of the total amount of premixed hydrogen and liquid fuel in the mixing chamber (4000).

9. The operating method of the combustion chamber nozzle structure according to claim 7 or 8, characterized in that: The hydrogen flow rate and / or the liquid fuel flow rate are adjustable, and the local equivalence ratio and the mixing ratio of hydrogen and liquid fuel are changed by adjusting the hydrogen flow rate and the liquid fuel flow rate.

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