Liquid hydrocarbon fuel multi-stage radial swirl nozzle and its co-combustion method

Abstract

A multi-stage radial swirling nozzle for hydrogen-blended liquid hydrocarbon fuel and its blending combustion method are provided. The multi-stage radial swirling nozzle for hydrogen-blended liquid hydrocarbon fuel includes: an aviation kerosene centrifugal nozzle; a Venturi tube arranged coaxially with the aviation kerosene centrifugal nozzle, the outlet of the Venturi tube forming the nozzle outlet; several radial swirlers, located radially outside the aviation kerosene centrifugal nozzle, each radial swirler including interconnected radial and axial channels; several swirling blades arranged in a ring array within the radial channels; and several hydrogen injection holes. The radial channel of the radial swirler furthest from the nozzle outlet is connected to the hydrogen injection hole, and the hydrogen injection holes are arranged in a ring array around the central axis of the radial swirler. Among the several radial swirlers, the further the radial channel is from the nozzle outlet, the closer its corresponding axial channel is to the central axis of the radial swirler. It exhibits good compatibility with traditional aero-engine combustion chambers.

Description

Technical Field

[0001] This application relates to the field of combustion nozzle technology, and in particular to a multi-stage radial swirl nozzle for hydrogen-blended liquid hydrocarbon fuel and its blending combustion method. Background Technology

[0002] As global warming becomes increasingly prominent, reducing carbon dioxide emissions has become an important part of environmental protection efforts. With the development of the aviation industry, the expansion of air routes, and the popularization of air transportation, the impact of CO2 emissions from aircraft engines is becoming increasingly apparent. Therefore, it is necessary to seek ways to reduce carbon emissions, and the use of hydrogen energy is one of the important approaches.

[0003] Hydrogen differs significantly from aviation kerosene in its combustion characteristics. Hydrogen has a higher flame propagation speed, requires less ignition energy, and burns more easily and rapidly. However, the use of hydrogen also introduces backfire and nitrogen oxides (NOx). X Problems such as excessive emissions exist. Therefore, using pure hydrogen as fuel presents the issue of poor compatibility with traditional aviation kerosene combustion chambers. To address this, a hydrogen-blended aviation kerosene scheme can be adopted as a transitional solution from pure aviation kerosene to pure hydrogen, accelerating the practical application of hydrogen in aircraft engines.

[0004] While aviation kerosene blended with hydrogen exhibits better combustion chamber adaptability in traditional aero-engines compared to pure hydrogen fuel, certain technical challenges exist in combustion organization. As aviation kerosene is a liquid hydrocarbon fuel, it requires atomization and evaporation before mixing with air and combustion, whereas hydrogen, as a gaseous fuel, can directly enter the combustion chamber to mix and react with air. Combustion of this blend requires coordinating fuel injection and mixing positions to achieve more uniform mixing, more stable combustion, and fewer localized high-temperature zones. Furthermore, the two fuels have different phases, resulting in significant differences in combustion characteristics such as ignition delay time and flame propagation speed.

[0005] Existing combustion organization technologies for liquid hydrocarbon fuels with hydrogen blending are mainly divided into large-scale swirling combustion and micro-scale mixing combustion, and further classified into diffusion combustion and premixed combustion based on the air-fuel blending conditions. Existing micro-scale mixing combustion organization technology can divide a large-scale flame into multiple smaller-scale flames, effectively reducing the occurrence of localized high temperatures, thereby reducing NO₂. X While reducing emissions, this also leads to excessive pressure drop at the nose. Furthermore, aircraft engines are poorly compatible with traditional aviation kerosene combustors, and modifications to the combination of aircraft engines and traditional aviation kerosene combustors also result in increased weight. Large-scale swirling combustion organization offers advantages such as compatibility with traditional combustors and lower NOx emissions. X Its advantages, such as emissions, make it a preferred option that is well-suited to both hydrogen and aviation kerosene fuels.

[0006] Existing large-scale swirl combustion technology can be further divided into two categories: diffusion combustion and premixed combustion. However, in diffusion combustion, the mixing of air and fuel is insufficient, resulting in NO... X The disadvantage of high pollutant emissions.

[0007] Currently, there are few technologies for large-scale swirl-configuration hydrogen-blended combustion of aviation kerosene. Chinese invention patent CN103277813B discloses "a low-pollution combustion chamber for hydrogen addition and emission reduction in aviation fuel combustion." This combustion chamber discloses a staged premixed lean-burn combustion organization method, in which hydrogen plays a role in assisting combustion, widening the lean-burn limit, and reducing NO in lean-burn combustion. X The emission reduction is in line with the requirements for retrofitting traditional aircraft engine combustion chambers, but there is a problem with the availability of hydrogen blending, and hydrogen is not a primary fuel.

[0008] Numerous technological inventions have been developed for the incorporation of hydrogen into gas turbines. Chinese invention patent publication number CN104870902A discloses a "Gas Turbine Combustor Suitable for Multiple Fuels." This combustor discloses a large-scale swirling nozzle design for blending natural gas and hydrogen, featuring low NO₂ levels. X While these technologies offer advantages such as emissions and stable combustion, natural gas is a gaseous fuel, while aviation kerosene is a liquid fuel. Therefore, these technologies are not entirely suitable for the combustion of liquid hydrocarbon fuels blended with hydrogen, and the design of nozzles for hydrogen-blended combustion of liquid aviation kerosene remains relatively scarce. Summary of the Invention

[0009] This application is made in view of the state of the prior art described above. This application aims to solve or alleviate at least one of the aforementioned problems.

[0010] In a first aspect, this application provides a multi-stage radial swirling nozzle for hydrogen-blended liquid hydrocarbon fuel, comprising: an aviation kerosene centrifugal nozzle; a venturi tube, coaxially arranged with the aviation kerosene centrifugal nozzle, the outlet of the venturi tube and the outlet of the aviation kerosene centrifugal nozzle facing the same axial direction, the outlet of the venturi tube forming the nozzle outlet; a plurality of radial swirlers, the radial swirlers being disposed radially outside the aviation kerosene centrifugal nozzle, the radial swirlers including interconnected radial channels and axial channels; a plurality of swirling blades arranged in a ring array within the radial channels; and a plurality of hydrogen injection holes, the radial channel of the radial swirler furthest from the nozzle outlet communicating with the hydrogen injection hole, the plurality of hydrogen injection holes arranged in a ring array around the central axis of the radial swirler; wherein, the radial channel of the plurality of radial swirlers, the farther away from the nozzle outlet, the closer its corresponding axial channel is to the central axis of the radial swirler.

[0011] As a further improvement of this application, the radial cyclone includes a first-stage radial cyclone and a second-stage radial cyclone. The first-stage radial cyclone includes a first-stage cyclone channel, which includes a first radial channel and a first axial channel that are perpendicularly connected to each other. The second-stage radial cyclone includes a second-stage cyclone channel, which includes a second radial channel and a second axial channel that are perpendicularly connected to each other. The cyclone blades include a plurality of first blades in the first-stage radial cyclone and a plurality of second blades in the second-stage radial cyclone. The axial distance from the first radial channel to the nozzle outlet is greater than the axial distance from the second radial channel to the nozzle outlet. The radial distance from the first axial channel to the central axis of the radial cyclone is less than the radial distance from the second axial channel to the central axis of the radial cyclone.

[0012] As a further improvement of this application, all hydrogen injection holes are covered by a hydrogen storage chamber on the side facing away from the radial cyclone. The side of the hydrogen storage chamber facing away from the radial cyclone is connected to a hydrogen inlet pipe, which is arranged parallel to the aviation kerosene centrifugal nozzle.

[0013] As a further improvement of this application, from the axial perspective of the radial cyclone, the first blade and the second blade are arranged alternately at intervals; the length of the first blade is greater than the length of the second blade; the extension direction of the cyclone blade does not intersect with the central axis of the radial cyclone, and from the axial perspective of the radial cyclone, the extension line of the cyclone blade itself is tangent to or intersects with the inner wall of the outer ring of the axial channel.

[0014] As a further improvement of this application, from the axial perspective of the radial cyclone, each of the cyclone blades extends in a straight line, and the cyclone direction of the first blade and the cyclone direction of the second blade are both clockwise or both counterclockwise; the blade rotation angle of the first blade is smaller than that of the second blade.

[0015] As a further improvement of this application, the blade rotation angle of the first blade is 40° to 50°, and the blade rotation angle of the second blade is 60° to 70°.

[0016] As a further improvement of this application, the inner diameter of the hydrogen injection hole is 0.6 mm to 1.0 mm, the vertical distance from the hydrogen injection hole to the central axis of the radial cyclone is 7 mm to 10 mm, and the number of hydrogen injection holes is 6 to 10; the axial dimension of the cyclone blade is 1.2 mm to 3.0 mm, and the number of cyclone blades in each radial cyclone is 6 to 12.

[0017] As a further improvement of this application, the hydrogen storage chamber is surrounded by a first radial plate, a second radial plate, a first axial tube, and the aviation kerosene centrifugal nozzle, which are parallel to each other. The hydrogen injection hole passes through the second radial plate, and the hydrogen inlet pipe passes through the first radial plate. A third radial plate and a fourth radial plate are arranged in parallel in sequence on the second radial plate away from the first radial plate. The space between the second radial plate and the third radial plate is the first radial channel, and the space between the third radial plate and the fourth radial plate is the second radial channel. The space between the inner wall of the Venturi tube and the outer wall of the aviation kerosene centrifugal nozzle forms the first axial channel. A second axial tube is fixed on the side of the third radial plate away from the second radial plate. The space between the inner wall of the second axial tube and the outer wall of the Venturi tube forms the second axial channel.

[0018] As a further improvement of this application, the outlet of the shaft end of the second axial tube is at the same axial position as the outlet of the shaft end of the Venturi tube; the outlet of the aviation kerosene centrifugal nozzle is located upstream of the outlet of the Venturi tube.

[0019] Secondly, a method for co-combustion of liquid hydrocarbon fuel with a multi-stage radial swirl nozzle is provided, comprising: using air as an oxidant and using aviation kerosene and hydrogen as fuel; the flowing medium in the first-stage swirl channel and the second-stage swirl channel is air; the flowing medium in the aviation kerosene centrifugal nozzle is aviation kerosene; the flowing medium in the hydrogen injection orifice is hydrogen; the air generates swirl after passing through the first-stage swirl channel and the second-stage swirl channel respectively, and forms a recirculation zone in the combustion chamber; the hydrogen and the air are mixed in the first-stage swirl channel; the aviation kerosene is atomized, and the resulting mixture of air and fuel enters the combustion chamber after passing through the venturi tube.

[0020] As a further improvement of this application, the spray of aviation kerosene from the aviation kerosene centrifugal nozzle has a particle diameter of 30 μm to 100 μm, and the cone angle of the spray ranges from 45° to 80°.

[0021] The beneficial effects of the multi-stage radial swirling nozzle for hydrogen blending of liquid hydrocarbon fuel in this application include: good compatibility with traditional aero-engine combustion chambers; and a basic layout employing multiple radial swirling nozzles, hydrogen injection holes, and a centrally arranged aviation kerosene centrifugal nozzle, which can function as a separate head within a full-annular combustion chamber. First, the swirling blades inside each radial swirling nozzle create swirling flow in the passing fluid, forming a recirculation zone within the combustion chamber. The radial channels guide the fluid radially inwards first, and then the axial channels redirect the fluid direction to the axial direction. Second, the annular array of hydrogen injection holes allows for multiple hydrogen injections, facilitating subsequent uniform mixing. Third, the radial swirling nozzle furthest from the nozzle outlet, connected to the hydrogen injection hole and located upstream, enables mixing of air and hydrogen, ensuring uniform mixing and atomizing the liquid aviation kerosene from the aviation kerosene centrifugal nozzle. Fourth, the radial swirling nozzles relatively closer to the nozzle outlet, located relatively downstream, facilitate the formation of a swirling zone in the main combustion chamber, thus contributing to stable combustion. Finally, the resulting air-fuel mixture enters the combustion chamber through the venturi tube, which also prevents backfire. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments, the accompanying drawings of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is an axial view of one embodiment of the liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle of this application;

[0024] Figure 2 This application is Figure 1 A cross-sectional view (AA) of a multi-stage radial swirl nozzle for hydrogen-blended liquid hydrocarbon fuel;

[0025] Figure 3 This is a front view of one embodiment of the liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle of this application;

[0026] Figure 4 This application is Figure 3 BB cross-sectional view of a multi-stage radial swirl nozzle for hydrogen-blended liquid hydrocarbon fuel;

[0027] Figure 5 This application is Figure 3 CC cross-sectional view of a multi-stage radial swirl nozzle for hydrogen-blended liquid hydrocarbon fuel;

[0028] Figure 6 This application is Figure 3 DD cross-sectional view of a multi-stage radial swirl nozzle for hydrogen-blended liquid hydrocarbon fuel;

[0029] Figure 7 This application is Figure 3 EE cross-sectional view of a multi-stage radial swirl nozzle for hydrogen-blended liquid hydrocarbon fuel;

[0030] Figure 8 This is a perspective view of one embodiment of the liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle of this application;

[0031] Figure 9 This is a quarter cross-sectional view of one embodiment of the liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle of this application;

[0032] Figure 10 This is a quarter cross-sectional view of one embodiment of the liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle of this application;

[0033] Figure 11 This is a fluid simulation diagram of the operating state of one embodiment of the liquid hydrocarbon fuel hydrogen-infused multi-stage radial swirl nozzle of this application.

[0034] Explanation of reference numerals in the attached figures

[0035] 1-First-stage cyclone inlet; 2-Second-stage cyclone inlet; 3-First-stage radial cyclone; 31-First blade; 4-Second-stage radial cyclone; 41-Second blade; 5-Hydrogen inlet pipe; 6-Hydrogen storage chamber; 7-Hydrogen injection hole; 8-Aerospace kerosene centrifugal nozzle; 9-First-stage cyclone channel; 91-First radial channel; 92-First axial channel; 10-Second-stage cyclone channel; 101-Second radial channel; 102-Second axial channel; 15 - Venturi tube; 151- Venturi tube throat; 17- Nozzle outlet; 171- First outlet; 172- Second outlet; 18- First radial plate; 19- First axial tube; 20- Second radial plate; 21- Third radial plate; 22- Fourth radial plate; 23- Second axial tube; 24- Rounded corner; α- First blade angle; β- Second blade angle; F- Outer ring inner wall; G- Central main recirculation zone; H- Stepped recirculation zone; I- Shear layer; J- Angular recirculation zone. Detailed Implementation

[0036] Exemplary embodiments of this application are described below with reference to the accompanying drawings. It should be understood that these specific descriptions are for teaching those skilled in the art how to implement this application only, and are not intended to exhaustively describe all possible methods of this application, nor to limit the scope of this application.

[0037] The following detailed description, in conjunction with specific embodiments, further illustrates the liquid hydrocarbon fuel multi-stage radial swirl nozzle and the liquid hydrocarbon fuel multi-stage radial swirl nozzle co-combustion method of this application.

[0038] See Figure 9 The liquid hydrocarbon fuel multi-stage radial swirling nozzle of this application may include: an aviation kerosene centrifugal nozzle 8, a venturi tube 15, a hydrogen injection orifice 7, and several radial swirlers. The venturi tube 15 and the aviation kerosene centrifugal nozzle 8 are arranged coaxially, and their respective outlets face the same axial direction (i.e., Figure 9 On the lower right side of the nozzle 15, the outlet of the Venturi tube 15 forms the nozzle outlet 17. Several radial cyclones are coaxially arranged on the radially outer side of the aviation kerosene centrifugal nozzle 8. Each radial cyclone includes interconnected radial and axial channels; several swirling blades are arranged within the radial channels, forming a ring array around the central axis of the radial cyclone. The radial channel of the radial cyclone furthest from the nozzle outlet 17 is connected to the hydrogen injection hole 7, such as... Figure 4 As shown, several hydrogen injection holes 7 are arranged in a ring array around the central axis of the radial cyclone. Among them, the radial channels in the radial cyclone are further away from the nozzle outlet 17, while their corresponding axial channels are closer to the central axis of the radial cyclone.

[0039] like Figure 9 , Figure 10 As shown in the attached diagram, to better illustrate the internal structure, the visual effect is as follows: Figure 9 , Figure 10 The fan-shaped region of one-quarter of the liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle in this application has been removed. In fact, the complete three-dimensional view of the liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle in this application is still as shown. Figure 8 As shown.

[0040] In one embodiment, there are two radial cyclones, such as... Figure 2 , Figure 9 , Figure 10 As shown, the radial cyclone separator includes a first-stage radial cyclone separator 3 and a second-stage radial cyclone separator 4. The cavity inside the first-stage radial cyclone separator 3 forms a first-stage cyclone channel 9, which includes a first radial channel 91 and a first axial channel 92 that are perpendicularly connected to each other. The cavity inside the second-stage radial cyclone separator 4 forms a second-stage cyclone channel 10, which includes a second radial channel 101 and a second axial channel 102 that are perpendicularly connected to each other. Both the first-stage cyclone channel 9 and the second-stage cyclone channel 10 guide the fluid to move radially inward and then unidirectionally along the same axial direction.

[0041] The beneficial effects of the above embodiments are: using a nozzle configuration similar to that used in conventional aircraft engine combustion chambers, and employing a two-stage radial swirler to introduce air. The air passing through the first-stage radial swirler 3 primarily serves to mix with hydrogen and atomize liquid aviation kerosene, while the air passing through the second-stage radial swirler 4 primarily serves to form a swirling zone in the main combustion chamber, thereby stabilizing combustion. Figure 11 The simulation shown depicts a combustion zone comprising a shear layer I and a central main recirculation zone G, similar to that of a conventional aero-engine combustor. Due to this structural similarity, the resulting nozzle pressure drop and head weight are comparable to those of conventional aviation kerosene nozzles. Simultaneously, a stepped recirculation zone H is formed near the outlet edge of the venturi 15, and an angular recirculation zone J is formed further outward from the shear layer I. Overall, it exhibits good compatibility with conventional aero-engine combustors.

[0042] The axial distance from the first radial channel 91 to the nozzle outlet 17 is greater than the axial distance from the second radial channel 101 to the nozzle outlet 17; the radial distance from the first axial channel 92 to the central axis of the radial cyclone is less than the radial distance from the second axial channel 102 to the central axis of the radial cyclone. That is, the first radial channel 91 is upstream of the second radial channel 101, and the second axial channel 102 is on the outer layer of the first axial channel 92.

[0043] The corresponding swirling blades include several first blades 31 in the first-stage radial swirler 3, and several second blades 41 in the second-stage radial swirler 4.

[0044] In one embodiment, from an axial perspective of the radial cyclone separator, the first blade 31 and the second blade 41 are arranged alternately, meaning that the axial projections of the first blade 31 and the second blade 41 do not overlap. This staggered arrangement of the first blade 31 and the second blade 41 can moderately reduce air intake resistance. Simultaneously, the length of the first blade 31 is greater than the length of the second blade 41; that is, the length of the first blade 31 extending in the direction perpendicular to the central axis of the radial cyclone separator is greater than the length of the second blade 41 extending in the same direction.

[0045] like Figure 5 and Figure 6 As shown, the extension directions of the first blade 31 and the second blade 41 do not intersect the central axis of the radial cyclone. From the axial perspective of the radial cyclone, the extension line of the cyclone blade itself can be intersecting or tangent to the inner wall F of the outer ring of the axial channel. The inner wall F of the outer ring is a circle from the axial perspective of the radial cyclone. In the same radial cyclone, the plane containing each cyclone blade is equidistant from the central axis of the radial cyclone.

[0046] like Figure 5 , Figure 6 As shown, in one embodiment, from the axial perspective of the radial cyclone, each cyclone blade extends in a straight line, and the first blade 31 and the second blade 41 each have a cyclone direction that is either clockwise or counterclockwise.

[0047] The inlet width of the first-stage cyclone inlet 1 corresponding to the first radial channel 91 of the first-stage cyclone channel 9 is greater than the outlet width of the first radial channel 91. The inlet width of the second-stage cyclone inlet 2 corresponding to the second radial channel 101 of the second-stage cyclone channel 10 is greater than the outlet width of the second radial channel 101.

[0048] Viewed axially, the first blade 31 and the second blade 41 have the same swirling direction, as shown below. Figure 5 , Figure 6 As shown, the circumferential direction of the airflow corresponding to the first blade 31 is the same as the circumferential direction of the airflow corresponding to the second blade 41, both being clockwise.

[0049] In a non-limiting example, the axial dimension of the swirling blades is 1.2 mm to 3.0 mm, and the number of swirling blades in each radial swirler is 6 to 12.

[0050] In one embodiment, the blade rotation angle of the first blade 31 can be smaller than that of the second blade 41. An auxiliary line is drawn from the nozzle axis of this application, and this auxiliary line contacts the inner end of the swirling blade. The angle between this swirling blade and the auxiliary line is the blade rotation angle. Figure 5 As shown, the blade rotation angle of the first blade 31 is the first blade rotation angle α, as... Figure 6 As shown, the blade rotation angle of the second blade 41 is the second blade rotation angle β. In a non-limiting example, the blade rotation angle of the first blade 31 is 40° to 50°, and the blade rotation angle of the second blade 41 is 60° to 70°.

[0051] like Figure 5 , Figure 6 As shown, each swirl blade extends along a straight line. In a non-limiting example, the surface of the swirl blade can also be curved. Curved swirl blades can reduce air resistance. Based on the design formula of the curved surface and numerical calculations, the specific curved surface shape of the swirl blade can be iteratively improved.

[0052] In one embodiment, all hydrogen injection holes 7, on the side facing away from the radial cyclone, are covered by a hydrogen storage chamber 6. The side of the hydrogen storage chamber 6 facing away from the radial cyclone is connected to a hydrogen inlet pipe 5, which is arranged parallel to the aviation kerosene centrifugal nozzle 8. The central axis of the hydrogen inlet pipe 5 does not coincide with the central axis of the aviation kerosene centrifugal nozzle 8, and their axial projections do not intersect. The inner diameter of the hydrogen inlet pipe 5 is larger than the inner diameter of a single hydrogen injection hole 7.

[0053] The cross-sectional profile of the inner wall of the hydrogen injection orifice 7 can be circular. The hydrogen injection orifice 7 is a direct injection orifice. In actual selection, the size and position of the hydrogen injection orifice 7 can be adjusted according to the configuration of the combustion chamber, standard operating conditions, nozzle outlet 17 temperature, and other requirements.

[0054] In a non-limiting example, the inner diameter of the hydrogen injection hole 7 is 0.6 mm to 1.0 mm, the vertical distance from the hydrogen injection hole 7 to the central axis of the radial cyclone is 7 mm to 10 mm, and the number of hydrogen injection holes 7 is 6 to 10.

[0055] like Figure 8 , Figure 9 As shown, in one embodiment, the hydrogen storage chamber 6 is surrounded by a first radial plate 18, a second radial plate 20, a first axial tube 19, and an aviation kerosene centrifugal nozzle 8, all parallel to each other. The hydrogen injection hole 7 passes through the second radial plate 20, and the hydrogen inlet pipe 5 passes through the first radial plate 18. A third radial plate 21 and a fourth radial plate 22 are arranged parallel to each other in the direction away from the first radial plate 18 on the second radial plate 20. The space between the second radial plate 20 and the third radial plate 21 is the first radial channel 91, and the space between the third radial plate 21 and the fourth radial plate 22 is the second radial channel 101. The space between the inner wall of the venturi tube 15 and the outer wall of the aviation kerosene centrifugal nozzle 8 is the first axial channel 92. A second axial tube 23 is fixed to the side of the third radial plate 21 away from the second radial plate 20. The space between the inner wall of the second axial tube 23 and the outer wall of the venturi tube 15 is the second axial channel 102.

[0056] like Figure 5 As shown, the widest point of two adjacent first blades 31 constitutes the first-stage cyclone inlet 1, and the number of first-stage cyclone inlets 1 is equal to the number of first blades 31. Simultaneously, the two ends of the first blades 31 contact the inner and outer edges of the third radial plate 21, respectively. Figure 6 As shown, the widest point of two adjacent second blades 41 constitutes the second-stage cyclone inlet 2, and the number of second-stage cyclone inlets 2 is equal to the number of second blades 41. At the same time, the two ends of the second blades 41 contact the inner and outer edges of the fourth radial plate 22, respectively.

[0057] like Figure 2 As shown, the nozzle outlet 17 includes both the first outlet 171 corresponding to the outlet of the venturi 15 and the second outlet 172 corresponding to the outlet of the second axial passage 102. Furthermore, the inner wall of the venturi 5 first contracts and then gradually expands, and the inner wall of the venturi 5 has a venturi throat 151 protruding (see...). Figure 9 The inner diameter corresponding to the throat 151 of the venturi tube is the minimum value of the inner diameter of the venturi tube 5.

[0058] The outlets at the axial ends of the second axial tube 23 and the venturi tube 15 are in the same axial position, that is, the outlet ends of the second axial tube 23 and the venturi tube 15 are flush. The outlet end of the aviation kerosene centrifugal nozzle 8 is not flush with the outlet end of the venturi tube 15. The outlet end of the aviation kerosene centrifugal nozzle 8 is located upstream of the outlet end of the venturi tube 15, that is, the outlet of the aviation kerosene centrifugal nozzle 8 is recessed inside the venturi tube 15.

[0059] The beneficial effects of the above embodiment are: the venturi tube 15 structure is located downstream of the axial channel outlet of the first-stage swirl channel 9, which enables the air-fuel mixture to be ejected at a higher speed, so that the combustion is stabilized downstream of the nozzle outlet 17, and has a certain backfire prevention capability.

[0060] In one embodiment, such as Figure 9 , Figure 10 As shown, the corner between the first radial channel 91 and the first axial channel 92 is transitioned by a fillet 24. Similarly, the corner between the second radial channel 101 and the second axial channel 102 is also transitioned by a fillet 24. The inside corner of the corner is transitioned by an inner fillet, and the outside corner of the corner is transitioned by an outer fillet.

[0061] like Figure 9 , Figure 10 As shown, in one embodiment, the axial end edge of the Venturi tube 5 and the axial end edge of the second axial tube 23 are also transitioned by fillet 24, and the axial end edges of the Venturi tube 5 and the second axial tube 23 are transitioned by outer fillet.

[0062] This application also provides a method for the co-combustion of liquid hydrocarbon fuel using a multi-stage radial swirl nozzle, comprising: using air as an oxidant and aviation kerosene and hydrogen as fuel; the flowing medium in the first-stage swirl channel 9 and the second-stage swirl channel 10 is air; the flowing medium in the aviation kerosene centrifugal nozzle 8 is aviation kerosene; and the flowing medium in the hydrogen injection orifice 7 is hydrogen. Hydrogen and air are mixed in the first-stage swirl channel 9. The aviation kerosene is atomized, and the resulting air-fuel mixture enters the combustion chamber through the venturi tube 15. The airflow entering the two swirl channels passes through the first-stage swirl channel 9 and the second-stage swirl channel 10 respectively, generating swirl and forming a recirculation zone in the combustion chamber.

[0063] In one embodiment, the spray of aviation kerosene from the aviation kerosene centrifugal nozzle 8 has a particle diameter of 30 μm to 100 μm and a spray cone angle ranging from 45° to 80°.

[0064] The liquid hydrocarbon fuel blending and combustion method of this application is equivalent to being divided into a supply zone, a nozzle body, and a downstream combustion zone.

[0065] The supply area includes the supply of air, aviation kerosene, and hydrogen. Air flows in from upstream, changes direction at the radial cyclone, and enters the radial cyclone from the inlet 1 of the first-stage cyclone and the inlet 2 of the second-stage cyclone. Hydrogen enters the hydrogen storage chamber 6 through the hydrogen inlet pipe 5. The shaft end face of the hydrogen storage chamber 6 is connected to the shaft end face of the first-stage radial cyclone 3. Hydrogen is injected into the first-stage cyclone channel 9 through the hydrogen injection hole 7. Aviation kerosene enters the aviation kerosene centrifugal nozzle 8 through the fuel pipe and is atomized and sprayed into the combustion chamber.

[0066] The first radial channel 91 in the first-stage swirling channel 9 is located upstream, and the first axial channel 92 has its own flow direction in the axial direction. The first axial channel 92 is located radially inward than the first radial channel 91. Air enters from the inlet 1 of the first-stage swirling device, passes through the first-stage radial swirling device 3, and mixes with the hydrogen ejected from the hydrogen injection hole 7. It also atomizes the liquid kerosene ejected from the aviation kerosene centrifugal nozzle 8. After passing through the venturi tube 15, it enters the combustion chamber and generates a backflow. In the shear layer I, it mainly reacts with hydrogen to form a stable jet shear layer flame. In the backflow zone, it mainly reacts with kerosene vapor to form a flame.

[0067] The nozzle body includes a first-stage radial vortex 3, a second-stage radial vortex 4, an aviation kerosene centrifugal nozzle 8, and a hydrogen injection orifice 7. The aviation kerosene centrifugal nozzle 8 includes a liquid aviation kerosene channel, a nozzle body structure, and a kerosene nozzle. The aviation kerosene centrifugal nozzle 8 can use a structure from the prior art, which is not shown in detail in the accompanying drawings.

[0068] The downstream combustion zone is where the combustion reaction of aviation kerosene and hydrogen occurs. The combustion of hydrogen mainly occurs in shear layer I, while the combustion of aviation kerosene mainly occurs in the recirculation zone.

[0069] The liquid hydrocarbon fuel blending and combustion method using a multi-stage radial swirl nozzle can achieve a wide range of hydrogen blending ratio control. While meeting the basic requirement of not ablating the nozzle head, it can achieve a hydrogen blending ratio of up to 60% under baseline operating conditions. This represents a relatively wide achievable range of hydrogen blending ratio control, while ensuring compatibility with traditional combustion chambers, resulting in high fuel flexibility in practical applications.

[0070] The above embodiments are only for illustrating the technical concept and features of this application. Their purpose is to enable those skilled in the art to understand the content of this application and implement it. They should not be used to limit the scope of protection of this application. All equivalent changes or modifications made in accordance with the spirit and essence of this application should be covered within the scope of protection of this application.

Claims

1. A liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle, characterized by, The application relates to an aviation kerosene centrifugal nozzle (8) and a venturi (15) coaxially arranged with the aviation kerosene centrifugal nozzle (8), the outlet of the venturi (15) and the outlet of the aviation kerosene centrifugal nozzle (8) are oriented towards the same axis, and the outlet of the venturi (15) forms a nozzle outlet (17). The radial swirler comprises a first-stage radial swirler (3) and a second-stage radial swirler (4), the first-stage radial swirler (3) comprises a first-stage swirler channel (9) comprising a first radial channel (91) and a first axial channel (92) which are perpendicular to each other, and the second-stage radial swirler (4) comprises a second-stage swirler channel (10) comprising a second radial channel (101) and a second axial channel (102) which are perpendicular to each other. The swirler vanes comprise a plurality of first vanes (31) in the first-stage radial swirler (3) and a plurality of second vanes (41) in the second-stage radial swirler (4). The axial distance from the first radial channel (91) to the nozzle outlet (17) is greater than the axial distance from the second radial channel (101) to the nozzle outlet (17), and the radial distance from the first axial channel (92) to the central axis of the radial swirler is smaller than the radial distance from the second axial channel (102) to the central axis of the radial swirler. The first vanes (31) and the second vanes (41) are alternately arranged along the axial view of the radial swirler, and the length of the first vanes (31) is greater than the length of the second vanes (41). The extension direction of the swirler vanes does not intersect the central axis of the radial swirler, and the extension line of the swirler vanes themselves is tangent to or intersects the outer wall (F) of the axial channel along the axial view of the radial swirler, and the blade turning angle of the first vanes (31) is smaller than the blade turning angle of the second vanes (41). A plurality of hydrogen injection holes (7) are arranged in a ring array around the central axis of the radial swirler, and the radial channel of the radial swirler farthest from the nozzle outlet (17) is communicated with the hydrogen injection holes (7). The farther the radial channel of the radial swirler is from the nozzle outlet (17), the closer the corresponding axial channel is to the central axis of the radial swirler. All the hydrogen injection holes (7) are collectively covered by a hydrogen storage cavity (6) on the side away from the radial swirler, the side away from the radial swirler of the hydrogen storage cavity (6) is communicated with a hydrogen inlet pipeline (5), and the hydrogen inlet pipeline (5) is arranged in parallel with the aviation kerosene centrifugal nozzle (8). ​ 2. The liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle according to claim 1, characterized in that: ​ 3. The liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle according to claim 1, characterized in that: Each of the swirl vanes extends in a straight line direction along an axial view of the radial swirler, and swirl directions of the first vanes (31) and the second vanes (41) are both clockwise or both counterclockwise.

4. The liquid hydrocarbon fuel hydrogen-doped multistage radial swirl nozzle according to claim 1, characterized in that: The first vanes (31) have a vane angle of 40° to 50°, and the second vanes (41) have a vane angle of 60° to 70°.

5. The liquid hydrocarbon fuel hydrogen-doped multistage radial flow swirl nozzle according to claim 1, characterized in that: The hydrogen injection holes (7) have an inner diameter of 0.6mm to 1.0mm, a vertical distance from the hydrogen injection holes (7) to a central axis of the radial swirler is 7mm to 10mm, and the number of the hydrogen injection holes (7) is 6 to 10; The axial dimension of the swirl vanes is 1.2mm to 3.0mm, and the number of the swirl vanes in each of the radial swirler is 6 to 12.

6. The liquid hydrocarbon fuel hydrogen-doped multistage radial flow swirl nozzle according to claim 2, characterized in that: The hydrogen storage cavity (6) is surrounded by the first radial plate (18), the second radial plate (20), the first axial tube (19), and the aero kerosene centrifugal nozzle (8), the hydrogen injection holes (7) penetrate the second radial plate (20), and the hydrogen inlet pipeline (5) penetrates the first radial plate (18); The third radial plate (21) and the fourth radial plate (22) are arranged in parallel in sequence in a direction away from the first radial plate (18) of the second radial plate (20), a space between the second radial plate (20) and the third radial plate (21) is the first radial channel (91), and a space between the third radial plate (21) and the fourth radial plate (22) is the second radial channel (101); A space between an inner wall of the venturi (15) and an outer wall of the aero kerosene centrifugal nozzle (8) forms the first axial channel (92); A side of the third radial plate (21) away from the second radial plate (20) is further fixed with the second axial tube (23), and a space between an inner wall of the second axial tube (23) and an outer wall of the venturi (15) forms the second axial channel (102).

7. The liquid hydrocarbon fuel hydrogen-doped multistage radial swirl nozzle according to claim 6, characterized in that: An outlet of an axial end of the second axial tube (23) is in the same axial position as an outlet of an axial end of the venturi (15). An outlet of the aero kerosene centrifugal nozzle (8) is located at a position more upstream than an outlet of the venturi (15).

8. A method of hydrogen-doped multi-stage radial swirl nozzle mixing combustion of liquid hydrocarbon fuel, characterized by, The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; After the air passes through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, the air generates swirl and forms a recirculation zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); and The hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel according to any one of claims 1 to 4, 6, and 7 is used in a hydrogen-doped multi-stage radial swirl nozzle for liquid hydrocarbon fuel combustion mixing method, which comprises: Air is used as an oxidant, and aero kerosene and hydrogen are used as fuel; the flow medium in the first-stage swirl channel (9) and the second-stage swirl channel (10) is air; the flow medium in the aero kerosene centrifugal nozzle (8) is aero kerosene The aviation kerosene is atomized, and the mixture of the air and the fuel generated enters into the combustion chamber through the venturi (15).

9. The method of claim 8, wherein the method further comprises: The particle diameter of the spray of the aviation kerosene sprayed from the aviation kerosene centrifugal nozzle (8) is 30-100 μm, and the cone angle of the spray ranges from 45° to 80°.

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