Liquid hydrocarbon fuel hydrogen-doped multistage radial swirl nozzle and mixing combustion method thereof

Abstract

The invention provides a liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle and a mixing combustion method thereof. The liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle comprises an aviation kerosene centrifugal nozzle; the venturi tube and the aviation kerosene centrifugal nozzle are coaxially arranged, and an outlet of the venturi tube forms a nozzle outlet; the radial swirlers are arranged on the radial outer side of the aviation kerosene centrifugal nozzle, and each radial swirler comprises a radial channel and an axial channel which are communicated with each other; a plurality of swirl vanes in an annular array are arranged in the radial channel; the radial channel, farthest from the nozzle outlet, of the radial swirler is communicated with the hydrogen injection holes, and the hydrogen injection holes are arranged in an annular array around the central axis of the radial swirler; and the farther the radial channels in the radial hydrocyclones are away from the nozzle outlet, the closer the axial channels corresponding to the radial channels in the radial hydrocyclones are to the central axis of the radial hydrocyclones. And the adaptability with a traditional aero-engine combustion chamber is good.

Description

Technical Field

[0001] The present application relates to the technical field of combustion nozzles, and in particular to a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle and a blending and combustion method thereof. Background Art

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

[0003] The combustion characteristics of hydrogen are very different from those of aviation kerosene. The flame propagation speed of hydrogen is higher, the ignition energy is smaller, and it is easier to burn and burns faster. However, the use of hydrogen will also cause flashback, nitrogen oxides (NO X ) and other issues. Therefore, the use of pure hydrogen as fuel will have the problem of poor adaptability to the combustion chamber of traditional aviation kerosene. In order to solve this problem, the solution of aviation kerosene mixed with hydrogen can be adopted as a transitional solution from pure aviation kerosene to pure hydrogen, so as to accelerate the progress of practical application of hydrogen in aviation engines.

[0004] Jet fuel mixed with hydrogen has better combustion chamber adaptability in traditional aircraft engine combustion chambers than pure hydrogen fuel, but there are certain technical difficulties in combustion organization. Since jet fuel, as a liquid hydrocarbon fuel, needs to be atomized and evaporated before it can be mixed with air and burned, while hydrogen, as a gaseous fuel, can directly enter the combustion chamber and mix with air for reaction, the combustion of the two fuels requires coordination of the injection and mixing positions of the fuels to make the mixing more uniform, the combustion more stable, and less likely to have local high temperature areas. In addition, the two fuels have different phases, and the combustion characteristics such as ignition delay time and flame propagation speed are also very different.

[0005] The existing liquid hydrocarbon fuel hydrogen-blended combustion organization technology is mainly divided into large-scale swirl combustion and micro-scale mixed combustion, and is further divided into diffusion combustion and premixed combustion according to the mixing of air and fuel. The existing micro-scale mixed combustion organization technology can divide the large-scale flame into multiple small-scale flames, effectively reducing the occurrence of local high temperature, thereby reducing NO X The large-scale swirl combustion organization mode has the advantages of being suitable for traditional combustion chambers, low NO X It has advantages such as low emissions and is the preferred option that has good adaptability to both hydrogen and aviation kerosene fuels.

[0006] The existing large-scale swirl combustion technology can be further divided into two categories: diffusion combustion and premixed combustion. In the diffusion combustion mode, the mixing of air and fuel is not sufficient, and there is still NO X The disadvantage is high pollutant emissions.

[0007] Currently, there are few technologies for large-scale swirl configuration aviation kerosene hydrogen combustion. The Chinese invention patent with the announcement number "CN103277813B" discloses "a low-pollution combustion chamber for hydrogenation and emission reduction in aviation fuel combustion". The combustion chamber discloses a staged premixed lean combustion organization mode, in which hydrogen plays an auxiliary role in combustion, widens the lean combustion limit, and reduces lean NO. X The effect of emissions is more in line with the requirements of modifications based on traditional aircraft engine combustion chambers, but there is a problem of relatively low available hydrogen blending, and hydrogen is not the main fuel.

[0008] There are many technical inventions for the addition of hydrogen to gas turbines. The Chinese invention patent with publication number "CN104870902A" discloses a "gas turbine burner suitable for multiple fuels". The burner discloses a large-scale swirl nozzle design for the mixture of natural gas and hydrogen, with low NO X However, since natural gas is a gaseous fuel and aviation kerosene is a liquid fuel, the above technologies do not fully have the reference value for the combustion of liquid hydrocarbon fuels blended with hydrogen, and the relevant designs of liquid aviation kerosene blended with hydrogen combustion nozzles are still relatively scarce. Summary of the invention

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

[0010] In a first aspect, the present application provides a liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle, comprising: an aviation kerosene centrifugal nozzle; a venturi, the venturi being coaxially arranged with the aviation kerosene centrifugal nozzle, the outlet of the venturi and the outlet of the aviation kerosene centrifugal nozzle facing the same axial direction, and the outlet of the venturi forming a nozzle outlet; a plurality of radial swirlers, the radial swirlers being arranged radially outside the aviation kerosene centrifugal nozzle, the radial swirlers comprising radial channels and axial channels connected to each other; a plurality of swirl blades in an annular array are arranged in the radial channels; a plurality of hydrogen injection holes, the radial channels of the radial swirler farthest from the nozzle outlet being connected to the hydrogen injection holes, the plurality of hydrogen injection holes being arranged in an annular array around the central axis of the radial swirler; wherein, the radial channels of the plurality of radial swirlers, as they are further away from the nozzle outlet, the corresponding axial channels are closer to the central axis of the radial swirlers.

[0011] As a further improvement of the present application, the radial swirler includes a first-stage radial swirler and a second-stage radial swirler, the first-stage radial swirler includes a first-stage swirl channel, the first-stage swirl channel includes a first radial channel and a first axial channel that are vertically connected to each other, the second-stage radial swirler includes a second-stage swirl channel, the second-stage swirl channel includes a second radial channel and a second axial channel that are vertically connected to each other; the swirl blades include a plurality of first blades in the first-stage radial swirler, and also include a plurality of second blades in the second-stage radial swirler; 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 swirler is less than the radial distance from the second axial channel to the central axis of the radial swirler.

[0012] As a further improvement of the present application, all hydrogen injection holes are collectively covered with a hydrogen storage chamber on one side facing away from the radial cyclone, and the hydrogen storage chamber is connected to a hydrogen inlet pipe on one side facing away from the radial cyclone, and the hydrogen inlet pipe is arranged in parallel with the aviation kerosene centrifugal nozzle.

[0013] As a further improvement of the present application, along the axial perspective of the radial swirler, the first blades and the second blades 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 swirl blade does not intersect with the central axis of the radial swirler, and along the axial perspective of the radial swirler, the extension line of the swirl blade itself is tangent to or intersecting with the inner wall of the outer ring of the axial channel.

[0014] As a further improvement of the present application, along the axial perspective of the radial swirler, each of the swirl blades extends in a straight direction, and the swirl direction of the first blade and the swirl direction of the second blade are both clockwise or counterclockwise; the blade angle of the first blade is smaller than the blade angle of the second blade.

[0015] As a further improvement of the present 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 the present 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 the hydrogen injection holes is 6 to 10; the axial dimension of the swirl blade is 1.2 mm to 3.0 mm, and the number of swirl blades in each radial cyclone is 6 to 12.

[0017] As a further improvement of the present application, the hydrogen storage chamber is surrounded by a first radial plate, a second radial plate and a first axial tube, which are parallel to each other, and the aviation kerosene centrifugal nozzle. The hydrogen injection hole penetrates the second radial plate, and the hydrogen inlet pipe penetrates the first radial plate; a third radial plate and a fourth radial plate are arranged in parallel in the direction of 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 path, and the space between the third radial plate and the fourth radial plate is the second radial path; the space between the inner wall of the venturi tube and the outer wall of the aviation kerosene centrifugal nozzle forms the first axial path; a second axial tube is also fixed to a side of the third radial plate away from the second radial plate, and the space between the inner wall of the second axial tube and the outer wall of the venturi tube forms the second axial path.

[0018] As a further improvement of the present application, the outlet of the axial end of the second axial tube and the outlet of the axial end of the venturi are at the same axial position; the outlet of the aviation kerosene centrifugal nozzle is located upstream of the outlet of the venturi.

[0019] In a second aspect, a method for mixing and burning liquid hydrocarbon fuel with hydrogen using 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 hole is hydrogen; the air generates a 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 generated mixed gas of the air and the fuel passes through the venturi and enters the combustion chamber.

[0020] As a further improvement of the present application, the particle diameter of the spray of aviation kerosene sprayed from the aviation kerosene centrifugal nozzle is 30 μm to 100 μm, and the cone angle of the spray is in the range of 45° to 80°.

[0021] The beneficial effects of the liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application include: good adaptability to the combustion chamber of the traditional aircraft engine, and the basic layout of multiple radial swirlers, hydrogen injection holes and centrally arranged aviation kerosene centrifugal nozzles can be used as a separate head in the full-ring combustion chamber. First, the swirl blades inside each radial swirler can cause the passing fluid to generate swirl and form a recirculation zone in the combustion chamber. The radial channel can first guide the fluid radially inward, and then use the axial channel to change the direction of the fluid to the axial direction. Secondly, the hydrogen injection holes arranged in an annular array can spray hydrogen at multiple locations, which is conducive to subsequent uniform mixing. Thirdly, the radial swirler farthest from the nozzle outlet is connected to the hydrogen injection hole and is located at the upstream, which can achieve the mixing of air and hydrogen, ensure the uniformity of mixing, and atomize the liquid aviation kerosene of the aviation kerosene centrifugal nozzle. From this, the radial swirler relatively close to the nozzle outlet is located relatively downstream, which is convenient for forming a swirl zone in the main combustion chamber to play a role in stabilizing combustion. Finally, the resulting air and fuel mixture can enter the combustion chamber through a venturi, which can also prevent backfire. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments, the drawings of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0023] Figure 1 It is an axial view of an embodiment of a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application;

[0024] Figure 2 This application Figure 1 AA cross-sectional view of a multi-stage radial swirl nozzle for hydrogenation of liquid hydrocarbon fuel;

[0025] Figure 3 It is a front view of an embodiment of a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application;

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

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

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

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

[0030] Figure 8 It is a three-dimensional diagram of an embodiment of a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application;

[0031] Fig. 9 It is a quarter cross-sectional view of an embodiment of a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application;

[0032] Fig.10 It is a quarter cross-sectional view of an embodiment of a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application;

[0033] Fig.11 It is a fluid simulation diagram of the operating state of an embodiment of the liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application.

[0034] Description of Reference Numerals

[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-aviation 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-fillet; α-first blade angle; β-second blade angle; F-inner wall of outer ring; G-central main recirculation zone; H-step recirculation zone; I-shear layer; J-angular recirculation zone. DETAILED DESCRIPTION

[0036] The exemplary embodiments of the present application are described below with reference to the accompanying drawings. It should be understood that these specific descriptions are only used to teach those skilled in the art how to implement the present application, and are not intended to exhaust all possible methods of the present application, nor to limit the scope of the present application.

[0037] The liquid hydrocarbon fuel hydrogenated multi-stage radial swirl nozzle and the liquid hydrocarbon fuel hydrogenated multi-stage radial swirl nozzle mixing and combustion method of the present application are further described in detail below in conjunction with specific embodiments.

[0038] See also Fig. 9 The liquid hydrocarbon fuel hydrogen-doped multi-stage radial swirl nozzle of the present application may include: an aviation kerosene centrifugal nozzle 8, a venturi 15, a hydrogen injection hole 7, and a plurality of radial swirlers. The venturi 15 is coaxially arranged with the aviation kerosene centrifugal nozzle 8, and the outlets of the venturi 15 and the aviation kerosene centrifugal nozzle 8 are oriented in the same axial direction (i.e., Fig. 9 The outlet of the venturi tube 15 forms the nozzle outlet 17. A plurality of radial swirlers are coaxially arranged radially outside the aviation kerosene centrifugal nozzle 8, and each radial swirler includes a radial channel and an axial channel that are interconnected; a plurality of swirl blades are arranged in the radial channel, and the plurality of swirl blades are arranged in a circular array around the central axis of the radial swirler. The radial channel of the radial swirler farthest from the nozzle outlet 17 is connected to the hydrogen injection hole 7, such as Figure 4 As shown, a plurality of hydrogen injection holes 7 are arranged in a circular array around the central axis of the radial swirler. The farther away the radial channel in the radial swirler is from the nozzle outlet 17, the closer the corresponding axial channel is to the central axis of the radial swirler.

[0039] like Fig. 9 , Fig.10 As shown, in order to facilitate the display of the internal structure, from the visual effect of the attached figure, Fig. 9 , Fig.10 The fan-shaped area of ​​the liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application is cut off by one quarter. In fact, the three-dimensional image of the complete liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle of the present application is still as shown in FIG. Figure 8 shown.

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

[0041] The beneficial effects of the above embodiment are: using a nozzle configuration similar to that used in a conventional aircraft engine combustion chamber, and using a two-stage radial swirler to introduce air, the air passing through the first-stage radial swirler 3 mainly plays the role of mixing with hydrogen, atomizing liquid aviation kerosene, etc., while the air passing through the second-stage radial swirler 4 mainly plays the role of forming a swirl zone in the main combustion chamber to stabilize combustion. Fig.11 In the simulation shown, the combustion zone formed includes a shear layer I and a central main reflow zone G, which is similar to the combustion chamber of a conventional aircraft engine. Due to the similar structure, the nozzle pressure drop and head weight generated are similar to those of a conventional aviation kerosene nozzle. At the same time, a step reflow zone H is formed near the outlet edge of the venturi 15, and an angle reflow zone J is formed further outside the shear layer I. In general, it has good compatibility with the combustion chamber of a conventional aircraft engine.

[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 swirler is less than the radial distance from the second axial channel 102 to the central axis of the radial swirler. 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 swirl blades include a plurality of first blades 31 in the first-stage radial swirler 3 , and a plurality of second blades 41 in the second-stage radial swirler 4 .

[0044] In one embodiment, along the axial perspective of the radial swirler, the first blade 31 and the second blade 41 are arranged alternately, that is, the axial projections of the first blade 31 and the second blade 41 do not overlap. That is, the staggered arrangement of the first blade 31 and the second blade 41 can moderately reduce the resistance during air intake. At the same time, 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 along the extension direction perpendicular to the central axis of the radial swirler is greater than the length of the second blade 41 along the extension direction perpendicular to the central axis of the radial swirler.

[0045] like Figure 5 and Figure 6 As shown, the extension direction of the first blade 31 and the second blade 41 does not intersect with the central axis of the radial cyclone. From the axial perspective of the radial cyclone, the extension line of the swirl blade itself may be intersecting with the inner wall F of the outer ring of the axial path where it is located, or may be tangential, and 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 vertical distance between the plane where each swirl blade is located and the central axis of the radial cyclone is equal.

[0046] like Figure 5 , Figure 6 As shown, in one embodiment, from an axial perspective of the radial swirler, each swirl blade extends in a straight line, and the swirl directions of the first blade 31 and the second blade 41 are both in the clockwise direction or the counterclockwise direction.

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

[0048] When viewed along the axial direction, the swirl direction of the first blade 31 and the second blade 41 is the same. 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 of which are clockwise.

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

[0050] In one embodiment, the blade rotation angle of the first blade 31 may be smaller than the blade rotation angle of the second blade 41. An auxiliary line is drawn from the nozzle axis of the present application, and the auxiliary line contacts the inner end of the swirl blade. The angle between the swirl 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 shown in 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 in a straight line. In a non-limiting example, the surface of the swirl blade can also be a curved surface, and the curved swirl blade can reduce air resistance. Depending on the design formula of the curved surface and numerical calculation, the specific curved surface shape of the swirl blade can be iteratively improved.

[0052] In one embodiment, all hydrogen injection holes 7 are covered with a hydrogen storage chamber 6 on one side away from the radial cyclone, and a hydrogen inlet pipe 5 is connected to the side of the hydrogen storage chamber 6 away from the radial cyclone. The hydrogen inlet pipe 5 is arranged in parallel with 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 the axial projections of the hydrogen inlet pipe 5 and the aviation kerosene centrifugal nozzle 8 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 inner wall cross-sectional profile of the hydrogen injection hole 7 can be circular. The hydrogen injection hole 7 is a straight injection hole. When actually selected, the size and position of the hydrogen injection hole 7 can be adjusted according to the configuration of the combustion chamber, standard working 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 ranges from 7 mm to 10 mm, and the number of the hydrogen injection holes 7 is 6 to 10.

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

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

[0057] like Figure 2 As shown, the nozzle outlet 17 includes both a first outlet 171 corresponding to the outlet of the venturi tube 15 and a second outlet 172 corresponding to the outlet of the second axial channel 102. In addition, the inner wall of the venturi tube 5 first contracts and then gradually expands, and the inner wall of the venturi tube 5 protrudes with a venturi throat 151 (see Fig. 9 ), the inner diameter corresponding to the venturi throat 151 is the minimum inner diameter of the venturi 5.

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

[0059] The beneficial effect of adopting the above embodiment is that a Venturi tube 15 structure is provided at the downstream position of the axial channel outlet of the first-stage swirl channel 9, which can make the air and fuel mixture spray out at a higher speed, so that the combustion is stabilized at the downstream position of the nozzle outlet 17, and has a certain anti-backfire ability.

[0060] In one embodiment, if Fig. 9 , Fig.10 As shown, the corner between the first radial track 91 and the first axial track 92 is transitioned through a fillet 24. Similarly, the corner between the second radial track 101 and the second axial track 102 is also transitioned through a fillet 24. The female corner at the corner is transitioned through an inner fillet, and the male corner at the corner is transitioned through an outer fillet.

[0061] like Fig. 9 , Fig.10 As shown, in one embodiment, the axial end edges of the venturi tube 5 and the axial end edges of the second axial tube 23 also transition through the fillet 24, and the axial end edges of the venturi tube 5 and the second axial tube 23 transition through the outer fillet.

[0062] The present application also provides a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle blending combustion method, which includes: using air as an oxidant, using aviation kerosene and hydrogen 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 aviation kerosene centrifugal nozzle 8 is aviation kerosene; the flow medium in the hydrogen injection hole 7 is hydrogen. Hydrogen and air are mixed in the first-stage swirl channel 9. The aviation kerosene is atomized, and the resulting air and fuel mixture passes through the venturi 15 and enters the combustion chamber. The airflow entering the two swirl channels passes through the first-stage swirl channel 9 and the second-stage swirl channel 10 respectively and generates a swirl, forming a recirculation zone in the combustion chamber.

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

[0064] The liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle mixing and combustion method of the present application is equivalent to being divided into a supply zone, a nozzle entity and a downstream combustion zone.

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

[0066] The first radial channel 91 in the first-stage swirl channel 9 is arranged upstream, and the flow direction of the first axial channel 92 is axial. The first axial channel 92 is located radially inwardly of the first radial channel 91. The air enters from the first-stage swirler inlet 1 and passes through the first-stage radial swirler 3, and is mixed with the hydrogen sprayed from the hydrogen injection hole 7, and atomizes the liquid kerosene sprayed from the aviation kerosene centrifugal nozzle 8, and then enters the combustion chamber after passing through the venturi 15 to generate reflux, and mainly reacts with hydrogen in the shear layer I to form a stable jet shear layer flame, and mainly reacts with kerosene vapor in the reflux zone to form a flame.

[0067] The nozzle entity includes a first-stage radial swirler 3, a second-stage radial swirler 4, an aviation kerosene centrifugal nozzle 8, and a hydrogen injection hole 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 in the prior art, which is not shown in detail in the drawings.

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

[0069] The liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle blending combustion method of the present application can achieve a wide range of hydrogen blending ratio control. Under the premise of meeting the basic requirement of non-ablation head nozzle, the benchmark working condition can be achieved, and the hydrogen blending ratio can reach 60%. Under the condition of ensuring compatibility with traditional combustion chambers, it belongs to a wide range of hydrogen blending ratio control that can be achieved, and the fuel use flexibility is high in actual applications.

[0070] The above embodiments are only for illustrating the technical concept and features of the present application, and their purpose is to enable people familiar with this technology to understand the content of the present application and implement it. They cannot be used to limit the scope of protection of the present application. All equivalent changes or modifications made according to the spirit of the present application should be included in the scope of protection of the present application.

Claims

1. A liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle, characterized in that: include: Aviation kerosene centrifugal nozzle (8); a venturi tube (15), the venturi tube (15) being coaxially arranged with the aviation kerosene centrifugal nozzle (8), the outlet of the venturi tube (15) and the outlet of the aviation kerosene centrifugal nozzle (8) facing the same axial direction, and the outlet of the venturi tube (15) forming a nozzle outlet (17); A plurality of radial swirlers, the radial swirlers being arranged radially outside the aviation kerosene centrifugal nozzle (8), the radial swirlers comprising a radial channel and an axial channel which are interconnected; a plurality of swirling blades in an annular array are arranged in the radial channel; a plurality of hydrogen injection holes (7), the radial channel of the radial swirler farthest from the nozzle outlet (17) being in communication with the hydrogen injection hole (7), the plurality of hydrogen injection holes (7) being arranged in an annular array around the central axis of the radial swirler; The further away the radial paths in the plurality of radial swirlers are from the nozzle outlet (17), the closer the corresponding axial paths are to the central axis of the radial swirlers.

2. The liquid hydrocarbon fuel hydrogen-blending multi-stage radial swirl nozzle according to claim 1, characterized in that: 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 swirling channel (9); the first-stage swirling channel (9) comprises a first radial channel (91) and a first axial channel (92) which are vertically connected to each other; the second-stage radial swirler (4) comprises a second-stage swirling channel (10); the second-stage swirling channel (10) comprises a second radial channel (101) and a second axial channel (102) which are vertically connected to each other; The swirl blades include a plurality of first blades (31) in the first-stage radial swirler (3), and also include a plurality of second blades (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); the radial distance from the first axial channel (92) to the central axis of the radial swirler is less than the radial distance from the second axial channel (102) to the central axis of the radial swirler.

3. The liquid hydrocarbon fuel hydrogen-blending multi-stage radial swirl nozzle according to claim 2, characterized in that: A side of all hydrogen injection holes (7) facing away from the radial cyclone is commonly covered with a hydrogen storage chamber (6), a side of the hydrogen storage chamber (6) facing away from the radial cyclone is connected to a hydrogen inlet pipe (5), and the hydrogen inlet pipe (5) is arranged in parallel with the aviation kerosene centrifugal nozzle (8).

4. The multi-stage radial swirl nozzle for hydrogenation of liquid hydrocarbon fuel according to claim 2, characterized in that: From an axial perspective of the radial swirler, the first blades (31) and the second blades (41) are arranged alternately and spaced apart; the length of the first blades (31) is greater than the length of the second blades (41); The extension direction of the swirl blade does not intersect with the central axis of the radial swirler. From the axial perspective of the radial swirler, the extension line of the swirl blade itself is tangent to or intersects with the inner wall (F) of the outer ring of the axial channel.

5. The multi-stage radial swirl nozzle for hydrogenation of liquid hydrocarbon fuel according to claim 2, characterized in that: From an axial perspective of the radial swirler, each of the swirl blades extends in a straight line, and the swirl direction of the first blade (31) and the swirl direction of the second blade (41) are both clockwise or counterclockwise; The blade rotation angle of the first blade (31) is smaller than the blade rotation angle of the second blade (41).

6. The multi-stage radial swirl nozzle for hydrogenation of liquid hydrocarbon fuel according to claim 2, characterized in that: 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°.

7. The multi-stage radial swirl nozzle for hydrogenation of liquid hydrocarbon fuel according to claim 1, characterized in that: The inner diameter of the hydrogen injection hole (7) is 0.6 mm to 1.0 mm, the vertical distance between the hydrogen injection hole (7) and the central axis of the radial cyclone is 7 mm to 10 mm, and the number of the hydrogen injection holes (7) is 6 to 10; The axial dimension of the swirl blade is 1.2 mm to 3.0 mm, and the number of the swirl blades in each radial swirler is 6 to 12.

8. The multi-stage radial swirl nozzle for hydrogenation of liquid hydrocarbon fuel according to claim 3, characterized in that: The hydrogen storage chamber (6) is surrounded by a first radial plate (18), a second radial plate (20) and a first axial tube (19) which are parallel to each other, and the aviation kerosene centrifugal nozzle (8); 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 sequentially arranged in parallel 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 path (91); and a space between the third radial plate (21) and the fourth radial plate (22) is the second radial path (101); The space between the inner wall of the venturi tube (15) and the outer wall of the aviation kerosene centrifugal nozzle (8) forms the first axial channel (92); A second axial tube (23) is also fixed to a side of the third radial plate (21) facing away from the second radial plate (20), and the space between the inner wall of the second axial tube (23) and the outer wall of the Venturi tube (15) forms the second axial channel (102).

9. The liquid hydrocarbon fuel hydrogen-blending multi-stage radial swirl nozzle according to claim 8, characterized in that: The outlet of the axial end of the second axial tube (23) and the outlet of the axial end of the Venturi tube (15) are located at the same axial position; The outlet of the aviation kerosene centrifugal nozzle (8) is located at a position further upstream than the outlet of the venturi tube (15).

10. A method for mixing and burning liquid hydrocarbon fuel with hydrogen using a multi-stage radial swirl nozzle, characterized in that: It uses a liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle according to any one of claims 2 to 6, 8, and 9, and the liquid hydrocarbon fuel hydrogen-blended multi-stage radial swirl nozzle blending and combustion method comprises: Air is used as an oxidant, and aviation 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 aviation kerosene centrifugal nozzle (8) is aviation kerosene; and the flow medium in the hydrogen injection hole (7) is hydrogen; The air generates swirl after passing through the first-stage swirl channel (9) and the second-stage swirl channel (10) respectively, and forms a reflow zone in the combustion chamber; The hydrogen and the air are mixed in the first-stage swirl channel (9); The aviation kerosene is atomized, and the generated mixed gas of the air and the fuel passes through the venturi (15) and then enters the combustion chamber.

11. The method for mixing and burning liquid hydrocarbon fuels with hydrogen through a multi-stage radial swirl nozzle according to claim 10, characterized in that: The particle diameter of the spray of the aviation kerosene sprayed from the aviation kerosene centrifugal nozzle (8) is 30 μm to 100 μm, and the cone angle of the spray is in the range of 45° to 80°.

Images