Cross-flow structure engine, aircraft and method

Abstract

The present disclosure relates to the field of aerospace technology, and in particular to an engine, aircraft and method with a cross-flow structure, in order to solve the problem of low combustion efficiency caused by poor lateral space utilization and oil-gas mixing effect in the prior art. The engine with a cross-flow structure comprises: an injection unit, a combustion chamber, a fractal cross-flow assembly and a tail nozzle, the injection unit, the combustion chamber and the tail nozzle are connected in sequence, and the fractal cross-flow assembly is arranged in a ring on the outer wall of the combustion chamber; the fractal cross-flow assembly comprises a cross-flow structural member and a plurality of guide members, the cross-flow structural member is distributed in a sinusoidal curve on the outer wall of the combustion chamber, the cross-flow structural member is connected to the air inlet of the combustion chamber, and each guide member is arranged in the cross-flow structural member to change the deflection angle of the air flowing into the combustion chamber. The engine, aircraft and method with a cross-flow structure provided by the present disclosure are used to maximize the utilization of the lateral space of the engine, improve the atomization performance and enhance the oil-gas mixing.

Description

Technical Field

[0001] The present disclosure relates to the field of aerospace technology, and in particular to an engine, an aircraft, and a method having a cross-flow structure. Background Art

[0002] The thrust chamber, as the core component of a liquid rocket engine, is mainly composed of injectors, combustion chambers and nozzles. The performance of the injectors plays a decisive role in the overall performance of the engine.

[0003] Currently, common injector types include direct current, centrifugal, and coaxial tube types. While direct current injectors offer a simple structure, they suffer from significant deficiencies in propellant atomization, making them difficult to meet the requirements for efficient combustion. Centrifugal injectors, through their specialized design, create a swirling flow in the propellant, forming a wide-angle conical spray upon injection into the combustion chamber. This significantly improves atomization compared to direct current injectors. However, these injectors suffer from complex structure and large size, and the spray cone angle is limited to the space surrounding the injector, resulting in limited improvement in oil-gas mixing and inability to fully utilize the combustion chamber's spatial efficiency. Coaxial tube injectors utilize the velocity difference between the inner and outer tubes to create a shear layer, breaking the liquid stream into small droplets and improving propellant atomization to some extent. However, in practice, the lateral movement of oil and gas relies primarily on diffusion, which inadequately utilizes the lateral space and prevents further enhancement of oil-gas mixing, thus limiting improvements in engine combustion efficiency.

[0004] Therefore, how to solve the problem of low combustion efficiency caused by poor lateral space utilization and oil-gas mixing effect in the existing technology is one of the important issues that need to be solved urgently in this field. Summary of the Invention

[0005] In view of this, the embodiments of the present disclosure provide an engine, an aircraft, and a method with a cross-flow structure to solve the problem of low combustion efficiency caused by poor lateral space utilization and oil-gas mixing effect in the prior art.

[0006] According to one aspect of the present disclosure, a cross-flow engine is provided, comprising: an injection unit, a combustion chamber, a fractal cross-flow assembly, and a tail nozzle, wherein the injection unit, the combustion chamber, and the tail nozzle are sequentially connected, and the fractal cross-flow assembly is annularly arranged on the outer wall of the combustion chamber;

[0007] The fractal cross-flow component includes a cross-flow structure and multiple guide members. The cross-flow structure is distributed in a sinusoidal curve on the outer wall of the combustion chamber. The cross-flow structure is connected to the air inlet of the combustion chamber. Each guide member is arranged in the cross-flow structure to change the deflection angle of the air flowing into the combustion chamber.

[0008] In addition, in the engine with a cross-flow structure according to one aspect of the present disclosure, the cross-flow structure includes a plurality of sub-cross-flow structures, and the outer contour of each sub-cross-flow structure is a sinusoidal curve and is arranged along the circumference of the combustion chamber.

[0009] In the engine with a cross-flow structure according to one aspect of the present disclosure, each sub-cross-flow structure is a hollow structure.

[0010] In an engine with a cross-flow structure according to one aspect of the present disclosure, each sub-cross-flow structure has a different amplitude.

[0011] In an engine with a cross-flow structure according to one aspect of the present disclosure, the period of each sub-cross-flow structure is different.

[0012] In the cross-flow structure engine according to one aspect of the present disclosure, each sub-cross-flow structure has a different phase.

[0013] According to another aspect of the present disclosure, an aircraft is provided, comprising the above-mentioned engine with a cross-flow structure.

[0014] According to another aspect of the present disclosure, a method for using a cross-flow engine is provided, which is used in the above-mentioned aircraft. The method for using a cross-flow engine includes:

[0015] Determine the position information of the fractal cross-flow component according to the position information of the injection unit;

[0016] When the position information of the fractal cross-flow component is determined, the number of sub-cross-flow structural components is determined based on the interference factor;

[0017] Determining trajectory parameters of the cross-flow structure according to each sub-cross-flow structure;

[0018] The trajectory of the cross-flow structure is determined based on the trajectory parameters.

[0019] According to an aspect of the present disclosure, the method for using an engine with a cross-flow structure further includes determining the trajectory parameters of the cross-flow structure according to each sub-cross-flow structure:

[0020] Create a trajectory curve function based on trajectory parameters:

[0021]

[0022] Where x is the circumferential angle, A i is the amplitude of the i-th sine curve, w i is the angular velocity of the i-th sine curve, k i is the initial phase angle of the i-th curve, and the b value is used to adjust the axial position of the entire curve.

[0023] According to an aspect of the present disclosure, the method for using an engine with a cross-flow structure further includes: determining the number of flow guides according to an interference factor.

[0024] At least one of the above-mentioned technical solutions employed in the disclosed embodiments can achieve the following beneficial effects: In the cross-flow engine, the injection unit, combustion chamber, and tail nozzle are sequentially connected. The fractal cross-flow assembly is annularly arranged on the outer wall of the combustion chamber. The cross-flow structural members are distributed sinusoidally on the outer wall of the combustion chamber, thereby expanding the cross-flow's impact area. Based on this, the cross-flow structural member is connected to the air inlet of the combustion chamber. Each guide member is disposed within the cross-flow structural member and is used to change the deflection angle of air flowing into the combustion chamber. The guide members of the fractal cross-flow assembly change the air deflection angle, allowing the air entering the combustion chamber to mix more fully and evenly with the fuel ejected from the injection unit. Furthermore, the increased cross-flow fully utilizes the cross-flow space, resulting in a uniform temperature distribution in the high-temperature zone and significantly enhanced fuel-gas mixing. Furthermore, the air flows into the combustion chamber at a specific angle, forming a more rational airflow organization within the combustion chamber, which helps stabilize the flame, making the combustion process more continuous and efficient, and reducing problems such as incomplete combustion and localized overheating. This effectively solves the problem of low combustion efficiency in the prior art due to poor cross-flow space utilization and fuel-gas mixing. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0026] Figure 1 A schematic diagram illustrating the structure of an engine to which a cross-flow structure according to an embodiment of the present disclosure is applied;

[0027] Figure 2 is a schematic structural diagram illustrating an injection unit according to an embodiment of the present disclosure;

[0028] Figure 3 is a schematic diagram illustrating the axial position structure of an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0029] Figure 4 Further illustrating a structural schematic diagram of a sinusoidal cross-flow structure according to an embodiment of the present disclosure;

[0030] Figure 5 A schematic diagram of a profile curve of a single sub-cross-flow structural member according to an embodiment of the present disclosure is further illustrated;

[0031] Figure 6Further illustrating a schematic structural diagram of a dual sinusoidal cross-flow structure according to an embodiment of the present disclosure;

[0032] Figure 7 Further illustrating a schematic diagram of contour curves of multiple sub-cross-flow structural members according to an embodiment of the present disclosure;

[0033] Figure 8 Further illustrating a schematic diagram of the spatial mixing principle of an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0034] Figure 9 Further illustrating a schematic diagram of engine temperature distribution in a cross-flow configuration according to an embodiment of the present disclosure;

[0035] Figure 10 Further illustrating a schematic diagram of fractal cross-flow area distribution of an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0036] Figure 11 Further illustrating a schematic diagram of kerosene distribution of an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0037] Figure 12 Further illustrating a flow chart of a method for using an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0038] Figure 13 Further illustrating a schematic top view of the structure of an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0039] Figure 14 A schematic diagram of the setting position of the guide member according to an embodiment of the present disclosure is further illustrated.

[0040] Reference numerals:

[0041] 1-injection unit, 2-fractal cross-flow assembly, 21-cross-flow structure, 211-sub-cross-flow structure, 22-flow guide, 3-combustion chamber, 4-tail nozzle. DETAILED DESCRIPTION

[0042] The following describes embodiments of the present disclosure in more detail with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as limited to the embodiments described herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are for illustrative purposes only and are not intended to limit the scope of protection of the present disclosure.

[0043] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0044] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". The relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0045] It should be noted that the modifications of "one" and "multiple" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, they should be understood as "one or more".

[0046] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0047] The thrust chamber, as the core component of a liquid rocket engine, is mainly composed of injectors, combustion chambers and nozzles. The performance of the injectors plays a decisive role in the overall performance of the engine.

[0048] Currently, common injector types include direct current, centrifugal, and coaxial tube types. While direct current injectors offer a simple structure, they suffer from significant deficiencies in propellant atomization, making them difficult to meet the requirements for efficient combustion. Centrifugal injectors, through their specialized design, create a swirling flow in the propellant, forming a wide-angle conical spray upon injection into the combustion chamber. This significantly improves atomization compared to direct current injectors. However, these injectors suffer from complex structure and large size, and the spray cone angle is limited to the space surrounding the injector, resulting in limited improvement in oil-gas mixing and inability to fully utilize the combustion chamber's spatial efficiency. Coaxial tube injectors utilize the velocity difference between the inner and outer tubes to create a shear layer, breaking the liquid stream into small droplets and improving propellant atomization to some extent. However, in practice, the lateral movement of oil and gas relies primarily on diffusion, which inadequately utilizes the lateral space and prevents further enhancement of oil-gas mixing, thus limiting improvements in engine combustion efficiency.

[0049] In response to the above problems, exemplary embodiments of the present disclosure provide an engine, an aircraft, and a method with a cross-flow structure to solve the problem of low combustion efficiency in the prior art due to poor lateral space utilization and oil-gas mixing effect.

[0050] An engine with a cross-flow structure according to an embodiment of the present disclosure will be described in detail below with reference to the accompanying drawings.

[0051] Figure 1 FIG2 is a schematic diagram of the structure of an engine using a cross-flow structure according to an embodiment of the present disclosure. Figure 2 is a schematic structural diagram illustrating an injection unit 1 according to an embodiment of the present disclosure, Figure 3 FIG is a schematic diagram illustrating the axial position structure of an engine with a cross-flow structure according to an embodiment of the present disclosure. Figure 1 - Figure 3 As shown, the engine with a cross-flow structure includes: an injection unit 1, a combustion chamber 3, a fractal cross-flow component 2 and a tail nozzle 4. The injection unit 1, the combustion chamber 3 and the tail nozzle 4 are connected in sequence, and the fractal cross-flow component 2 is arranged in a ring on the outer wall of the combustion chamber 3; the fractal cross-flow component 2 includes a cross-flow structural member 21 and a plurality of guide members 22. The cross-flow structural member 21 is distributed in a sinusoidal curve on the outer wall of the combustion chamber 3. The cross-flow structural member 21 is connected to the air inlet of the combustion chamber 3. Each guide member 22 is arranged in the cross-flow structural member 21 to change the deflection angle of the air flowing into the combustion chamber 3.

[0052] In practical applications, such as Figure 1 - Figure 3 As shown, the injection unit 1, combustion chamber 3, and tail nozzle 4 are connected in sequence. The fractal cross-flow assembly 2 is annularly arranged on the outer wall of the combustion chamber 3. The cross-flow structural members 21 are distributed on the outer wall of the combustion chamber 3 in a sinusoidal curve, which can expand the impact on the cross-flow influence area. Based on this, the cross-flow structural member 21 is connected to the air inlet of the combustion chamber 3. Each guide member 22 is arranged within the cross-flow structural member 21 to change the deflection angle of the air flowing into the combustion chamber 3. The guide members 22 of the fractal cross-flow assembly 2 change the air deflection angle so that the air entering the combustion chamber 3 and the fuel ejected by the injection unit 1 can be more fully and evenly mixed. The increased cross-flow makes full use of the cross-space, uniformly distributes the temperature in the high-temperature zone, and significantly enhances the oil-gas mixing effect. At the same time, the air flows into the combustion chamber 3 at a specific angle, which can form a more reasonable airflow organization in the combustion chamber 3, helping to stabilize the flame, making the combustion process more continuous and efficient, and reducing problems such as incomplete combustion and local overheating. The invention effectively solves the problem of low combustion efficiency caused by poor lateral space utilization and oil-gas mixing effect in the prior art.

[0053] For example, Figure 2 As shown, the cross-flow structure 21 includes a plurality of sub-cross-flow structures 211 , and the outer contour of each sub-cross-flow structure 211 is sinusoidally arranged along the circumference of the combustion chamber 3 .

[0054] In practical applications, Figure 4 Further illustrating a schematic structural diagram of a single sinusoidal cross-flow structure according to an embodiment of the present disclosure, as shown in FIG. Figure 4 As shown, a sinusoidal curve formed by the outer contour of a single sub-cross-flow structure 211, a single sinusoidal curve function y = A1sin(w1x+k1)+b, wherein x is the circumferential angle, A1 is the amplitude of the first sinusoidal curve, w1 is the angular velocity of the first sinusoidal curve, k1 is the initial phase angle of the first curve, and the b value is used to adjust the axial position of the entire curve. Figure 5 Further illustrating a schematic diagram of a profile curve of a single sub-cross flow structure according to an embodiment of the present disclosure, wherein the profile curve of a single sub-cross flow structure is as shown in FIG. Figure 5 shown. Figure 6 Further illustrating the structural diagram of the dual sinusoidal cross-flow structure according to an embodiment of the present disclosure, as shown in FIG. Figure 6 As shown, the outer contours of multiple sub-cross-flow structural components constitute a sinusoidal curve, and the sinusoidal curve function y=A1sin(w1x+k1)+A2sin(w2x+k2)+b of the multiple sub-cross-flow structural components, wherein x is the circumferential angle, A1 is the amplitude of the first sinusoidal curve, A2 is the amplitude of the second sinusoidal curve, w1 is the angular velocity of the first sinusoidal curve, w2 is the angular velocity of the second sinusoidal curve, k1 is the initial phase angle of the first curve, k2 is the initial phase angle of the second curve, and the b value is used to adjust the axial position of the entire curve. Figure 7 Further illustrating a schematic diagram of the profile curves of multiple sub-cross-flow structural members according to an embodiment of the present disclosure, wherein the profile curve of a single sub-cross-flow structural member is as shown in FIG. Figure 7 As shown in the figure, a single sinusoidal profile or multiple sinusoidal profiles combined with a guide baffle can cause the airflow to flow into the combustion chamber at a certain deflection angle within the cross-flow structure. The undulating characteristics of the sinusoidal profile expand the cross-flow's impact width, thereby increasing the interaction time between the cross-flow and the injection fuel beam, further enhancing the oil-gas mixing effect.

[0055] Exemplarily, each sub-cross-flow structure is a hollow structure. It should be understood that each of the above-mentioned sub-cross-flow structures is interconnected. When the airflow flows into the combustion chamber, the airflow can flow into the combustion chamber at a certain deflection angle in the channel.

[0056] Exemplarily, the amplitude of each sub-cross-flow structure is different, the period of each sub-cross-flow structure is different, and the phase of each sub-cross-flow structure is different. Figure 8 Further illustrating the schematic diagram of the spatial mixing principle of the engine with a cross-flow structure according to an embodiment of the present disclosure, as shown in FIG. Figure 8As shown, in the structure where the cross-flow structural member is a sinusoidal curve, due to the superposition of sinusoidal curves of different amplitudes, different periods and different phases of each sub-cross-flow structural member, the local amplification of the channel is still a sinusoidal curve configuration, and the multi-layer curve undulation characteristics are used to increase the local influence width.

[0057] Figure 9 Further illustrating a schematic diagram of engine temperature distribution of a cross-flow structure according to an embodiment of the present disclosure, as shown in FIG. Figure 9 As shown, the fractal cross-flow component can also introduce a portion of the combustion exhaust gas by means of exhaust gas recirculation. This can not only enhance the oil-gas mixing through the transverse convection flow, but also reduce the oxygen concentration near the wall. Combined with the fuel film cooling method, the wall temperature of the combustion chamber can be further reduced.

[0058] Figure 10 Further illustrating a schematic diagram of the fractal cross-flow area distribution of the engine with a cross-flow structure according to an embodiment of the present disclosure, as shown in FIG. Figure 10 As shown, the cross-flow influence area can be significantly expanded without changing the width of the cross-flow channel by using the above-mentioned fractal cross-flow component. Figure 10 The red and blue areas in the figure both indicate that the airflow has a component velocity flowing toward the center, which is the effect of lateral flow. Figure 11 Further illustrating the kerosene distribution diagram of the engine with a cross-flow structure according to an embodiment of the present disclosure, as shown in FIG. Figure 11 As shown, Figure 11 The color of the fuel particles shown in the figure represents the velocity distribution in the Y direction (vertical direction). Figure 11 It can be seen that the fuel particles in the original solution are all green and have almost no movement in the Y direction, while the red and blue areas of the fuel particles in the disclosed solution indicate that the lateral flow velocity component has begun to appear even at the upstream end to the left of the cross-flow channel outlet, which also shows that the sinusoidal fractal cross-flow structure has amplified the influence on the lateral movement of the fuel particles.

[0059] The exemplary embodiments of the present disclosure provide an aircraft, including an engine with a cross-flow structure according to the exemplary embodiments of the present disclosure. It should be understood that the aircraft according to the exemplary embodiments of the present disclosure may be a drone or a manned aircraft. For example:

[0060] Compared with the prior art, the beneficial effects of the aircraft provided by the embodiments of the present disclosure refer to the beneficial effects of the engine with a cross-flow structure, which will not be described in detail here.

[0061] It should be noted that the aircraft provided in the embodiments of the present disclosure may further include a fuselage, a flight controller, etc., and the engine, flight controller, etc. are arranged in the fuselage.

[0062] The exemplary embodiment of the present disclosure also provides a method for using an engine with a cross-flow structure. Figure 12Further illustrating a flow chart of a method for using an engine with a cross-flow structure according to an embodiment of the present disclosure, as applied to the above-mentioned aircraft, the method for using an engine with a cross-flow structure includes:

[0063] S1201: Determine the position information of the fractal cross-flow assembly based on the position information of the injection unit. It should be understood that the position information of the fractal cross-flow assembly is determined based on the position information of the injection unit so that the fractal cross-flow assembly and the end of the injection unit do not overlap in the axial direction, ensuring that airflow entering from the fractal cross-flow assembly is not blocked by the injection unit.

[0064] S1202: When the position information of the fractal cross-flow assembly is determined, the number of sub-cross-flow structural components is determined based on the interference factor. It should be understood that the interference factor is the processing difficulty of the fractal cross-flow assembly and the cross-flow enhancement effect. The use of a single sine curve or the superposition of two sine curves can be determined based on actual working conditions.

[0065] S1203: Determine trajectory parameters of the cross-flow structural component according to each sub-cross-flow structural component;

[0066] S1204: Determine the trajectory of the cross-flow structural component based on the trajectory parameters.

[0067] Exemplarily, determining the trajectory parameters of each sub-cross-flow structural component further includes: establishing a trajectory curve function based on the trajectory parameters:

[0068]

[0069] Where x is the circumferential angle, A i is the amplitude of the i-th sine curve, w i is the angular velocity of the i-th sine curve, k i is the initial phase angle of the i-th curve, and the b value is used to adjust the axial position of the entire curve. It can be understood that A i is the amplitude of the i-th sine curve, which is used to control the fluctuation of the curve. i The larger the value, the greater the curve fluctuation. i is the angular velocity of the i-th sine curve, which is used to control the fluctuation period of the curve, w i The larger it is, the smaller the fluctuation period is, and the tighter the curve fluctuation is. The period is T = 2π / w i , k i is the initial phase angle of the i-th curve, which is used to control the circumferential position of the curve and can usually be 0. The b value is used to adjust the axial position of the entire curve so that the entire curve does not interfere with the extended part of the diaphragm injector. Figure 4 - Figure 7This is an example of a single sine curve and a contour curve of two superimposed sine curves. In the two superimposed sine curves, for example: A2 = 0.382A1, w2 = 9w1, k1 = k2 = 0, so the amplitude of the superimposed curve is increased by 0.382 times compared with the single curve. Within the original cycle, 9 small sine cycles are superimposed.

[0070] Exemplarily, the method for using an engine with a cross-flow structure further includes: determining the number of flow guides according to an interference factor.

[0071] In practical applications, Figure 13 Further illustrating a schematic top view of the structure of an engine with a cross-flow structure according to an embodiment of the present disclosure, Figure 14 Further illustrating a schematic diagram of the location of the guide member according to an embodiment of the present disclosure, as shown in FIG. Figure 13 - Figure 14 As shown, according to different working conditions, the appropriate number of guide pieces m is selected, generally ranging from 10 to 50. Figure 13 As shown, according to the number of guide pieces m, Figure 13 Divide the inner circle into equal parts to determine m channel center points B j , j takes values from 1 to m. Figure 13 On the inner circle of j and B j+1 The midpoint of point E j , as the root point of the jth guide, j value ranges from 1 to m. Connect point B j and the center point O, take the line segment OB j The midpoint is A j , connecting point A j and point B j+1 , and the extended line intersects the outer circle at point C j+1 The value of j ranges from 1 to m. When j is m, j+1 is 1. Point C j+1 This is the center point of the diversion channel on the outer circle. On the outer circle, take point C j and point C j+1 The midpoint F j , as the vertex of the guide baffle, j value ranges from 1 to m, when j is m, j+1 is 1. Connect point E j and point F j , line segment E j F j That is the position of the guide piece. Insert the guide piece into the cross flow channel according to the position and weld it.

[0072] Through the above design, the main flow direction of the airflow in the j+1th section of the guide channel can be towards the line segment OB j Midpoint A j Flow, without considering other factors, the cross flow reaches the midpoint A of the previous area jWhen point B j The effect is basically the same as point O, which makes the cross-flow mixing effect uniform everywhere to the maximum extent, such as Figure 13 As shown in the figure, the deflection design of the guide makes the cross flow flow to the front space area, and also avoids the situation that all cross flow flows to the center and gathers when there is no deflection design, causing the oil and gas to gather to the center and distribute unevenly. At the same time, the deflection design enables the cross flow component to expand the width of the cross flow to form the following Figure 8 The effect shown.

[0073] The above descriptions are merely some embodiments of the present disclosure and an illustration of the technical principles employed. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above-mentioned technical features, but also encompasses other technical solutions formed by any combination of the above-mentioned technical features or their equivalents without departing from the above-mentioned disclosed concepts. For example, a technical solution formed by replacing the above-mentioned features with (but not limited to) technical features with similar functions disclosed in the present disclosure.

[0074] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art will appreciate that the above examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Those skilled in the art will appreciate that modifications may be made to the above embodiments without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A method for using a cross-flow engine, characterized in that: The method for using the engine with the cross-flow structure includes: Determine the position information of the fractal cross-flow component according to the position information of the injection unit; When the position information of the fractal cross-flow component is determined, the number of sub-cross-flow structural components is determined based on the interference factor; Determining a trajectory parameter of the cross-flow structure according to each of the sub-cross-flow structures; determining a trajectory of the cross-flow structure based on the trajectory parameters; The cross-flow structure comprises a plurality of sub-cross-flow structures, and the outer contour of each sub-cross-flow structure is a sine curve and is arranged along the circumference of the combustion chamber; Each of the sub-cross-flow structural components is a hollow structure.

2. The method for using a cross-flow engine according to claim 1, characterized in that: Determining the trajectory parameters of the cross-flow structure according to each of the sub-cross-flow structures further includes: Establish a trajectory curve function based on the trajectory parameters: Where x is the circumferential angle, A i is the amplitude of the i-th sine curve, w i is the angular velocity of the i-th sine curve, k i is the initial phase angle of the i-th curve, and the b value is used to adjust the axial position of the entire curve.

3. The method for using a cross-flow engine according to claim 1, characterized in that: The method for using the engine with a cross-flow structure further includes: determining the number of flow guides according to an interference factor.

4. A cross-flow engine, characterized in that: A method for using an engine with a cross-flow structure according to any one of claims 1 to 3, wherein the engine with the cross-flow structure comprises: an injection unit, a combustion chamber, a fractal cross-flow component, and a tail nozzle, wherein the injection unit, the combustion chamber, and the tail nozzle are sequentially connected, and the fractal cross-flow component is annularly arranged on the outer wall of the combustion chamber; The fractal cross-flow assembly includes a cross-flow structure and a plurality of flow guides, wherein the cross-flow structure is distributed in a sinusoidal curve on the outer wall of the combustion chamber, the cross-flow structure is connected to the air inlet of the combustion chamber, and each flow guide is arranged in the cross-flow structure to change the deflection angle of the air flowing into the combustion chamber; The cross-flow structure comprises a plurality of sub-cross-flow structures, and the outer contour of each sub-cross-flow structure is a sine curve and is arranged along the circumference of the combustion chamber; Each of the sub-cross-flow structural components is a hollow structure.

5. The cross-flow engine according to claim 4, characterized in that: The amplitude of each of the sub-cross-flow structures is different.

6. The cross-flow engine according to claim 4, characterized in that: The period of each of the sub-cross-flow structures is different.

7. The cross-flow engine according to claim 4, characterized in that: The phase of each of the sub-cross-flow structures is different.

8. An aircraft, characterized in that: An engine comprising the cross-flow structure according to any one of claims 4 to 7.

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