Engine of cross flow structure, aircraft and method

Abstract

The invention relates to the technical field of aerospace, in particular to an engine of a transverse flow structure, an aircraft and a method, and aims to solve the problem of low combustion efficiency caused by poor transverse space utilization and oil-gas mixing effect in the prior art. The engine of the cross flow structure comprises an injection unit, a combustion chamber, a fractal cross flow assembly and an exhaust nozzle, the injection unit, the combustion chamber and the exhaust nozzle are sequentially communicated, and the fractal cross flow assembly is annularly arranged on the outer side wall of the combustion chamber; the fractal cross flow assembly comprises a cross flow structural part and a plurality of flow guide parts, the cross flow structural part is distributed on the outer side wall of the combustion chamber in a sine curve mode and communicates with an air inlet of the combustion chamber, and each flow guide part is arranged in the cross flow structural part and used for changing the deflection angle of air flowing into the combustion chamber. According to the engine of the cross flow structure, the aircraft and the method, the transverse space of the engine is utilized to the maximum extent, the atomization performance is improved, and oil-gas mixing is enhanced.

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 of a cross-flow structure. Background Art

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

[0003] At present, the common types of injectors are mainly direct current, centrifugal and coaxial tube. Although the direct current injector has a simple structure, it has obvious deficiencies in the atomization effect of the propellant and is difficult to meet the needs of efficient combustion. The centrifugal injector uses a special design to make the propellant produce a vortex flow, which can form a conical spray with a larger angle after being injected into the combustion chamber. Compared with the direct current type, the atomization effect is significantly improved. However, this type of injector has the disadvantages of complex structure and large size, and the range of its spray cone angle is limited to the limited space around the injector, which has limited improvement on the oil-gas mixing effect and cannot give full play to the spatial efficiency of the combustion chamber. The coaxial tube injector uses the velocity difference between the inner tube and the outer tube to form a shear layer, which causes the liquid flow to break into small droplets, and improves the atomization of the propellant to a certain extent. However, in actual applications, the lateral movement of oil and gas mainly depends on diffusion, which makes the lateral space insufficiently utilized and cannot further enhance the oil-gas mixing effect, thereby limiting the improvement of the 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 prior art is one of the important issues 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, there is provided an engine with a cross-flow structure, the engine with a cross-flow structure comprising: an injection unit, a combustion chamber, a fractal cross-flow component and a tail nozzle, the injection unit, the combustion chamber and the tail nozzle are connected in sequence, and the fractal cross-flow component is arranged on the outer side 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 on the outer wall of the combustion chamber in a sinusoidal curve. 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 air flowing into the combustion chamber.

[0008] In addition, in an 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 sinusoidally 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 member 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 an engine with a cross-flow structure 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 an engine with a cross-flow structure is provided, which is used for the above-mentioned aircraft, and the method for using an engine with a cross-flow structure 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 the 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] A trajectory of the cross-flow structure is determined based on the trajectory parameters.

[0019] According to an engine use method of a cross-flow structure in one aspect of the present disclosure, determining the trajectory parameters of the cross-flow structure component according to each sub-cross-flow structure component also includes:

[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 ith sine curve, w i is the angular velocity of the ith 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 technical solutions adopted in the embodiment of the present disclosure can achieve the following beneficial effects: in the engine of the above cross-flow structure, the injection unit, the combustion chamber and the tail nozzle are connected in sequence, the fractal cross-flow assembly is arranged on the outer wall of the combustion chamber, and the cross-flow structural parts are distributed on the outer wall of the combustion chamber in a sine curve, which can expand the influence on the cross-flow influence area. Based on this, the cross-flow structural part is connected to the air inlet of the combustion chamber, and each guide member is arranged in the cross-flow structural part to change the deflection angle of the air flowing into the combustion chamber. The guide member of the fractal cross-flow assembly changes the air deflection angle, so that the air entering the combustion chamber can be more fully and evenly mixed with the fuel sprayed by the injection unit, and after increasing the cross-flow, the cross-flow space is fully utilized, the temperature distribution in the high-temperature zone is uniform, and the oil-gas mixing effect is significantly enhanced. At the same time, the air flows into the combustion chamber at a specific angle, which can form a more reasonable airflow organization in the combustion chamber, which helps to stabilize the flame, make the combustion process more continuous and efficient, and reduce problems such as incomplete combustion and local overheating. It effectively solves the problem of low combustion efficiency caused by poor cross-flow space utilization and oil-gas mixing effect in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 paying 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 diagram illustrating the structure of 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 schematic structural diagram of a sinusoidal cross-flow structure according to an embodiment of the present disclosure;

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

[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 a plurality of 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] Fig. 9 Further illustrating a schematic diagram of engine temperature distribution in a cross-flow structure according to an embodiment of the present disclosure;

[0035] Fig.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] Fig.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] Fig.12 Further illustrating a schematic flow chart of a method for using an engine with a cross-flow structure according to an embodiment of the present disclosure;

[0038] Fig.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] Fig.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] Embodiments of the present disclosure will be described in more detail below 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 being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes 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". 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 "plurality" 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, it 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] As the core component of a liquid rocket engine, the thrust chamber is mainly composed of injectors, a combustion chamber and a nozzle. The performance of the injectors plays a decisive role in the overall performance of the engine.

[0048] At present, the common types of injectors are mainly direct current, centrifugal and coaxial tube. Although the direct current injector has a simple structure, it has obvious deficiencies in the atomization effect of the propellant and is difficult to meet the needs of efficient combustion. The centrifugal injector uses a special design to make the propellant produce a vortex flow, which can form a conical spray with a larger angle after being injected into the combustion chamber. Compared with the direct current type, the atomization effect is significantly improved. However, this type of injector has the disadvantages of complex structure and large size, and the range of its spray cone angle is limited to the limited space around the injector, which has limited improvement on the oil-gas mixing effect and cannot give full play to the spatial efficiency of the combustion chamber. The coaxial tube injector uses the velocity difference between the inner tube and the outer tube to form a shear layer, which causes the liquid flow to break into small droplets, and improves the atomization of the propellant to a certain extent. However, in actual applications, the lateral movement of oil and gas mainly depends on diffusion, which makes the lateral space insufficiently utilized and cannot further enhance the oil-gas mixing effect, thereby limiting the improvement of the engine combustion efficiency.

[0049] In view of 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 caused by poor lateral space utilization and oil-gas mixing effect in the prior art.

[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 FIG. 1 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 diagram illustrating the structure of the injection unit 1 according to an embodiment of the present disclosure, Figure 3 Schematic diagram of the axial position structure of the engine of the cross-flow structure according to the 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, and the cross-flow structural member 21 is distributed on the outer wall of the combustion chamber 3 in a sinusoidal curve, and the cross-flow structural member 21 is connected to the air inlet of the combustion chamber 3, and each guide member 22 is arranged in the cross-flow structural member 21, and is used 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, the combustion chamber 3 and the tail nozzle 4 are connected in sequence, the fractal cross-flow component 2 is arranged on the outer wall of the combustion chamber 3, and the cross-flow structure 21 is distributed on the outer wall of the combustion chamber 3 in a sine curve, which can expand the influence on the cross-flow influence area. Based on this, the cross-flow structure 21 is connected to the air inlet of the combustion chamber 3, and each guide 22 is arranged in the cross-flow structure 21, which is used to change the deflection angle of the air flowing into the combustion chamber 3. The guide 22 of the fractal cross-flow component 2 changes the air deflection angle, so that the air entering the combustion chamber 3 can be more fully and evenly mixed with the fuel sprayed by the injection unit 1, and after increasing the lateral airflow, the lateral space is fully utilized, the temperature distribution in the high temperature zone is uniform, and the oil-gas mixing effect is significantly enhanced. 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, which helps to stabilize the flame, make the combustion process more continuous and efficient, and reduce problems such as incomplete combustion and local overheating. The problem of low combustion efficiency caused by poor lateral space utilization and oil-gas mixing effect in the prior art is effectively solved.

[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 arranged along the circumference of the combustion chamber 3 in a sinusoidal curve.

[0054] In practical applications, Figure 4 Further illustrating a schematic diagram of the structure of a single sinusoidal cross-flow structure according to an embodiment of the present disclosure, as shown in Figure 4 As shown, a sine curve formed by the outer contour of a single sub-cross-flow structure 211, a single sine curve function y = A1sin(w1x+k1)+b, wherein x is the circumferential angle, A1 is the amplitude of the first sine curve, w1 is the angular velocity of the first sine 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 the single sub-cross-flow structure is as shown in FIG. Figure 5 shown. Figure 6 Further illustrating the structural schematic diagram of the double sinusoidal cross-flow structure according to an embodiment of the present disclosure, as shown in Figure 6 As shown, the outer contours of multiple sub-cross-flow structural parts constitute a sinusoidal curve, and the sinusoidal curve function y=A1sin(w1x+k1)+A2sin(w2x+k2)+b constitutes multiple sub-cross-flow structural parts, 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 contour curves of multiple sub-cross-flow structural members according to an embodiment of the present disclosure, wherein the contour curve of a single sub-cross-flow structural member is as shown in FIG. Figure 7 As shown. By using a single sinusoidal curve or multiple sinusoidal curves superimposed profile combined with a guide baffle, the airflow can flow into the combustion chamber at a certain deflection angle in the cross-flow structure. The undulating characteristics of the sinusoidal profile are used to expand the influence width of the cross-flow airflow, thereby increasing the action time of the cross-flow airflow and the injection oil beam, and 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 Figure 8As shown, in the structure in which the cross-flow structure is a sinusoidal curve, due to the superposition of sinusoidal curves of different amplitudes, different periods and different phases of each sub-cross-flow structure, the local amplification of the channel is still a sinusoidal curve configuration, and the local influence width is increased by utilizing the multi-layer curve fluctuation characteristics.

[0057] Fig. 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. 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 lateral 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] Fig.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, as shown in FIG. Fig.10 As shown, by using the above-mentioned fractal cross-flow component, the cross-flow flow influence area can be significantly expanded without changing the width of the cross-flow channel. Fig.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. Fig.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.11 As shown, Fig.11 The color of the fuel particles shown in the figure indicates the velocity distribution in the Y direction (vertical direction). Fig.11 It can be seen that the fuel particles in the original scheme 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 scheme indicate that there is a component velocity of the lateral flow even at the upstream end to the left of the cross-flow channel outlet, which also shows that the sinusoidal fractal cross-flow structure expands the influence on the lateral movement of the fuel particles.

[0059] The exemplary embodiment of the present disclosure provides an aircraft, including an engine with a cross-flow structure according to the exemplary embodiment of the present disclosure. It should be understood that the aircraft according to the exemplary embodiment 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 elaborated here.

[0061] It should be noted that the aircraft provided in the embodiments of the present disclosure may also include a fuselage, a flight controller, etc., and the engine, the 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. Fig.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, the method for using an engine with a cross-flow structure applied to the above-mentioned aircraft includes:

[0063] S1201: Determine the position information of the fractal cross-flow assembly according to the position information of the injection unit. It should be understood that the position information of the fractal cross-flow assembly is determined according to 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 the airflow entering from the fractal cross-flow assembly will not be blocked by the injection unit.

[0064] S1202: 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. It should be understood that the interference factor is the processing difficulty and cross-flow strengthening effect of the fractal cross-flow component, and the use of a single sine curve or the superposition of two sine curves can be determined according to actual working conditions.

[0065] S1203: Determine a trajectory parameter of the cross-flow structure according to each sub-cross-flow structure;

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

[0067] Exemplarily, determining the trajectory parameters of the cross-flow structure for each sub-cross-flow structure 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 ith sine curve, w i is the angular velocity of the ith 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, the tighter the curve fluctuation is, and the period 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 partition injector. Figure 4 - Figure 7This is an example of a single sine curve and a contour curve of two superimposed sine curves, where 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, and 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 guide members according to an interference factor.

[0071] In practical applications, Fig.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, Fig.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.13 - Fig.14 As shown, according to different working conditions, the appropriate number of guide pieces m is selected, which is generally in the range of 10 to 50. Fig.13 As shown, according to the number of guide pieces m, Fig.13 The inner circle in is equally divided into m channel center points B j , j takes values ​​from 1 to m. Fig.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 values ​​range from 1 to m. Connect point B j and the center point O, take line segment OB j The midpoint is A j , connect 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 mainstream direction of the airflow in the j+1th section of the guide channel can be toward the line segment OB j The midpoint A j Flow, without considering other factors, the cross flow reaches the point A in the previous area jWhen j The effect is basically the same as point O, which maximizes the uniformity of the cross-flow mixing effect everywhere, such as Fig.13 As shown in the figure, the deflection design of the guide makes the crossflow flow to the front space area, and also avoids the situation that when there is no deflection design, all the crossflow flows to the center and gathers, causing the oil and gas to gather to the center and uneven distribution. At the same time, the deflection design enables the crossflow component to expand the width of the crossflow to form Figure 8 The effect shown.

[0073] The above descriptions are only some embodiments of the present disclosure and an explanation of the technical principles used. 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 technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, a technical solution formed by replacing the above features with the technical features with similar functions disclosed in the present disclosure (but not limited to).

[0074] Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present disclosure. It should be understood by those skilled in the art that the above embodiments may be modified 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. An engine with a cross-flow structure, characterized in that: 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 connected in sequence, and the fractal cross-flow component is arranged on the outer side wall of the combustion chamber; The fractal cross-flow component includes a cross-flow structure and a plurality of 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.

2. The engine with a cross-flow structure according to claim 1, characterized in that: The cross-flow structure comprises a plurality of sub-cross-flow structures, and the outer contour of each of the sub-cross-flow structures is sinusoidally arranged along the circumference of the combustion chamber.

3. The engine with a cross-flow structure according to claim 2, characterized in that: Each of the sub-cross-flow structures is a hollow structure.

4. The engine with a cross-flow structure according to claim 2, characterized in that: The amplitude of each of the sub-cross-flow structures is different.

5. The engine with a cross-flow structure according to claim 2, characterized in that: The period of each of the sub-cross-flow structures is different.

6. The engine with a cross-flow structure according to claim 2, characterized in that: The phase of each of the sub-cross-flow structures is different.

7. An aircraft, characterized in that: An engine comprising the cross-flow structure as described in any one of claims 1 to 6.

8. A method for using a cross-flow engine, characterized in that: For the aircraft of claim 7, the method for using the engine of the cross-flow structure comprises: Determining 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 trajectory parameters of the cross-flow structure according to each of the sub-cross-flow structures; A trajectory of the cross-flow structure is determined based on the trajectory parameters.

9. The method for using the engine with a cross-flow structure according to claim 8, characterized in that: Determining the trajectory parameters of the cross-flow structure according to each of the sub-cross-flow structures also includes: Establish a trajectory curve function based on the trajectory parameters: Where x is the circumferential angle, A i is the amplitude of the ith sine curve, w i is the angular velocity of the ith 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.

10. The method for using the engine with a cross-flow structure according to claim 8, characterized in that: The method for using the engine with the cross-flow structure also includes: The number of the guide members is determined according to the interference factor.

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