Mixed flow structure, working method and engine of air turbine rocket engine

Abstract

The present invention belongs to the technical field of air turbine rocket engines, and discloses a mixed flow structure, working method and engine of an air turbine rocket engine, wherein one end of a first swirl plate is connected to one side of the outlet end of a corresponding inner channel, and the other end is located obliquely in front of the outlet end of the corresponding inner channel; one end of a second swirl plate is connected to the other side of the outlet end of the corresponding inner channel, and the other end is located obliquely in front of the outlet end of the corresponding inner channel; an arc connecting plate is connected to the top of the outlet end of the corresponding inner channel, the upper ends of the first swirl plate and the second swirl plate; the first swirl plate, the second swirl plate and the arc connecting plate form a gas swirl channel, and an air swirl channel is formed between the first swirl plate and the second swirl plate of two adjacent mixed flow reinforcement lobes. The purpose of the present invention is to shorten the mixing distance required by the lobe mixer to reduce the size of the air turbine rocket engine, while taking into account the mixing uniformity of high-temperature gas and cold air.

Description

Technical Field

[0001] The present invention belongs to the technical field of air turbine rocket engines, and in particular relates to a mixed flow structure, a working method and an engine of an air turbine rocket engine. Background Art

[0002] The air turbine rocket engine is an organic fusion of a rocket engine and an aircraft engine. It has the characteristics of a large airspace and a wide speed range, and is suitable for providing power for near-space vehicles. This type of engine optimizes the energy release of the combustion products by mixing high-temperature combustion gas with cold air, thereby increasing the thrust and efficiency of the engine. However, the uniformity of the mixing of high-temperature combustion gas and cold air has become one of the key factors restricting the improvement of engine performance. The ideal mixing state can significantly increase the heat release of the afterburner, thereby increasing the thrust output.

[0003] Lobe mixers are widely used to promote the mixing process of high-temperature gas and cold air because they can effectively generate complex vortex structures (stream vortex, orthogonal vortex, etc.). That is to say, in the design of the mixing structure of high-temperature gas and cold air in air turbine rocket engines, lobe mixers are generally used for mixing. The high-temperature gas flows through the inner duct of the lobe mixer, and the cold air flows through the outer duct of the lobe mixer. The lobe mixer guides the high-temperature gas in the inner duct and the cold air in the outer duct to interact with each other to achieve preliminary mixing. However, under high-speed flow conditions, this naturally formed vortex structure requires a long distance to fully develop the mixing to achieve the ideal mixing effect, which inevitably increases the overall size of the engine; if the development mixing distance is compressed, it will affect the mixing uniformity of the high-temperature gas and cold air, and thus affect the engine performance. Summary of the invention

[0004] In response to the problems existing in the prior art, the present invention provides a mixed flow structure, a working method and an engine of an air turbine rocket engine, the purpose of which is to shorten the mixing distance required for the lobe mixer to reduce the size of the air turbine rocket engine, while taking into account the mixing uniformity of high-temperature combustion gas and cold air.

[0005] In order to solve the above technical problems, the present invention is implemented by the following technical solutions:

[0006] In a possible implementation of the first aspect, a mixed flow structure of an air turbine rocket engine includes a lobe mixer, each inner channel outlet of the lobe mixer is connected to a mixed flow reinforcement lobe; the mixed flow reinforcement lobe includes a first swirl plate, a second swirl plate and an arc-shaped connecting plate, one end of the first swirl plate is connected to one side of the corresponding inner channel outlet end, and the other end of the first swirl plate is located obliquely in front of the corresponding inner channel outlet end; one end of the second swirl plate is connected to the other side of the corresponding inner channel outlet end, and the other end of the second swirl plate is located obliquely in front of the corresponding inner channel outlet end; the arc-shaped connecting plate is connected to the top of the corresponding inner channel outlet end, the upper end of the first swirl plate and the upper end of the second swirl plate;

[0007] The first swirl plate, the second swirl plate and the arc-shaped connecting plate of each mixing flow reinforcement lobe form a gas swirl channel, and the gas swirl channel is connected to the inner channel of the lobe mixer;

[0008] An air swirl channel is formed between the first swirl plate and the second swirl plate of two adjacent mixed flow reinforcement lobes, and the air swirl channel is communicated with the outer duct of the lobe mixer.

[0009] According to a first aspect of the present invention, a portion of the other end of the first swirl plate below the middle is twisted away from the second swirl plate, and a portion of the other end of the second swirl plate below the middle upper portion is twisted toward the first swirl plate.

[0010] According to a first aspect of the present invention, a first dimension of the mixed flow enhancement lobe gradually decreases along a first direction; wherein the first direction refers to a direction from the outermost periphery of the outlet end face of the lobe mixer to the center of the outlet end face of the lobe mixer; the first dimension of the mixed flow enhancement lobe refers to a horizontal distance from one end to the other end of the mixed flow enhancement lobe after the mixed flow enhancement lobe is projected onto the radial center plane of the corresponding inner channel.

[0011] According to a first aspect of the present invention, the maximum first dimension of the mixing flow reinforcement lobe is one third to two thirds of the length of the lobe mixer; wherein the length of the lobe mixer refers to the vertical distance from the inlet end face to the outlet end face of the lobe mixer.

[0012] According to the first aspect of the present invention, on the same circumference with the center of the outlet end face of the lobe mixer as the center, the distance from the other end of the first swirl plate to the other end of the second swirl plate is one third to one half of the distance from one side to the other side of the outlet end of the corresponding inner channel.

[0013] According to the first aspect of the present invention, an angle between the mixed flow enhancement flap and a radial center plane of the corresponding inner channel is provided in a range of 16° to 18°.

[0014] According to a first aspect of the present invention, it is provided that the wall thickness of the mixing flow enhancing lobe is the same as the wall thickness of the lobe mixer.

[0015] According to a first aspect of the present invention, the arc-shaped connecting plate is integrally connected with the upper end of the first swirl plate and the upper end of the second swirl plate.

[0016] In a possible implementation of the second aspect, a working method of a mixed flow structure of an air turbine rocket engine includes:

[0017] The combustion gas is introduced into the inner duct of the lobe mixer, and the air is introduced into the outer duct of the lobe mixer;

[0018] When the gas flows through the gas swirl channel, it is in a swirl flow state in the gas swirl channel;

[0019] When the air flows through the air swirl channel, it is in a swirl flow state in the air swirl channel;

[0020] The gas in the swirl flow state and the air in the swirl flow state are alternately distributed along the circumference, and the gas flowing out of the gas swirl channel outlet in swirl flow and the air flowing out of the air swirl channel outlet in swirl flow contact each other to generate mixed swirl vortices.

[0021] In a possible implementation of the third aspect, an air turbine rocket engine includes the mixed flow structure of the air turbine rocket engine.

[0022] Compared with the prior art, the present invention has at least the following beneficial effects:

[0023] The present invention provides a mixed flow structure of an air turbine rocket engine. By changing the design of the lobe mixer outlet, a mixed flow reinforcement lobe is designed, which significantly improves the mixing uniformity of high-temperature gas and cold air. Specifically, the high-temperature gas is introduced into the inner duct of the lobe mixer, and the cold air enters through the outer duct of the lobe mixer. When the high-temperature gas flows through the gas swirl channel, under the guidance of the first swirl plate and the second swirl plate, the high-temperature gas rotates, and part of its axial velocity is converted into a rotational velocity. At the same time, when the cold air in the outer duct of the lobe mixer passes through the air swirl channel between the first swirl plate and the second swirl plate of the adjacent mixed flow reinforcement lobe, it is also guided by the swirl plate to generate a rotating flow, and the cold air rotates, and part of its axial velocity is converted into a rotational velocity. The cold air and the high-temperature gas are both in a swirl state before mixing. The high-temperature gas in the swirl flow state and the cold air in the swirl flow state are alternately distributed along the circumference. When the high-temperature gas and the cold air in the swirl flow state flow out of the corresponding gas swirl channel and the air swirl channel, they contact each other and generate a strong mixing swirl vortex, which is conducive to the full mixing between the two. At the same time, after the axial speed of the high-temperature combustion gas and the cold air is partially converted into a rotational speed, the mixing time is prolonged, and thus a longer distance is not required for the two to develop mixing, that is, the straight-line distance required for mixing is reduced. Therefore, the air turbine rocket engine can achieve efficient mixing within a shorter mixing distance, which is beneficial to reducing the overall size of the engine. In summary, the mixed flow structure of an air turbine rocket engine provided by the present invention can not only shorten the mixing distance required for the lobe mixer to reduce the size of the air turbine rocket engine, but also improve the mixing uniformity of the high-temperature combustion gas and the cold air to avoid affecting the performance of the engine.

[0024] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the specific implementation modes of the present invention, the drawings required for use in the description of the specific implementation modes will be briefly introduced below. Obviously, the drawings described below are some implementation modes of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 It is an overall schematic diagram of a mixed flow structure of an air turbine rocket engine according to an embodiment of the present invention at one viewing angle;

[0027] Figure 2 It is an overall schematic diagram of a mixed flow structure of an air turbine rocket engine according to an embodiment of the present invention from another perspective;

[0028] Figure 3 It is a partial structural schematic diagram of a mixed flow structure of an air turbine rocket engine according to an embodiment of the present invention at a certain viewing angle;

[0029] Figure 4 It is an overall schematic diagram of a mixed flow reinforcement flap in a mixed flow structure of an air turbine rocket engine according to an embodiment of the present invention at a certain viewing angle;

[0030] Figure 5 The overall schematic diagram of the lobe mixer at one viewing angle.

[0031] In the figure: 1-lobe mixer; 2-mixing flow strengthening lobe; 20-first swirl plate; 21-second swirl plate; 22-arc connecting plate; 3-gas swirl channel; 4-air swirl channel. DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] Combination Figures 1 to 5 As shown, an embodiment of the present invention provides a mixed flow structure of an air turbine rocket engine, which aims to improve the mixing uniformity of high-temperature gas and cold air by optimizing the outlet design of the lobe mixer 1, which can not only shorten the mixing distance required by the lobe mixer 1 to reduce the size of the air turbine rocket engine, but also improve the mixing uniformity of high-temperature gas and air. The mixed flow structure of the air turbine rocket engine includes a lobe mixer 1, and each inner channel outlet of the lobe mixer 1 is connected to a mixed flow enhancement lobe 2. Among them, the mixed flow enhancement lobe 2 includes a first swirl plate 20, a second swirl plate 21 and an arc-shaped connecting plate 22, one end of the first swirl plate 20 is connected to one side of the corresponding inner channel outlet end, and the other end of the first swirl plate 20 is located obliquely in front of the corresponding inner channel outlet end. One end of the second swirl plate 21 is connected to the other side of the corresponding inner channel outlet end, and the other end of the second swirl plate 21 is located obliquely in front of the corresponding inner channel outlet end. The arc-shaped connecting plate 22 is connected to the top of the corresponding inner channel outlet end, the upper end of the first swirl plate 20 and the upper end of the second swirl plate 21. The first swirl plate 20, the second swirl plate 21 and the arc-shaped connecting plate 22 of each mixing flow enhancing lobe 2 form a gas swirl channel 3, and the gas swirl channel 3 is connected to the inner channel of the lobe mixer 1. An air swirl channel 4 is formed between the first swirl plate 20 and the second swirl plate 21 of two adjacent mixing flow enhancing lobe 2, and the air swirl channel 4 is connected to the outer channel of the lobe mixer 1.

[0034] Specifically, a conventional lobe mixer 1 is selected as the basic structure, and its design ensures that the high-temperature gas and the cold air can flow through the inner duct and the outer duct respectively. Figure 5 As shown, the lobe mixer 1 is a conventional structure, which is usually formed by connecting the lobes in an array around the central axis to form a structure with inner channels and outer channels alternating with each other; the specific size of the lobe mixer 1 is adjusted according to the specific requirements of the air turbine rocket engine to ensure the basic mixing effect. Figure 1 As shown, at the outlet of each inner channel of the lobe mixer 1, a mixed flow enhancement flap 2 is designed and installed. Each mixed flow enhancement flap 2 consists of three parts: a first swirl plate 20, a second swirl plate 21 and an arc-shaped connecting plate 22. Among them, one end of the first swirl plate 20 is fixed on one side of the outlet end of the corresponding inner channel, and the other end extends to the oblique front of the outlet end, forming a certain inclination angle. This design can guide the high-temperature gas flowing out of the inner channel to produce a rotating flow. The second swirl plate 21 is similar to the first swirl plate 20, but one end of the second swirl plate 21 is located on the other side of the outlet of the inner channel, and the other end also extends to the oblique front of the outlet end. In this way, the gas flowing out of the inner channel can form a stable swirl under the guidance of the swirl plates on both sides. The arc-shaped connecting plate 22 is connected to the top of the outlet of the inner channel and the upper ends of the first swirl plate 20 and the second swirl plate 21 to form a semi-closed gas swirl channel 3.

[0035] Through the above structure, the first swirl plate 20, the second swirl plate 21 and the arc-shaped connecting plate 22 in each mixed flow enhancement flap 2 together form a gas swirl channel 3. At the same time, the space between two adjacent mixed flow enhancement flaps 2 forms an air swirl channel 4, allowing the cold air in the outer duct to pass through in a swirl state.

[0036] The working method of the mixed flow structure of the air turbine rocket engine is specifically as follows: after starting the air turbine rocket engine, the high-temperature gas is introduced into the inner channel of the lobe mixer 1, and the cold air enters through the outer channel of the lobe mixer 1. When the high-temperature gas flows through the gas swirl channel 3, under the guidance of the first swirl plate 20 and the second swirl plate 21, the high-temperature gas rotates, and part of its axial velocity is converted into a rotational velocity. At the same time, when the cold air in the outer channel of the lobe mixer 1 passes through the air swirl channel 4 between the first swirl plate 20 and the second swirl plate 21 of the adjacent mixed flow reinforcement lobe 2, it is also guided by the swirl plate to generate a swirl flow. Similarly, the cold air rotates, and part of its axial velocity is converted into a rotational velocity. It can be seen that this design makes the cold air and the high-temperature gas in the swirl flow state before mixing. The high-temperature gas in the swirl flow state and the cold air in the swirl flow state are alternately distributed along the circumference. When the high-temperature gas in the swirl state and the cold air meet in the mixing area downstream of the lobe mixer 1, a strong mixing swirl vortex is generated, which is conducive to the full mixing between the two. At the same time, after the axial velocity of the high-temperature combustion gas and the cold air is partially converted into rotational speed, the mixing time is prolonged, and thus a longer distance is not required to develop the mixing, which is beneficial to reducing the size of the air turbine rocket engine.

[0037] In summary, through the design of the above-mentioned embodiments, the present invention can not only shorten the mixing distance required by the lobe mixer 1 to reduce the size of the air turbine rocket engine, but also improve the mixing uniformity of the high-temperature combustion gas and air, which is beneficial to the improvement of engine performance. In other words, due to the improvement of mixing uniformity, the heat release in the afterburner chamber is optimized, thereby increasing the thrust output of the air turbine rocket engine. In addition, due to the shortening of the mixing distance, the overall size of the air turbine rocket engine is also effectively controlled. The mixed flow structure of the air turbine rocket engine of the present invention realizes efficient and uniform mixing of high-temperature combustion gas and cold air, providing a new solution for the development of the aviation power field.

[0038] In one possible implementation, combining Figure 1 , Figure 3 and Figure 4 As shown, the other end of the first swirl plate 20 below the middle portion is twisted away from the second swirl plate 21 , and the other end of the second swirl plate 21 below the middle upper portion is twisted toward the first swirl plate 20 .

[0039] Specifically, the other end of the first swirl plate 20 (i.e., the portion away from the connection end with the lobe mixer 1) is designed to be twisted in a direction away from the second swirl plate 21 at a position below the middle. In other words, the first swirl plate 20 does not simply extend straight, but has a certain twist to guide and change the direction of the airflow, which helps to increase the degree of swirl of the airflow and optimize the mixing effect of the airflow. In contrast to the first swirl plate 20, the other end of the second swirl plate 21 (also referring to the portion away from the connection end with the lobe mixer 1) is designed to be twisted in a direction close to the first swirl plate 20 at a position below the middle and upper part. Similarly, the second swirl plate 21 does not simply extend straight, but has a certain twist to help increase the degree of swirl of the airflow and optimize the mixing effect of the airflow. In summary, the design of this embodiment forms an airflow pattern with a better degree of swirl through the mutual cooperation of the first swirl plate 20 and the second swirl plate 21, thereby better enhancing the mixing effect of the airflow.

[0040] In an achievable manner, the first dimension of the mixing flow enhancement lobe 2 gradually decreases along the first direction. The first direction refers to the direction from the outermost periphery of the outlet end face of the lobe mixer 1 to the center of the outlet end face of the lobe mixer 1. The first dimension of the mixing flow enhancement lobe 2 refers to the horizontal distance from one end to the other end of the mixing flow enhancement lobe 2 after the mixing flow enhancement lobe 2 is projected onto the radial center plane of the corresponding inner channel.

[0041] Specifically, the definitions of the first direction and the first dimension are clarified: the first direction is the direction from the outermost periphery of the outlet end face of the lobe mixer 1 to the center of the outlet end face; the first dimension is the horizontal distance from one end to the other end of the mixed flow reinforcement lobe 2 after being projected onto the radial center plane of the corresponding inner channel. Along the first direction, the first dimension of the mixed flow reinforcement lobe 2 gradually decreases. This design reduces the amount of material used, thereby effectively reducing the overall weight of the engine, which is beneficial to improving the fuel economy and endurance of the aircraft.

[0042] In order to further reduce the weight, the material of the mixed flow reinforcement flap 2 can be selected from lightweight and high-strength alloy materials, such as titanium alloy or high-temperature alloy. These materials not only have excellent mechanical properties, but also can maintain stable performance under high temperature and high pressure environments.

[0043] Preferably, the maximum first dimension of the mixing flow reinforcement lobe 2 is one third to two thirds of the length of the lobe mixer 1. The length of the lobe mixer 1 refers to the vertical distance from the inlet end face to the outlet end face of the lobe mixer 1.

[0044] That is to say, the maximum first dimension of the mixing enhancement flap 2 should be between one-third and two-thirds of the length of the lobe mixer 1, which can ensure that the mixing enhancement flap 2 can effectively promote airflow mixing without adding unnecessary weight or hindering the smooth flow of airflow due to excessive size.

[0045] In one achievable manner, on the same circle with the center of the outlet end face of the lobe mixer 1 as the center (i.e., the center of the outlet end face of the lobe mixer 1 is determined as the center of the circle, and a circle is drawn with this as the center), the distance from the other end of the first swirl plate 20 to the other end of the second swirl plate 21 is one third to one half of the distance from one side to the other side of the outlet end of the corresponding inner channel.

[0046] That is to say, the distance between the first swirl plate 20 and the second swirl plate 21 should be adjusted according to the actual width of the outlet end face of the inner channel to ensure that the above-mentioned proportional relationship is satisfied, so that the mixing process of high-temperature gas and cold air in the mixed flow structure is more uniform and efficient.

[0047] In one possible implementation, the angle between the mixed flow enhancement flap 2 and the radial center plane of the corresponding inner channel is 16° to 18°, which can achieve a better visual airflow mixing effect and also help enhance the stability of the mixed flow structure. Exemplarily, the angle between the mixed flow enhancement flap 2 and the radial center plane of the corresponding inner channel is 18°.

[0048] Preferably, the wall thickness of the mixing reinforcement flap 2 is the same as the wall thickness of the lobe mixer 1. By designing the same wall thickness, it is ensured that no steps are generated at the connection between the mixing reinforcement flap 2 and the lobe mixer 1, and the wall airflow is violently disturbed. At the same time, it can also be ensured that the two have similar load-bearing capacity when subjected to high-temperature and high-pressure airflow, thereby enhancing the stability of the entire mixing structure.

[0049] Better, such as Figure 4 As shown, the arc-shaped connecting plate 22 is integrally connected with the upper end of the first swirl plate 20 and the upper end of the second swirl plate 21. The integral connection ensures a seamless connection between the arc-shaped connecting plate 22 and the first swirl plate 20 and the second swirl plate 21, thereby greatly enhancing the overall strength of the entire mixed flow structure, so that under the impact of high-speed and high-temperature airflow, the mixed flow reinforcement flap 2 can remain stable and is not easily deformed or damaged. In addition, since the connection between the arc-shaped connecting plate 22 and the first swirl plate 20 and the second swirl plate 21 is smooth and unobstructed, it can ensure the smooth flow of the airflow in the mixed flow structure, reduce the turbulence and eddy loss of the airflow at the connection, and improve the mixing effect of the airflow.

[0050] The embodiment of the present invention provides a working method of a mixed flow structure of an air turbine rocket engine, specifically: a lobe mixer 1 has been installed in a combined exhaust turbofan engine, and its inner duct and outer duct are used to receive high-temperature combustion gas and cold air respectively. High-temperature combustion gas is introduced into the inner duct of the lobe mixer 1, and the high-temperature combustion gas flows in the inner duct. When it flows through the combustion gas swirl channel 3 formed by the first swirl plate 20, the second swirl plate 21 and the arc-shaped connecting plate 22, it is guided by the swirl plate to form a swirl flow state in the channel. At the same time, cold air is introduced into the outer duct of the lobe mixer 1, and the cold air flows in the outer duct. When it flows through the air swirl channel 4 formed between the first swirl plate 20 and the second swirl plate 21 of two adjacent mixed flow reinforcement lobes 2, it is also guided by the swirl plate to form a swirl flow state in the channel. The high-temperature gas in a swirl flow state and the cold air in a swirl flow state are alternately distributed along the circumference in the mixed flow structure. When the high-temperature gas flows out from the outlet of the gas swirl channel 3, it contacts with the cold air flowing out from the outlet of the air swirl channel 4, generating a strong mixing swirl vortex. This mixing swirl vortex greatly improves the mixing uniformity of the high-temperature gas and the cold air, and the mixed airflow is introduced into the afterburner chamber for combustion.

[0051] An embodiment of the present invention provides an air turbine rocket engine, which includes a mixed flow structure of an air turbine rocket engine in the above embodiment. Through the mixed flow structure of an air turbine rocket engine in the above embodiment, the mixing effect of high-temperature fuel gas and air is better, the size of the air turbine rocket engine is reduced, and the overall performance of the air turbine rocket engine is improved.

[0052] More specifically, the air turbine rocket engine is mainly composed of a compressor, a front combustion chamber, a turbine, a rear combustion chamber and a tail nozzle. Among them, a lobe mixer 1 is arranged at the front end of the rear combustion chamber. The inner channel of the lobe mixer 1 is used to receive the high-temperature combustion gas from the combustion chamber, and the outer duct is used to receive the cold air from the compressor. During the operation of the engine, the high-temperature combustion gas generated in the front combustion chamber enters the inner channel of the lobe mixer 1 from the turbine, and the cold air enters the outer duct of the lobe mixer 1 from the compressor. When the high-temperature combustion gas and the cold air flow through their respective corresponding swirl channels, they are guided by the swirl plate to form a swirl. The high-temperature combustion gas and the cold air in the swirl state are alternately distributed along the circumference in the mixed flow structure, and contact each other at the outlet to generate a mixed swirl vortex. This mixing process effectively improves the mixing uniformity of the combustion gas and air, thereby increasing the combustion heat release in the rear combustion chamber and improving the overall performance of the air turbine rocket engine.

[0053] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "bottom", "inside", "outside", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0054] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0055] In the present invention, unless otherwise clearly specified and limited, the terms "connected", "connection" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0056] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0057] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0058] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present invention, which are used to illustrate the technical solutions of the present invention rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the aforementioned embodiments, those of ordinary skill in the art should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the aforementioned embodiments within the technical scope disclosed by the present invention, or can easily conceive of changes, or make equivalent replacements for some of the technical features therein. Such modifications, changes or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered within the protection scope of the present invention.

Claims

1. A mixed flow structure of an air turbine rocket engine, characterized in that: The invention comprises a lobe mixer (1), wherein each inner channel outlet of the lobe mixer (1) is connected to a mixed flow reinforcement lobe (2); the mixed flow reinforcement lobe (2) comprises a first swirl plate (20), a second swirl plate (21) and an arc-shaped connecting plate (22); one end of the first swirl plate (20) is connected to one side of the corresponding inner channel outlet end, and the other end of the first swirl plate (20) is located obliquely in front of the corresponding inner channel outlet end; one end of the second swirl plate (21) is connected to the other side of the corresponding inner channel outlet end, and the other end of the second swirl plate (21) is located obliquely in front of the corresponding inner channel outlet end; the arc-shaped connecting plate (22) is connected to the top of the corresponding inner channel outlet end, the upper end of the first swirl plate (20) and the upper end of the second swirl plate (21); The first swirl plate (20), the second swirl plate (21) and the arc-shaped connecting plate (22) of each of the mixed flow reinforcement lobes (2) form a gas swirl channel (3), and the gas swirl channel (3) is connected to the inner channel of the lobe mixer (1); An air swirl channel (4) is formed between the first swirl plate (20) and the second swirl plate (21) of two adjacent mixed flow reinforcement lobes (2), and the air swirl channel (4) is connected to the outer duct of the lobe mixer (1).

2. The mixed flow structure of an air turbine rocket engine according to claim 1, characterized in that: The portion of the other end of the first swirl plate (20) below the middle portion is twisted in a direction away from the second swirl plate (21), and the portion of the other end of the second swirl plate (21) below the middle upper portion is twisted in a direction approaching the first swirl plate (20).

3. The mixed flow structure of an air turbine rocket engine according to claim 1, characterized in that: Along a first direction, a first dimension of the mixing flow enhancement flap (2) gradually decreases; wherein the first direction refers to a direction from the outermost periphery of the outlet end face of the lobe mixer (1) to the center of the outlet end face of the lobe mixer (1); the first dimension of the mixing flow enhancement flap (2) refers to a horizontal distance from one end to the other end of the mixing flow enhancement flap (2) after the mixing flow enhancement flap (2) is projected onto the radial center plane of the corresponding inner channel.

4. The mixed flow structure of an air turbine rocket engine according to claim 3, characterized in that: The maximum first dimension of the mixing flow reinforcement lobe (2) is one third to two thirds of the length of the lobe mixer (1); wherein the length of the lobe mixer (1) refers to the vertical distance from the inlet end face to the outlet end face of the lobe mixer (1).

5. The mixed flow structure of an air turbine rocket engine according to claim 1, characterized in that: On the same circumference with the center of the outlet end surface of the lobe mixer (1) as the center, the distance from the other end of the first swirl plate (20) to the other end of the second swirl plate (21) is one third to one half of the distance from one side to the other side of the outlet end of the corresponding inner channel.

6. The mixed flow structure of an air turbine rocket engine according to claim 1, characterized in that: The angle between the mixed flow enhancement flap (2) and the radial center plane of the corresponding inner channel is 16° to 18°.

7. The mixed flow structure of an air turbine rocket engine according to claim 1, characterized in that: The wall thickness of the mixed flow reinforcement lobe (2) is the same as the wall thickness of the lobe mixer (1).

8. The mixed flow structure of an air turbine rocket engine according to claim 1, characterized in that: The arc-shaped connecting plate (22) is integrally connected with the upper end of the first swirl plate (20) and the upper end of the second swirl plate (21).

9. The method for operating the mixed flow structure of an air turbine rocket engine according to any one of claims 1 to 8, characterized in that: include: Introducing fuel gas into the inner duct of the lobe mixer (1), and introducing air into the outer duct of the lobe mixer (1); When the gas flows through the gas swirl channel (3), it is in a swirl flow state in the gas swirl channel (3); When the air flows through the air swirl channel (4), it is in a swirl flow state in the air swirl channel (4); The gas in a swirl flow state and the air in a swirl flow state are alternately distributed along the circumference, and the gas flowing out of the outlet of the gas swirl channel (3) and the air flowing out of the outlet of the air swirl channel (4) contact each other to generate a mixed swirl vortex.

10. An air turbine rocket engine, characterized in that: A mixed flow structure comprising an air turbine rocket engine as described in any one of claims 1 to 8.

Images