A pulse detonation combustor based on rotating detonation wave ignition

Abstract

To address the limitations of existing pulse detonation combustors using detonation jet ignition, which require long jet tubes and thus restrict the increase of their operating frequency, and the dependence of stable operation of pulse detonation turbine engines on the performance and reliability of the igniter, this invention proposes a pulse detonation combustor based on rotating detonation wave ignition. This invention utilizes the relatively high frequency of rotating detonation combustion and the requirement for only a single ignition. The rotating detonation wave generated by the rotating detonation chamber serves as a continuous high-energy ignition source, igniting the explosive mixture within the detonation jet channel. This creates a high-energy detonation jet at the channel's exit, which then flows into the pulse detonation tube and ignites the explosive mixture within. This invention, while maintaining the excellent initiation performance of the detonation jet ignition method, overcomes the adverse effects of long jet tubes and high-frequency ignition on the efficient and stable operation of pulse detonation turbine engines.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and specifically to a pulse detonation combustion chamber. Background Technology

[0002] The Pulse Detonation Turbine Engine (PDTE) is a novel power unit based on pulse detonation combustion. It benefits from both the high thermal efficiency of the detonation cycle and the efficient power extraction of the gas turbine. Furthermore, it boasts advantages such as simple structure, light weight, high thrust-to-weight ratio, and low fuel consumption. Compared to traditional gas turbine engines based on isobaric combustion, it exhibits significant performance advantages and has a very broad application prospect.

[0003] High-frequency triggering and initiation of detonation waves are crucial for the normal operation of pulse detonation turbine engines. Detonation waves are typically initiated in two ways: direct initiation and indirect initiation. Direct initiation requires extremely high ignition energy, making it very difficult to implement in practice. Indirect initiation, on the other hand, achieves detonation through a deflagration-to-detonation transition (DDT), making it a feasible method. However, indirect initiation usually requires a long DDT time and distance, which limits the operating frequency, increases size and weight, and reduces the thrust-to-weight ratio of the pulse detonation turbine engine, severely impacting its overall performance. Therefore, exploring rapid, short-distance initiation technology is a key issue in the application and fundamental research of pulse detonation turbine engines, and also a focus and challenge in detonation research.

[0004] After years of research, various initiation methods have been developed, including solid-state turbulence-induced detonation, transverse jet-induced detonation, jet ignition initiation, and shock wave focusing initiation. Among these, jet ignition initiation combines the advantages of low total pressure loss and good detonation-initiating performance, showing great promise for application. Based on the intensity of the flame jet, jet ignition initiation can be divided into high-speed flame jet ignition initiation and detonation jet ignition initiation. The intensity of the flame jet has a significant impact on initiation performance. Detonation jet ignition initiation has the best performance, but it requires pre-triggered detonation within the jet tube, which often presents challenges. Increasing the length of the jet tube is one method to obtain a detonation jet, but this limits the increase in the operating frequency of the pulse detonation combustion chamber. Furthermore, the intermittent operation of pulse detonation requires high-frequency ignition from the igniter, which places high demands on the performance and reliability of the igniter and is also detrimental to the stable operation of the pulse detonation turbine engine. Summary of the Invention

[0005] To address the limitations on increasing the operating frequency of existing pulse detonation combustors using detonation jet ignition due to the need for long jet tubes, and the dependence of stable operation of pulse detonation turbine engines on the performance and reliability of the igniter, this invention proposes a pulse detonation combustor based on rotating detonation wave ignition. Utilizing the advantage of rotating detonation requiring only a single ignition, this invention uses rotating detonation waves for ignition and detonation of the pulse detonation combustor. This approach maintains the excellent detonation performance of the detonation jet ignition method while resolving the adverse effects of long jet tubes and high-frequency ignition on the efficient and stable operation of pulse detonation turbine engines.

[0006] The technical solution of this invention is:

[0007] A pulse detonation combustion chamber based on rotating detonation wave ignition is characterized by comprising a detonation jet channel, a rotary valve, and an inner combustion chamber casing, a pulse detonation tube, and a rotating detonation chamber arranged radially from the inside to the outside.

[0008] There are N pulse detonation tubes, which are evenly distributed along the circumference in the annular channel formed by the combustion chamber casing and the rotary detonation chamber; N≥2 and is an even number; the pulse detonation tube includes a mixing chamber and a main detonation chamber arranged sequentially along the axial direction; the front half of the mixing chamber is provided with a fuel nozzle for supplying fuel into the mixing chamber.

[0009] There are N detonation jet channels, which are used to connect the N pulse detonation tubes to the rotating detonation chamber, and the path of each detonation jet channel is matched with the propagation direction of the rotating detonation generated by the rotating detonation chamber; each detonation jet channel is provided with a valve near the pulse detonation tube for opening and closing the detonation jet channel; the opening and closing of the valve is controlled according to the working state of the pulse detonation tube corresponding to its detonation jet channel: when the pulse detonation tube has finished air intake and a uniform gas mixture has been formed inside it, the valve is open, and the valve is closed at other times;

[0010] The rotary valve is located at the end of all pulse detonation tubes and is used to control the working state of each pulse detonation tube. Under the premise that each pulse detonation tube works intermittently, the rotary valve can ensure that at least half of the pulse detonation tubes are in the air intake state at any time.

[0011] The outer wall of the rotating detonation chamber is provided with a pre-detonation tube. After the pre-detonation tube is detonated, it generates a detonation and enters the annular cavity of the rotating detonation chamber to form a rotating detonation. The rotating detonation enters the open detonation jet channel and detonates the explosive mixture therein, forming a high-energy detonation jet at the outlet of the detonation jet channel. The high-energy detonation jet flows into the corresponding pulse detonation tube to achieve ignition.

[0012] Furthermore, there are multiple pre-detonation tubes, which are evenly distributed along the same circumference; the propagation direction of the detonation waves generated by all the pre-detonation tubes is the same, which is either counterclockwise or clockwise.

[0013] Furthermore, the pre-detonation tube includes a straight pipe section and an arc-shaped pipe section connected to each other, with the straight pipe section and the arc-shaped pipe section being tangent at the connection point; the straight pipe section is tangent to and connected to the annular cavity of the rotating detonation chamber; the end of the arc-shaped pipe section is provided with an inlet for fuel and oxidizer; the pre-detonation tube is also provided with a spark plug, the spark plug being positioned close to the inlet for fuel and oxidizer.

[0014] Furthermore, the mounting surface of the arc-shaped pipe section matches the outer wall of the rotating detonation chamber and is set close to the outer wall of the rotating detonation chamber.

[0015] Furthermore, the path of the detonation jet channel is arc-shaped, and the inner wall of the inlet end is tangent to the inner wall of the rotating detonation chamber annular cavity, while the outlet end is located at the connection between the mixing chamber and the main detonation chamber of the pulse detonation tube.

[0016] Furthermore, the rotary valve has multiple air inlets evenly distributed along the same circumference on its end face. By rotating the rotary valve, the relative position of the air inlets and each pulse detonation tube is changed, thereby controlling the working state of each pulse detonation tube: the pulse detonation tube connected to the air inlet is in the air intake state, and the other pulse detonation tubes are in the working state; the part of the rotary valve end face without air inlets acts as the thrust wall of the pulse detonation tube in the working state.

[0017] Furthermore, the axial cross-section of a single air inlet is composed of four arc segments. The radial segment includes two arc segments that are coaxial with the rotary valve and tangent to the inner wall of the pulse detonation tube. The circumferential segment includes two arc segments with a diameter equal to the inner diameter of the pulse detonation tube. The two radial arc segments are arranged opposite each other, and the two circumferential arc segments are arranged opposite each other.

[0018] The present invention also provides a pulse detonation turbine engine, which is characterized by including the above-mentioned pulse detonation combustion chamber based on rotating detonation wave ignition.

[0019] The beneficial effects of this invention are:

[0020] 1. In existing schemes that combine rotating detonation chambers and pulse detonation tubes, both rotating detonation chambers and pulse detonation tubes are initiated and operated independently. The role of rotating detonation chambers is to reduce the unsteady characteristics of the pulse detonation tube's exhaust gas. The pulse detonation tube still requires frequent ignition, and due to its low ignition energy, the DDT distance and time are relatively long.

[0021] This invention innovatively utilizes the high-energy detonation jet generated by rotary detonation to directly ignite the pulse detonation combustion tube. Specifically, taking advantage of the relatively high frequency of rotary detonation combustion and the fact that it only requires a single ignition, the rotary detonation wave generated by the rotary detonation chamber is used as a continuous high-energy ignition source. The rotary detonation ignites the explosive mixture in the detonation jet channel, thereby forming a high-energy detonation jet at the outlet of the detonation jet channel. The high-energy detonation jet flows into the pulse detonation tube and ignites the explosive mixture inside. Therefore, this invention can fully maintain the excellent initiation performance of the detonation jet ignition method, requiring a shorter DDT distance and time. This invention uses the rotating detonation wave generated by the rotating detonation chamber to replace the igniter of the traditional pulse detonation tube. Since the rotating detonation chamber only needs one ignition, it avoids the drawbacks of the traditional pulse detonation tube requiring high-frequency ignition. The pulse detonation tube in this invention uses the high-energy detonation jet generated by the rotating detonation wave for ignition and detonation. The ignition energy is extremely high, and there is no need to use a long jet tube. Therefore, it overcomes the problem of limited operating frequency of existing pulse detonation tubes using detonation jet ignition and detonation, which is beneficial to the continuous and stable operation of the pulse detonation turbine engine.

[0022] Furthermore, the exhaust from the rotating detonation chamber in this invention can also improve the unsteady characteristics of the exhaust from the pulse detonation tube to a certain extent.

[0023] 2. The present invention designs the detonation jet channel as an arc shape, and the inner wall of the inlet end is tangent to the inner wall of the rotating detonation chamber annular cavity, which is more conducive to the rotating detonation wave detonating the explosive mixture in the detonation jet channel.

[0024] 3. In this invention, the pre-explosion tube is designed to consist of straight pipe sections and arc-shaped pipe sections, which reduces the radial dimension of the combustion chamber and improves the structural compactness.

[0025] 4. In this invention, there are multiple pulse detonation tubes evenly distributed circumferentially. The evenly distributed air inlets on the rotary valve ensure that at least half of the pulse detonation tubes are in the intake state. This not only reduces the intake resistance of the pulse detonation turbine engine and lowers the pressure pulsation in the intake duct and compressor, but also continuously cools the turbine in the pulse detonation turbine engine. The design of the air inlets on the rotary valve to be evenly distributed circumferentially ensures that the pulse detonation tubes in the working state are always centrally symmetrical. This helps to avoid vibration of the entire pulse detonation combustion chamber caused by uneven thrust. Correspondingly, there can be multiple pre-detonation tubes. When there are multiple tubes, they are designed to be evenly distributed circumferentially and the propagation direction of the detonation waves generated by all pre-detonation tubes is the same. This can better match the pulse detonation tubes in the working state in symmetrical positions and improve the stability of the combustion chamber. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall structure of the present invention (partial cross-sectional view).

[0027] Figure 2 This is the front view of the present invention.

[0028] Figure 3 This is the right view of the present invention.

[0029] Figure 4 yes Figure 3 Schematic diagram of section AA.

[0030] Figures 5-11 This is a schematic diagram of the detonation principle in an embodiment of the present invention.

[0031] Figure label:

[0032] 1- Rotary valve; 2- Outlet of detonation jet channel; 3- Pre-detonation tube; 4- Fuel inlet; 5- Outer wall of rotary detonation chamber; 6- Inner wall of rotary detonation chamber; 7- Pulse detonation tube; 8- Combustion chamber casing; 9- Fuel and oxidizer inlet of pre-detonation tube; 10- Detonation jet channel; 11- Fuel nozzle; 12- Air inlet; 13- Mixing chamber; 14- Main detonation chamber; 15- Annular seam. Detailed Implementation

[0033] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0034] like Figure 1 As shown, the pulse detonation combustion chamber based on rotating detonation wave ignition provided by the present invention includes an inner casing 8, a rotating detonation chamber, a pulse detonation tube 7, a detonation jet channel 10, and a rotary valve 1.

[0035] The combustion chamber casing 8 has the same function as the combustion chamber casing on a conventional aero-engine, one of which is to fix the pulse detonation tube 7.

[0036] The rotating detonation chamber is located on the periphery of the entire pulse detonation combustion chamber, while the inner casing 8 of the combustion chamber is located at the center of the entire pulse detonation combustion chamber. The rotating detonation chamber includes an inner wall 6 and an outer wall 5, which are radially spaced to form an annular cavity. An annular channel is formed between the inner wall 6 of the rotating detonation chamber and the inner casing 8 of the combustion chamber. The front end of the rotating detonation chamber has an annular slot 15, which communicates with the annular cavity for introducing air into the annular cavity. The rear end of the rotating detonation chamber is used to connect with the turbine in the pulse detonation turbine engine to exhaust exhaust into the turbine. Multiple fuel inlets 4 and one or more pre-detonation tubes 3 are uniformly arranged circumferentially on the outer wall 5 of the rotating detonation chamber, and the circumference of the fuel inlets 4 is close to that of the front end of the pre-detonation tubes 3. The fuel inlets 4 are used to supply fuel into the annular cavity of the rotating detonation chamber, and the pre-detonation tubes 3 are used to detonate the rotating detonation chamber. When there are multiple pre-detonation tubes 3, all pre-detonation tubes 3 are evenly distributed along the same circumference, and the propagation direction of the detonation waves generated by all pre-detonation tubes 3 should be the same, either clockwise or counterclockwise. The advantage of multiple pre-detonation tubes 3 is that they can make the pulse detonation tubes 7, which are in a rotationally symmetrical position, detonate synchronously as much as possible, thereby improving the stability of the combustion chamber. The structural shape of the pre-detonation tubes 3 is not limited, as long as it can detonate the rotating detonation chamber. Preferably, in order to reduce the radial dimension and make the structure more compact, the pre-detonation tube 3 is composed of an arc-shaped pipe section and a straight pipe section. The straight pipe section and the arc-shaped pipe section are tangent at the connection point, and the straight pipe section is connected to the annular cavity of the rotating detonation chamber. The tubes are connected and tangentially connected. At the end of the arc-shaped tube section, there are inlets 9 for fuel and oxidizer (since the fuel and oxidizer can be pre-mixed before being introduced into the pre-detonation tube 3 through inlet 9, or introduced separately into the pre-detonation tube 3 and mixed within it, fuel and oxidizer inlets can be provided on the pre-detonation tube 3, or inlets for pre-mixed fuel and oxidizer can be provided). Each pre-detonation tube 3 is equipped with a spark plug, positioned close to the fuel and oxidizer inlet 9. The slow combustion generated by spark plug ignition is converted into detonation within its corresponding pre-detonation tube 3 and tangentially enters the annular cavity of the rotating detonation chamber to form rotating detonation. To minimize the radial dimension of the entire combustion chamber, the shape of the mounting surface of the arc-shaped tube section of the pre-detonation tube 3 can be designed to fit the outer wall of the rotating detonation chamber, ensuring it is tightly fitted against the outer wall.

[0037] There are N pulse detonation tubes 7, where N ≥ 2 and is an even number. The N pulse detonation tubes 7 have identical structures, each including a mixing chamber 13 and a main detonation chamber 14 arranged sequentially along the axial direction. Multiple fuel nozzles 11 are evenly distributed circumferentially on the front half of the mixing chamber 13's tube wall. The fuel nozzles 11 supply fuel to the mixing chamber 13. After the fuel spray is formed, it mixes with the air supplied from the air inlet 12 of the rotary valve 1 in the mixing chamber 13 and then fills the main detonation chamber 14. The N pulse detonation tubes 7 are evenly distributed circumferentially outside the combustion chamber casing 8, and are located within the annular channel formed by the inner wall 6 of the rotating detonation chamber and the combustion chamber casing 8, with the tube wall of the pulse detonation tube 7 connected to the inner wall 6 of the rotating detonation chamber.

[0038] There are N detonation jet channels 10, which are used to connect the annular cavity of the rotating detonation chamber with N pulse detonation tubes 7. The path of each detonation jet channel 10 must match the propagation direction of the rotating detonation wave to ensure that the rotating detonation wave can propagate smoothly into the detonation jet channel 10. When the rotating detonation wave propagates to the inlet end of the detonation jet channel 10 inside the annular cavity of the rotating detonation chamber, it will detonate the explosive mixture in the detonation jet channel 10 and form a high-energy detonation jet at the outlet end of the detonation jet channel, which will then be introduced into the pulse detonation tube 7 to achieve ignition. The cross-sectional geometric parameters of the detonation jet channel 10 and its optimal ratio to the inner diameter of the pulse detonation tube 7 need to be determined according to the fuel used in the pulse detonation turbine engine. In addition, each detonation jet channel 10 is equipped with a valve near the pulse detonation tube. The opening and closing of the valve is controlled according to the working state of the pulse detonation tube 7. When the pulse detonation tube 7 has finished intake and a uniform gas mixture has been formed, its corresponding valve opens to open the detonation jet channel and introduce the detonation jet for initiation. At other times, its corresponding valve is closed. The specific shape of the path of the detonation jet channel 10 of the present invention is not particularly required, as long as it can introduce the rotating detonation wave into the pulse detonation tube 7. Preferably, the path of the detonation jet channel is as follows: Figure 4 The arc shape shown, with the inner wall of the inlet end tangent to the inner wall of the rotating detonation chamber annular cavity, is more conducive to the rotating detonation wave igniting the explosive mixture in the detonation jet channel 10. The outlet end is located at the connection between the mixing chamber 701 of the pulse detonation tube 7 and the main detonation chamber 702, which is more conducive to the transmission of the rotating detonation wave.

[0039] A rotary valve 1 is located at the end of the pulse detonation tube 7. Multiple air inlets 12 are evenly distributed along the same circumference on the end face of the rotary valve 1. By rotating the rotary valve 1, the relative position of the air inlets 12 and each pulse detonation tube 7 can be changed, thus controlling the working state of each pulse detonation tube 7: the pulse detonation tube 7 connected to the air inlets 12 on the rotary valve 1 is in the air intake state, while the remaining pulse detonation tubes 7 are in the working state. The portion of the end face of the rotary valve 1 without air inlets 12 acts as the thrust wall for the corresponding pulse detonation tube 7. The cross-sectional shape, size, and location of the air inlets 12 on the rotary valve 1 should ensure that, under intermittent operation, at least half of the pulse detonation tubes 7 are in the air intake state at any given time. This not only reduces the intake resistance of the pulse detonation turbine engine and lowers the pressure pulsation in the intake duct and compressor, but also continuously cools the turbine in the pulse detonation turbine engine. This invention designs the air inlet holes on the rotary valve 1 to be circumferentially uniformly distributed, ensuring that the pulse detonation tube 7 remains rotationally symmetrical during operation. This helps avoid vibration of the entire pulse detonation combustion chamber caused by uneven thrust. Simultaneously, when there are multiple pre-detonation tubes 3, the spark plugs corresponding to all pre-detonation tubes 3 ignite simultaneously, and the resulting unidirectionally propagating rotating detonation waves can better match the symmetrically positioned pulse detonation tubes 7 during operation.

[0040] Example:

[0041] Reference Figure 1-2 In this embodiment:

[0042] The outer wall of the rotating detonation chamber is circumferentially provided with 120 fuel inlets 4 and two centrally symmetrically arranged pre-detonation tubes 3; correspondingly, two spark plugs are also provided. Each pre-detonation tube 3 consists of a straight section and an arc-shaped section. The straight section is tangential to the annular cavity of the rotating detonation chamber, and the shape of the mounting surface of the arc-shaped section is adapted to the outer wall of the rotating detonation chamber, ensuring it fits tightly against the outer wall. The slow combustion produced by spark plug ignition is converted into detonation within the arc-shaped tube and enters the rotating detonation chamber tangentially, forming rotating detonation. When the spark plugs of the two pre-detonation tubes 3 ignite simultaneously, the slow combustion produced by each tube is converted into detonation within the arc-shaped tubes of the two pre-detonation tubes 3 and enters the rotating detonation chamber in the same direction.

[0043] There are eight pulse detonation tubes 7, which are evenly distributed circumferentially within the annular channel formed by the inner wall of the rotating detonation chamber and the combustion chamber casing 8. Three fuel nozzles are evenly distributed circumferentially on the wall of the mixing chamber 13 of the pulse detonation tube 7.

[0044] The path of the detonation jet channel is arc-shaped, and the inner wall of the inlet end is tangent to the inner wall of the rotating detonation chamber annular cavity. The outlet end is located at the connection between the mixing chamber 701 and the main detonation chamber 702 of the pulse detonation tube 7.

[0045] A rotary valve 1 is located at the end of the pulse detonation tube 7. The end face of the rotary valve 1 has two circumferentially distributed and centrally symmetrical air inlets 12. The axial cross-section of each air inlet 12 consists of four arc segments: two radially coaxial segments tangent to the inner wall of the pulse detonation tube and two circumferentially segments with a diameter equal to the inner diameter of the pulse detonation tube. The two radial segments are arranged opposite each other, as are the two circumferential segments. These two air inlets 12 allow all four pulse detonation tubes 7 to be in a fully inflated state simultaneously.

[0046] The following embodiment serves as an example to illustrate the working principle of the present invention.

[0047] For ease of explanation, the eight pulse detonation tubes 7 are designated C1 to C8 sequentially, and the detonation jet channels connected to each pulse detonation tube are designated T1 to T8, such as... Figure 5-11 As shown.

[0048] Open the fuel and oxidizer inlet 9 of the pre-detonation tube 3. After a fully mixed explosive mixture has formed inside the pre-detonation tube 3, close the fuel and oxidizer inlet 9. Simultaneously, begin supplying air and fuel into the annular cavity of the rotating detonation chamber, mixing them to form an explosive mixture. Subsequently, both spark plugs are simultaneously ignited to set the explosive mixture inside the pre-detonation tube 3 in the following manner: Figure 5 As shown. The flame continuously accelerates and forms a detonation wave within the pre-detonation tube 3, as... Figure 6 As shown, two detonation waves will enter the annular cavity of the rotating detonation chamber tangentially, directly initiating the explosive mixture within the chamber and forming a dual-wavehead propagation mode, as shown. Figure 7 As shown. Since the pre-detonation tube 3 is centrally symmetrical, the propagation mode of this dual-wavehead can simultaneously detonate the two pulse detonation tubes located at the centrally symmetrical positions, enabling them to work simultaneously. This avoids the situation where the combustion chamber is unstable due to the inconsistent working times of the two centrally symmetrical pulse detonation tubes 7 in operation.

[0049] Assuming that the air inlet 12 of the rotary valve 1 is located at the pulse detonation tubes 7 numbered C3, C4, C7 and C8, then the pulse detonation tubes 7 numbered C1, C2, C5 and C6 are in working condition; and the pulse detonation tubes 7 numbered C1, C2, C5 and C6 have completed air intake and fuel injection, and a uniformly mixed explosive mixture has been formed inside them; the valves on the detonation jet channels 10 numbered T1, T2, T5 and T6 are in the open state, and they are also filled with a uniformly mixed explosive mixture.

[0050] The rotating detonation wave first propagates to the inlet of detonation jet channels 10, numbered T1 and T5, which will directly detonate the explosive mixture within the detonation jet channels 10 and form a detonation wave therein, such as... Figure 8As shown. The detonation wave in the detonation jet channels 10, numbered T1 and T5, propagates to the outlet of the detonation jet channel 10 to form a detonation jet, and then enters the pulse detonation tubes 7, numbered C1 and C5, as shown. Figure 9 As shown, the rotating detonation wave continues to propagate. Subsequently, the rotating detonation wave will propagate to the inlet of the detonation jet channels 10 numbered T2 and T6, where the explosive mixture is detonated and a detonation wave is formed, as shown. Figure 10 As shown. The detonation wave in the detonation jet channels 10, numbered T2 and T6, propagates to the outlet of the detonation jet channel 10, forming a detonation jet, and enters the pulse detonation tubes 7, numbered C2 and C6, igniting the mixed gas inside. Figure 11 As shown.

[0051] As the rotary valve 1 rotates, the pulse detonation tubes 7 numbered C1, C5, C2, and C6 will sequentially enter the intake stage from the exhaust stage, and the pulse detonation tubes 7 numbered C3, C7, C4, and C8 will sequentially enter the working state.

[0052] Simply repeat the above process.

[0053] In summary, the pulse detonation combustion chamber based on rotating detonation wave ignition proposed in this invention achieves an organic combination of rotating detonation combustion and detonation jet ignition through specific structural design and spatial layout, and its beneficial effects are obvious.

[0054] The present invention also provides a pulse detonation turbine engine, which differs from conventional engines in that it employs a pulse detonation combustion chamber based on rotating detonation wave ignition provided by the present invention.

[0055] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention without departing from the principles and spirit of the present invention.

Claims

1. A pulse detonation combustion chamber based on rotating detonation wave ignition, characterized in that: It includes a detonation jet channel, a rotary valve, and a combustion chamber casing, a pulse detonation tube, and a rotary detonation chamber arranged radially from the inside to the outside; There are N pulse detonation tubes, which are evenly distributed along the circumference in the annular channel formed by the combustion chamber casing and the rotary detonation chamber; N≥2 and is an even number; the pulse detonation tube includes a mixing chamber and a main detonation chamber arranged sequentially along the axial direction; the front half of the mixing chamber is provided with a fuel nozzle for supplying fuel into the mixing chamber. There are N detonation jet channels, which are used to connect N pulse detonation tubes to the rotating detonation chamber, and the path of each detonation jet channel is matched with the propagation direction of the rotating detonation generated by the rotating detonation chamber; each detonation jet channel is provided with a valve near the pulse detonation tube for opening and closing the detonation jet channel; the opening and closing of the valve is controlled according to the working state of the pulse detonation tube corresponding to its detonation jet channel: when the pulse detonation tube has finished air intake and a uniform gas mixture has been formed inside it, the valve is open, and the valve is closed at other times; The rotary valve is located at the end of all pulse detonation tubes and is used to control the working state of each pulse detonation tube. Under the premise that each pulse detonation tube works intermittently, the rotary valve can ensure that at least half of the pulse detonation tubes are in the air intake state at any time. The outer wall of the rotating detonation chamber is provided with a pre-detonation tube. After the pre-detonation tube is detonated, it generates a detonation and enters the annular cavity of the rotating detonation chamber to form a rotating detonation. The rotating detonation enters the open detonation jet channel and detonates the explosive mixture therein, forming a high-energy detonation jet at the outlet of the detonation jet channel. The high-energy detonation jet flows into the corresponding pulse detonation tube to achieve ignition.

2. The pulse detonation combustion chamber based on rotating detonation wave ignition according to claim 1, characterized in that: There are multiple pre-detonation tubes, which are evenly distributed along the same circumference; the propagation direction of the detonation waves generated by all the pre-detonation tubes is the same, which is either counterclockwise or clockwise.

3. The pulse detonation combustion chamber based on rotating detonation wave ignition according to claim 2, characterized in that: The pre-detonation tube includes a straight pipe section and an arc-shaped pipe section connected to each other, with the straight pipe section and the arc-shaped pipe section being tangent at the connection point; the straight pipe section is tangent to and connected to the annular cavity of the rotating detonation chamber; the end of the arc-shaped pipe section is provided with an inlet for fuel and oxidizer; the pre-detonation tube is also provided with a spark plug, the spark plug being located close to the inlet for fuel and oxidizer.

4. The pulse detonation combustion chamber based on rotating detonation wave ignition according to claim 3, characterized in that: The mounting surface of the arc-shaped pipe section matches the outer wall of the rotating detonation chamber and is set close to the outer wall of the rotating detonation chamber.

5. The pulse detonation combustion chamber based on rotating detonation wave ignition according to any one of claims 1-4, characterized in that: The path of the detonation jet channel is arc-shaped, and the inner wall of the inlet end is tangent to the inner wall of the rotating detonation chamber annular cavity. The outlet end is located at the connection between the mixing chamber of the pulse detonation tube and the main detonation chamber.

6. The pulse detonation combustion chamber based on rotating detonation wave ignition according to claim 5, characterized in that: The rotary valve has multiple air inlets evenly distributed along the same circumference on its end face. By rotating the rotary valve, the relative position of the air inlets and each pulse detonation tube is changed, thereby controlling the working state of each pulse detonation tube: the pulse detonation tube connected to the air inlet is in the air intake state, and the other pulse detonation tubes are in the working state; the part of the rotary valve end face without air inlets acts as the thrust wall of the pulse detonation tube in the working state.

7. The pulse detonation combustion chamber based on rotating detonation wave ignition according to claim 6, characterized in that: The axial cross-section of a single air inlet is composed of four arc segments. The radial segment includes two arc segments that are coaxial with the rotary valve and tangent to the inner wall of the pulse detonation tube. The circumferential segment includes two arc segments with a diameter equal to the inner diameter of the pulse detonation tube. The two radial arc segments are arranged opposite each other, and the two circumferential arc segments are arranged opposite each other.

8. A pulse detonation turbine engine, characterized in that, Includes the pulse detonation combustion chamber based on rotating detonation wave ignition as described in any one of claims 1-7.

Images