A detonation combustion chamber and detonation engine

Abstract

This paper discloses a detonation combustor and a detonation engine. The detonation combustor includes: a combustor body with an annular combustion chamber, the annular combustion chamber having a rotating detonation wave generating region and an installation area located upstream of the rotating detonation wave generating region; and a reverse wave suppression device disposed in the installation area, configured to operate under the action of the pressure wave generated in the rotating detonation wave generating region to suppress the propagation of the pressure wave upstream of the installation area. The detonation combustor disclosed herein can effectively solve the problem of detonation wave pressure back transmission.

Description

Technical Field

[0001] This application relates to, but is not limited to, the field of engines, particularly a detonation combustion chamber and a detonation engine. Background Technology

[0002] Detonation combustion is achieved by compressing an explosive mixture with a leading fundamental wave, causing it to undergo a high-speed chemical reaction. Because detonation combustion has advantages such as high heat release per unit time, self-pressurization, high combustion efficiency, and low pollutant emissions, propulsion technology based on detonation combustion is an important development trend in future space technology.

[0003] The Rotating Detonation Engine (RDE) is a novel engine concept that generates thrust through continuous detonation combustion. Compared to the Pulse Detonation Engine (PDE), which also employs a detonation cycle, the RDE requires only a single initiation to achieve continuous detonation wave propagation. The RDE's thermal cycle efficiency is significantly higher than that of traditional jet engines based on isobaric combustion, and it also boasts a faster heat release rate and simpler structure. Therefore, the Rotating Detonation Engine has attracted widespread attention worldwide and has become one of the hottest research topics in the aerospace propulsion field.

[0004] A rotating detonation combustor is an annular combustor that utilizes detonation combustion. Fuel is supplied by multiple nozzles at the combustor head (upstream). The existing annular combustor operates by supplying fuel to the combustor head through nozzles, where it mixes with the mainstream oxidizer. A detonation wave can then pass through a region of appropriately proportioned explosive mixture. When the detonation wave passes through, the resulting high-pressure region propagates outwards. The back pressure propagating upstream affects fuel injection and the flow of the mainstream gas, thus impacting fuel-oxidizer mixing and hindering the stable propagation of rotating detonation. This also narrows the stable operating range of the rotating detonation combustor. Summary of the Invention

[0005] This application provides a detonation combustion chamber and a detonation engine, which can effectively solve the problem of detonation wave pressure back transmission.

[0006] This application provides a detonation combustion chamber, which includes:

[0007] The combustion chamber body is provided with an annular combustion chamber, the annular combustion chamber is provided with a rotating detonation wave generating area and an installation area located upstream of the rotating detonation wave generating area; and a reverse wave suppression device is provided in the installation area, configured to: operate under the action of the pressure wave generated in the rotating detonation wave generating area to suppress the pressure wave from propagating upstream of the installation area through the installation area.

[0008] Furthermore, the reverse wave suppression device includes a blocking component, which is configured to switch from a closed state to an open state under the action of the pressure wave generated in the rotating detonation wave generation zone.

[0009] When the shielding member is in the closed state, the flow area of ​​the installation area is S0, and when the shielding member is in the open state, the flow area of ​​the installation area is S1, wherein S0 > S1.

[0010] Furthermore, the annular combustion chamber includes an inner wall and an outer wall disposed opposite to each other in its radial direction, and one of the inner wall and the outer wall is configured as a mounting wall surface;

[0011] One end of the shielding member along the radial direction of the annular combustion chamber is rotatably connected to the mounting wall, and the other end of the shielding member along the radial direction of the annular combustion chamber is set as a free end. The shielding member is configured to rotate from a closed state to an open state under the action of the pressure wave generated in the rotating detonation wave generation zone.

[0012] Furthermore, a reserved groove is provided on the mounting wall. When the shielding member is in the closed state, the free end of the shielding member is located at the opening of the reserved groove and there is a channel between the shielding member and the reserved groove. This allows part of the pressure wave propagating upstream in the annular combustion chamber to enter the reserved groove through the channel, thereby pushing the shielding member to rotate to the open state.

[0013] Furthermore, the reserved groove is an annular groove extending 360° circumferentially along the mounting wall surface.

[0014] Furthermore, a guide groove communicating with the channel is also provided on the mounting wall surface. The guide groove is located at one end of the reserved groove in the axial direction of the annular combustion chamber near the rotating detonation wave generation area, and is configured to guide the pressure wave through the guide groove into the reserved groove.

[0015] Furthermore, the reverse wave suppression device also includes a first limiting device disposed within the annular combustion chamber. The first limiting device is configured to restrict the free end of the shielding member from abutting the mounting wall when the shielding member is in a closed state, so that the channel is formed between the free end of the shielding member and the reserved groove.

[0016] Furthermore, the reverse wave suppression device also includes a reset device, which cooperates with the blocking member and is configured to provide a reset force to switch the blocking member from the open state to the closed state.

[0017] Furthermore, the reset device includes an elastic element disposed in the mounting area, which uses a reset force to switch the blocking element from the open state to the closed state.

[0018] Furthermore, the reverse wave suppression device also includes a second limiting device disposed in the installation area. The second limiting device is configured to limit the shielding member when it is in the open state, so as to limit the shielding member to the open state.

[0019] Furthermore, the shielding member includes a plurality of baffles arranged circumferentially along the annular combustion chamber.

[0020] Furthermore, a gap is provided between adjacent baffles, and / or a gap is provided between the free end of the baffle and the wall of the annular combustion chamber.

[0021] Furthermore, the annular combustion chamber includes a throat section and a downstream section of the combustion chamber connected axially, wherein the radial width of the throat section is smaller than the radial width of the downstream section of the combustion chamber; the downstream section of the combustion chamber is configured as the rotating detonation wave generating area, and the throat section is configured as the mounting area; or,

[0022] The combustion chamber includes an upstream section and a downstream section connected along the axial direction, and the upstream section and the downstream section have the same radial width; the downstream section is set as the rotating detonation wave generating area, and the upstream section is set as the installation area.

[0023] This application embodiment also provides a knock engine, which includes a fuel injection section and the aforementioned knock combustion chamber. The fuel injection section is connected to the inlet of the knock combustion chamber, and the reverse wave suppression device restricts the pressure wave from entering the fuel injection section under the action of the pressure wave.

[0024] Compared to some other technologies, this application has the following advantages:

[0025] The detonation combustion chamber provided in this application embodiment has a reverse wave suppression device. When the detonation wave pressure (i.e., pressure wave) is transmitted in reverse, the reverse wave suppression device can operate to suppress the pressure wave from further propagating upstream of the installation area, thereby avoiding affecting the fuel injection and mainstream gas flow at the feed section, ensuring the smooth mixing of fuel and oxidant, stabilizing the propagation of the rotating detonation wave, and increasing the stable operating range of the rotating detonation combustion chamber.

[0026] The detonation engine provided in this application embodiment has the aforementioned detonation combustion chamber, which has high working efficiency and good combustion stability, effectively solves the back pressure problem in detonation combustion, and improves the working reliability of the detonation engine.

[0027] Other features and advantages of this application will be set forth in the following description. Attached Figure Description

[0028] The accompanying drawings are used to provide a further understanding of the technical solutions of this application and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of this application and do not constitute a limitation on the technical solutions of this application.

[0029] Figure 1 This is a schematic diagram of the detonation combustion chamber described in the embodiments of this application. Figure 1 ;

[0030] Figure 2 This is a schematic diagram of the detonation combustion chamber described in the embodiments of this application. Figure 2 (The fuel injection section has been removed);

[0031] Figure 3 This is a schematic diagram of the detonation combustion chamber described in the embodiments of this application. Figure 3 ;

[0032] Figure 4 for Figure 3 Enlarged view of the structure of section A in the middle;

[0033] Figure 5 This is a schematic diagram illustrating the configuration of the first limiting device described in an embodiment of this application;

[0034] Figure 6 This is a schematic diagram of the reverse wave suppression device described in the embodiments of this application (with the shielding component in the open state);

[0035] Figure 7 This is a schematic diagram illustrating the configuration of the second limiting device described in an embodiment of this application;

[0036] Figure 8 This is a schematic diagram of the detonation combustion chamber described in the embodiments of this application. Figure 4 (A throat section is provided).

[0037] Illustration:

[0038] 1-Combustion chamber body, 11-Annular combustion chamber, 111-Installation area, 112-Rotating detonation wave generation area, 113-Inner wall, 114-Outer wall, 115-Outer ring of combustion chamber, 116-Inner column of combustion chamber, 117-Throat section, 118-Downstream section of combustion chamber, 2-Reverse wave suppression device, 21-Shielding component, 211-Rotating shaft, 31-Reserved groove, 32-Guide groove, 33-First limiting device, 34-Second limiting device, 4-Fuel injection section. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be arbitrarily combined with each other.

[0040] A continuous rotating detonation engine is a power technology that utilizes detonation combustion. The detonation combustion chamber is the core of the engine, serving as the primary space for fuel mixing and combustion. Continuous rotating detonation combustion chambers are typically of annular slit design.

[0041] Detonation is a combustion mode that couples shock waves and flames (chemical reactions). It has a fast chemical reaction rate, a fast flame propagation speed (greater than 1000 m / s), and can generate extremely high pressure and temperature. Detonation waves generate extremely high gas pressure (greater than 1.5–5.5 MPa) and extremely high gas temperature (greater than 2800 K).

[0042] Back pressure: When a detonation wave is generated in the detonation chamber, the high-pressure area generated by the detonation wave will spread to the surrounding areas, and the back pressure is the area that spreads to the front end of the detonation chamber.

[0043] The back pressure propagating upstream in the combustion chamber affects fuel injection and the flow of mainstream gases, thus impacting fuel and oxidizer mixing and hindering the stable propagation of rotating detonation. This also narrows the stable operating range of the rotating detonation combustion chamber. Therefore, how to suppress the back propagation of detonation wave pressure remains a problem to be solved.

[0044] This application provides a detonation combustion chamber, such as... Figures 1 to 8 As shown, the detonation combustion chamber includes: a combustion chamber body 1, which has an annular combustion chamber 11, the annular combustion chamber 11 having a rotating detonation wave generating zone 112 and an installation zone 111 located upstream of the rotating detonation wave generating zone 112; and a reverse wave suppression device 2, which is located in the installation zone 111 and is configured to: operate under the action of the pressure wave generated by the rotating detonation wave generating zone 112 to suppress the pressure wave from propagating upstream of the installation zone 111 through the installation zone 111.

[0045] The knock combustion chamber includes a combustion chamber body 1 and a reverse wave suppression device 2. The reverse wave suppression device 2 is installed in the mounting area 111 of the annular combustion chamber 11. When the pressure wave generated by the rotating knock wave generating area 112 propagates to the mounting area 111 (i.e., the reverse wave), the reverse wave suppression device 2 is activated to block and suppress the reverse wave, thereby limiting its continued propagation to the upstream components of the combustion chamber body 1, so as to ensure the normal fuel supply to the upstream components (fuel injection section 4) of the combustion chamber body 1.

[0046] The reverse wave suppression device 2 is designed to operate under the action of pressure waves without the need for operator control, eliminating the reaction time required by the operator. The reverse wave suppression device 2 is sensitive, fast and accurate, and can effectively block and suppress the reverse propagation of pressure waves.

[0047] When a rotating detonation wave forms within the annular detonation chamber, the high-pressure area generated by the wave propagates upstream, forming a back pressure (pressure wave). When this back pressure reaches the reverse wave suppression device 2, it activates to prevent further upstream propagation. This improves the operating environment of the upstream components of the rotating detonation combustion chamber and increases the total pressure gain of the chamber. Figure 3 The upper part is the upstream region, and the lower part is the downstream region.

[0048] In practical use, the detonation combustion chamber may include an outer ring 115 and an inner column 116. The outer ring 115 is sleeved on the outside of the inner column 116 and is coaxially arranged with the inner column 116 to form an annular combustion chamber 11.

[0049] In one exemplary embodiment, such as Figures 4 to 7 As shown, the reverse wave suppression device 2 includes a shielding member 21, which is configured to switch from a closed state to an open state under the action of the pressure wave generated by the rotating detonation wave generation zone 112. When the shielding member 21 is in the closed state, the flow area of ​​the installation zone 111 is S0, and when the shielding member 21 is in the open state, the flow area of ​​the installation zone 111 is S1, wherein S0 > S1.

[0050] The reverse wave suppression device 2 includes a rotatable shield 21, which rotates to switch between a closed state and an open state.

[0051] Under the pressure wave generated in the rotating detonation wave generating zone 112, the shielding member 21 rotates to the open state to block the flow channel at the mounting zone 111; when no pressure wave is generated, the shielding member 21 is in the closed state, so that fuel and other substances can pass through the mounting zone 111 and enter the rotating detonation wave generating zone 112. The open state of the shielding member 21 can be perpendicular to the axial direction of the annular combustion chamber 11; the closed state of the shielding member 21 can be parallel to the axial direction of the annular combustion chamber 11.

[0052] When the blocking member 21 is in the closed state, the flow area of ​​the mounting area 111 is greater than that when the blocking member 21 is in the open state. In other words, when the blocking member 21 is in the open state, it does not need to completely close the flow channel of the mounting area 111; when the blocking member 21 is in the closed state, it can still provide some obstruction to the flow channel of the mounting area 111. This configuration reduces the precision requirements for the installation of the blocking member 21 and its own specifications, thereby reducing manufacturing costs.

[0053] In one exemplary embodiment, such as Figure 3As shown, the annular combustion chamber 11 includes an inner wall 113 and an outer wall 114 arranged opposite to each other in its radial direction, one of which is configured as a mounting wall; one end of the shielding member 21 in the radial direction of the annular combustion chamber 11 is rotatably connected to the mounting wall, and the other end of the shielding member 21 in the radial direction of the annular combustion chamber 11 is configured as a free end, and the shielding member 21 is configured to rotate from a closed state to an open state under the action of the pressure wave generated by the rotating detonation wave generation zone 112.

[0054] One end of the shield 21 is hinged to the inner wall 113 or the outer wall 114 of the combustion chamber. The shield 21 can be rotated to shield or open the flow channel of the installation area 111.

[0055] When the shield 21 rotates, one end serves as the pivot 211, and the other end rotates around the pivot 211 under the action of the pressure wave until it reaches the open state.

[0056] When the pressure wave is transmitted axially to the shield 21, the shield 21 is pushed by the pressure wave to rotate to the open state. When the shield 21 is in the open state, it can be perpendicular to the axial direction of the annular combustion chamber 11, that is, perpendicular to the propagation direction of the pressure wave, so as to block the propagation of the pressure wave.

[0057] In one exemplary embodiment, such as Figures 4 to 7 As shown, a reserved groove 31 is provided on the mounting wall. When the shielding member 21 is in the closed state, the free end of the shielding member 21 is located at the opening of the reserved groove 31 and there is a channel between the shielding member 21 and the reserved groove 31, so that part of the pressure wave propagating upstream in the annular combustion chamber 11 enters the reserved groove 31 through the channel, thereby pushing the shielding member 21 to rotate to the open state.

[0058] Taking the example of a reserved groove 31 being formed on the outer wall 114: A reserved groove 31 is formed on the outer wall 114 of the annular combustion chamber 11. The blocking member 21 is located inside the reserved groove 31 in the radial direction of the annular combustion chamber 11, so that part of the pressure wave propagating axially in the annular combustion chamber 11 enters the reserved groove 31, thereby pushing the blocking member 21 to rotate and blocking the entrance of the annular combustion chamber 11.

[0059] There is a channel between the free end of the shield 21 and the reserved groove 31. This channel serves as the entrance for the pressure wave to enter the reserved groove 31. After the pressure wave enters the reserved groove 31, it drives the shield 21 to rotate.

[0060] It should be understood that the reserved groove 31 can also be opened on the inner wall 113, similar to the above-mentioned setting method, which will not be described in detail here.

[0061] In an exemplary embodiment, the reserved groove 31 is an annular groove extending 360° circumferentially along the mounting wall surface.

[0062] The reserved slot 31 is simple to set and easy to process, which helps to reduce the overall manufacturing cost of the detonation combustion chamber.

[0063] In one exemplary embodiment, such as Figure 4 system Figure 7 As shown, a guide groove 32 communicating with the channel is also provided on the mounting wall. The guide groove 32 is located at one end of the reserved groove 31 in the axial direction of the annular combustion chamber 11, close to the rotating detonation wave generation area 112, and is configured to guide the pressure wave through the guide groove 32 into the reserved groove 31.

[0064] The guide groove 32 is located at one end of the reserved groove 31 in the axial direction of the annular combustion chamber 11, near the rotating detonation wave generation area 112. In other words, when the shielding member 21 is in the closed state, the guide groove 32 is located at one end of the annular combustion chamber 11 in the axial direction, near the free end of the shielding member 21. After setting the guide groove 32, more axially propagating pressure waves can be guided into the reserved groove 31, making the path of the pressure waves into the reserved groove 31 smoother, thereby improving the effect of the pressure waves driving the shielding member 21 to rotate, and ensuring that the shielding member 21 can reliably and quickly act under the action of the pressure waves to shield subsequent pressure waves.

[0065] In one exemplary embodiment, such as Figure 5 As shown, the reverse wave suppression device 2 also includes a first limiting device 33 disposed in the annular combustion chamber 11. The first limiting device 33 is configured to restrict the free end of the shielding member 21 from abutting the mounting wall when the shielding member 21 is in the closed state, so that a channel is formed between the free end of the shielding member 21 and the reserved groove 31.

[0066] The first limiting device 33 is used to limit the shield 21 when it is in the closed state, preventing the shield 21 from directly abutting the mounting wall, thereby closing the channel between the free end of the shield 21 and the reserved groove 31. The first limiting device 33 can limit the shield 21 in the axial direction parallel to the annular combustion chamber 11, leaving a channel for pressure waves to pass through between the free end of the shield 21 and the reserved groove 31.

[0067] The first limiting device 33 can be a limiting block formed on the mounting wall, such as... Figure 5 As shown.

[0068] In an exemplary embodiment, the reverse wave suppression device 2 further includes a reset device that cooperates with the blocking member 21 and is configured to provide a reset force that switches the blocking member 21 from an open state to a closed state.

[0069] After the shielding member 21 completes the process of shielding the pressure wave, the reset device provides a reset force to switch the shielding member 21 from the open state to the closed state, in preparation for blocking and suppressing the next pressure wave.

[0070] After setting the reset device, the obstruction component 21 can be prevented from causing adverse effects such as obstruction to normal fuel delivery.

[0071] In an exemplary embodiment, the reset device includes an elastic member disposed in the mounting area 111, which uses a reset force to switch the blocking member 21 from an open state to a closed state.

[0072] The reset device can be an elastic element, such as a torsion spring sleeved on one end of the blocking member 21 (i.e., the rotating shaft 211). One end of the torsion spring abuts against the blocking member 21, and the other end abuts against the mounting wall. The blocking member 21 is rotated and reset by its own elastic force.

[0073] In one exemplary embodiment, such as Figure 7 As shown, the reverse wave suppression device 2 also includes a second limiting device 34 disposed in the mounting area 111. The second limiting device 34 is configured to limit the shielding member 21 when it is in the open state, so as to limit the shielding member 21 to the open state.

[0074] The second limiting device 34 is used to limit the shielding member 21 when it is in the open state, so as to prevent the shielding member 21 from rotating excessively and losing its shielding effect or being difficult to reset. The second limiting device 34 can limit the shielding member 21 in the axial direction perpendicular to the annular combustion chamber 11, so as to prevent the shielding member 21 from rotating further.

[0075] The second limiting device 34 can be a limiting protrusion formed on the wall surface, such as... Figure 7 As shown. That is, when the blocking member 21 is installed on the outer wall 114, the limiting protrusion can be provided on the inner wall 113 so that the free end of the blocking member 21 can be engaged.

[0076] Of course, the second limiting device 34 can also be a limiting structure located at one end of the blocking member 21 (i.e., at the rotating shaft 211), and this application does not limit this.

[0077] In one exemplary embodiment, such as Figure 2 As shown, the shielding member 21 includes a plurality of baffles arranged circumferentially along the annular combustion chamber 11.

[0078] The shielding member 21 includes multiple baffles arranged circumferentially, and the multiple baffles can be configured to have the same shape and structure. The multiple baffles rotate together under the action of the pressure wave to block and suppress the pressure wave.

[0079] It should be understood that the specific size and quantity of the baffles can be adjusted according to actual needs.

[0080] In one exemplary embodiment, such as Figure 2 As shown, a gap is provided between adjacent baffles, and / or a gap is provided between the free end of the baffle and the wall of the annular combustion chamber 11.

[0081] A gap is provided between adjacent baffles to prevent them from rubbing against each other and interfering with each other during rotation. A gap is also provided between the free end of the baffle and the mating wall of the annular combustion chamber 11 to ensure that the free end of the baffle will not get stuck with the mating wall when it is open, thus preventing the baffle from failing to reset and affecting subsequent fuel supply.

[0082] It should be understood that during the process of the baffle blocking and suppressing the pressure wave, the baffle does not need to completely seal the flow channel of the installation area 111. Leaving a gap can still achieve a good reverse wave suppression effect.

[0083] In one exemplary embodiment, such as Figure 8 As shown, the annular combustion chamber 11 includes a throat section 117 and a downstream section 118 connected axially. The radial width of the throat section 117 is smaller than the radial width of the downstream section 118. The downstream section 118 is configured as a rotating detonation wave generating region 112, and the throat section 117 is configured as an installation region 111; or, as shown... Figure 3 As shown, the combustion chamber includes an upstream section and a downstream section connected along the axial direction, and the radial widths of the upstream section and the downstream section are the same; the downstream section is set as a rotating detonation wave generating area 112, and the upstream section is set as an installation area 111.

[0084] There are two main types of structures for the annular combustion chamber 11:

[0085] One type of annular combustion chamber 11 includes an upstream section and a downstream section of the combustion chamber along the entire axial direction. The radial widths of the upstream section and the downstream section of the combustion chamber are the same, and the shielding member 21 is disposed in the upstream section of the combustion chamber.

[0086] Another type of annular combustion chamber 11 has a throat section 117, that is, the annular combustion chamber 11 includes a throat section 117 and a downstream section 118 connected along the axial direction. The radial width of the throat section 117 is smaller than the radial width of the downstream section 118. The shielding member 21 is disposed in the throat section 117. Disposing the shielding member 21 in the throat section 117 with a smaller radial width is beneficial to reducing the size of the shielding member 21 and can obtain a better reverse wave suppression effect.

[0087] The rotary detonation combustor provided in this embodiment of the application, which prevents back pressure transmission, has a shielding member 21 positioned at the front end of the rotary detonation combustor, after the fuel injection section 4, and before the propagation position of the rotary detonation wave. The shielding member 21 comprises multiple baffles. When all baffles are open, they block the rotary detonation combustor channel; when closed, they fit perfectly into the pre-reserved slot 31. After the back pressure propagates forward through the guide groove 32 into the pre-reserved slot 31, the baffles open under the action of the back pressure, preventing further upstream propagation of the back pressure. This improves the working environment of the upstream components of the rotary detonation combustor and increases the total pressure gain of the rotary detonation combustor. The rotary detonation combustor provided in this embodiment has a simple structure. It utilizes the high-pressure characteristics of the back pressure generated by the detonation wave to control the opening and closing of the shielding member 21, preventing the forward propagation of back pressure, making it simple and reliable.

[0088] This application embodiment also provides a knock engine, which includes a fuel injection section 4 and the aforementioned knock combustion chamber. The fuel injection section 4 is connected to the inlet of the knock combustion chamber, and the reverse wave suppression device 2 restricts the pressure wave from entering the fuel injection section 4 under the action of the pressure wave.

[0089] The detonation engine provided in this application embodiment has the aforementioned detonation combustion chamber, which has high working efficiency and good combustion stability, effectively solves the back pressure problem in detonation combustion, and improves the working reliability of the detonation engine.

[0090] In the description of this application, it should be noted that the orientation or positional relationship indicated by terms such as "upper", "lower", "one end", and "one side" is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing this application and simplifying the description, and does not indicate or imply that the structure referred to has a specific orientation, or is constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of this application.

[0091] In the description of the embodiments of this application, unless otherwise expressly specified and limited, the terms "connection," "assembly," and "installation" should be interpreted broadly. For example, the term "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0092] The embodiments described in this application are exemplary and not limiting, and it will be apparent to those skilled in the art that many more embodiments and implementations are possible within the scope of the embodiments described herein. Although many possible combinations of features are shown in the drawings and discussed in the detailed description, many other combinations of the disclosed features are also possible. Unless specifically limited, any feature or element of any embodiment may be used in combination with or in lieu of any other feature or element in any other embodiment.

[0093] This application includes and contemplates combinations of features and elements known to those skilled in the art. The embodiments, features, and elements disclosed in this application can also be combined with any conventional features or elements to form a unique technical solution as defined by the claims. Any feature or element of any embodiment can also be combined with features or elements from other technical solutions to form another unique technical solution as defined by the claims. Therefore, it should be understood that any feature shown and / or discussed in this application can be implemented individually or in any suitable combination. Therefore, the embodiments are not limited except by the limitations imposed by the appended claims and their equivalents. Furthermore, various modifications and changes can be made within the scope of the appended claims.

Claims

1. A detonation combustion chamber, characterized in that, include: The combustion chamber body is provided with an annular combustion chamber, which is provided with a rotating detonation wave generating area and an installation area located upstream of the rotating detonation wave generating area; and A reverse wave suppression device is provided in the installation area and is configured to operate under the action of the pressure wave generated in the rotating detonation wave generation area to suppress the propagation of the pressure wave from the installation area to the upstream of the installation area. The reverse wave suppression device includes a shielding component, which is configured to switch from a closed state to an open state under the action of the pressure wave generated in the rotating detonation wave generation zone; when the shielding component is in the closed state, the flow area of ​​the installation zone is S0, and when the shielding component is in the open state, the flow area of ​​the installation zone is S1, wherein S0 > S1. The annular combustion chamber includes an inner wall and an outer wall that are arranged opposite to each other in the radial direction, and one of the inner wall and the outer wall is configured as a mounting wall surface; one end of the shielding member in the radial direction of the annular combustion chamber is rotatably connected to the mounting wall surface, and the other end of the shielding member in the radial direction of the annular combustion chamber is configured as a free end; the shielding member is configured to rotate from a closed state to an open state under the action of the pressure wave generated in the rotating detonation wave generation zone. A reserved groove is provided on the mounting wall. When the shielding member is in the closed state, the free end of the shielding member is located at the opening of the reserved groove and there is a channel between the shielding member and the reserved groove. This allows part of the pressure wave propagating upstream in the annular combustion chamber to enter the reserved groove through the channel, thereby pushing the shielding member to rotate to the open state.

2. The detonation combustion chamber according to claim 1, characterized in that, The reserved groove is an annular groove that extends 360° circumferentially along the mounting wall surface.

3. The detonation combustion chamber according to claim 1, characterized in that, The mounting wall surface is also provided with a guide groove that communicates with the channel. The guide groove is located at one end of the reserved groove in the axial direction of the annular combustion chamber near the rotating detonation wave generation area, and is configured to guide the pressure wave through the guide groove into the reserved groove.

4. The detonation combustion chamber according to claim 1, characterized in that, The reverse wave suppression device further includes a first limiting device disposed in the annular combustion chamber. The first limiting device is configured to restrict the free end of the shielding member from abutting the mounting wall when the shielding member is in the closed state, so that the channel is formed between the free end of the shielding member and the reserved groove.

5. The detonation combustion chamber according to any one of claims 1 to 4, characterized in that, The reverse wave suppression device further includes a reset device, which cooperates with the blocking member and is configured to provide a reset force to switch the blocking member from the open state to the closed state.

6. The detonation combustion chamber according to claim 5, characterized in that, The reset device includes an elastic element disposed in the installation area, and the elastic element uses a reset force to switch the blocking element from the open state to the closed state.

7. The detonation combustion chamber according to any one of claims 1 to 4, characterized in that, The reverse wave suppression device further includes a second limiting device disposed in the installation area. The second limiting device is configured to limit the shielding member when it is in the open state, so as to limit the shielding member to the open state.

8. The detonation combustion chamber according to any one of claims 1 to 4, characterized in that, The shielding component includes multiple baffles arranged circumferentially along the annular combustion chamber.

9. The detonation combustion chamber according to claim 8, characterized in that, A gap is provided between adjacent baffles, and / or a gap is provided between the free end of the baffle and the wall of the annular combustion chamber.

10. The detonation combustion chamber according to any one of claims 1 to 4, characterized in that, The annular combustion chamber includes a throat section and a downstream section of the combustion chamber connected axially, wherein the radial width of the throat section is smaller than the radial width of the downstream section of the combustion chamber; the downstream section of the combustion chamber is configured as the rotating detonation wave generating area, and the throat section is configured as the mounting area; or, The combustion chamber includes an upstream section and a downstream section connected along the axial direction, and the upstream section and the downstream section have the same radial width; the downstream section is set as the rotating detonation wave generating area, and the upstream section is set as the installation area.

11. A knock engine, characterized in that, It includes a fuel injection section and a knock combustion chamber as described in any one of claims 1 to 10, wherein the fuel injection section is connected to the inlet of the knock combustion chamber, and the reverse wave suppression device restricts the pressure wave from entering the fuel injection section under the action of the pressure wave.

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