A rotating detonation combustion chamber with variable flow resistance

Abstract

The present invention discloses a rotating detonation combustion chamber with variable flow resistance, comprising an outer wall of a channel, an inner ring body, an injection disc, an oil inlet ring, an outer wall of the combustion chamber, a control shaft, a No. 1 flow resistance control panel, a No. 2 flow resistance control panel, an inner wall of the combustion chamber, and a nozzle; a plurality of fan-shaped cavities are evenly spaced on the inclined surface at the end of the inner ring body, a plurality of fan-shaped blank areas are evenly spaced on the inner wall of the combustion chamber, a plurality of fan-shaped panels are evenly spaced on the No. 1 flow resistance control panel and the No. 2 flow resistance control panel, the No. 1 flow resistance control panel cooperates with the inner wall of the inner ring body, and the No. 2 flow resistance control panel cooperates with the inner wall of the combustion chamber, and the control shaft is used to simultaneously drive the axial movement and axial rotation of the No. 1 flow resistance control panel and the No. 2 flow resistance control panel. As an afterburner combustion chamber, the present invention can switch between two operating modes, providing a new approach to improving engine performance.

Description

Technical Field

[0001] The present invention relates to the technical field of rotating detonation engines, and in particular to a rotating detonation combustion chamber with variable flow resistance. Background Art

[0002] With the development of the aviation industry, the demand for aircraft power performance is becoming increasingly stringent. Traditional turbine propulsion systems have certain limitations in increasing thrust. Using a rotating detonation combustor as an afterburner can effectively improve combustion efficiency and reduce emissions. Currently, research on the application of rotating detonation combustors in traditional turbine propulsion systems focuses on using them as the engine's main combustion chamber. Afterburners are an essential component of aircraft engines, and improving their performance can further enhance engine power output.

[0003] The rotating detonation afterburner can use the supplemental fuel to re-organize the combustion of unburned oxygen in the fuel gas and oxygen in the surrounding air to further increase the fuel gas temperature. Compared with the traditional afterburner, it has a simple structure. Due to the characteristics of rotating detonation, the flame propagates in the combustion chamber in the form of a shock wave, and the flame stability is good. The combustion chamber is small in size and the simple structure is effective in controlling the overall weight of the engine.

[0004] In order to reduce the impact of the forward transmission of the rotating detonation wave pressure and speed up the filling of combustibles, the combustion chamber inlet is usually designed to be convergent and divergent to accelerate the incoming flow. However, in the non-afterburner state, the inlet airflow at the throat of the rotating detonation combustion chamber will reach supersonic speed, resulting in a large total pressure loss, which is not conducive to increasing the thrust of aviation turbine engines. Summary of the Invention

[0005] The object of the present invention is to provide a rotating detonation combustion chamber with variable flow resistance, which relies on a flow resistance control panel to achieve the conversion between the afterburner state and the non-afterburner state, thereby reducing the total pressure loss in the non-afterburner state.

[0006] To achieve the above object, the technical solution adopted by the present invention is:

[0007] A rotating detonation combustion chamber with variable flow resistance, characterized by comprising:

[0008] A detonation combustion chamber, the detonation combustion chamber having an annular combustion cavity, an oil inlet ring installed on the outer wall of the detonation combustion chamber and near the entrance of the annular combustion cavity, the oil inlet ring being in communication with the annular combustion cavity; the oil inlet ring being used to replenish fuel to the throat of the detonation combustion chamber;

[0009] An airflow regulating portion is located at one end of the detonation combustion chamber and includes an inner ring body, an outer channel wall of the inner ring body being sleeved thereon, an airflow channel being formed between the inner ring body and the outer channel wall, an outlet of the airflow channel being in communication with the annular combustion chamber; an end of the inner ring body proximate to the detonation combustion chamber is formed into an inclined surface, the inclined surface being located within the airflow channel, such that a downstream section of the airflow channel has a convergent structure, thereby increasing the incoming flow velocity;

[0010] a nozzle, the nozzle being located at the other end of the detonation combustion chamber, the nozzle being connected to the outlet of the annular combustion chamber;

[0011] A rotating assembly comprising a control shaft movably disposed in the middle of the inner ring body, a first flow resistance control panel mounted on an end of the control shaft, and a second flow resistance control panel coaxially connected to the first flow resistance control panel;

[0012] A plurality of fan-shaped panels are arranged at intervals on the No. 1 flow resistance control panel and the No. 2 flow resistance control panel, a plurality of fan-shaped cavities are arranged at intervals on the inclined surface of the inner ring body end, a plurality of fan-shaped blank areas are arranged at intervals on the inner side surface of the detonation combustion chamber, and the fan-shaped cavities and the fan-shaped blank areas are located in the same axial direction; the control shaft is used to drive the No. 1 flow resistance control panel and the No. 2 flow resistance control panel to move axially and rotate axially, so that the No. 1 flow resistance control panel is aligned with or staggered from the fan-shaped cavity, the No. 1 flow resistance control panel is fitted with or separated from the inclined surface of the inner ring body end, the No. 2 flow resistance control panel is aligned with or staggered from the fan-shaped blank area, and the No. 2 flow resistance control panel is fitted with or separated from the inner side surface of the detonation combustion chamber, so as to realize the switching between the afterburner state and the non-afterburner state.

[0013] Furthermore, the detonation combustion chamber includes an inner wall of the combustion chamber and an outer wall of the combustion chamber that is sleeved on the inner wall of the combustion chamber. The annular combustion chamber is formed between the inner wall of the combustion chamber and the outer wall of the combustion chamber, and the side of the inner wall of the combustion chamber close to the entrance of the annular combustion chamber is the inner side.

[0014] Furthermore, a positioning ring is provided at the center of the inclined surface at the end of the inner ring body, and a positioning groove adapted to the positioning ring is provided at the front end of the No. 1 flow resistance control panel. In the force-applied state, the positioning ring is embedded in the positioning groove.

[0015] Furthermore, the No. 2 flow resistance control panel is coaxially connected to the No. 1 flow resistance control panel via a connecting ring, and the No. 1 flow resistance control panel is coaxially connected to the control shaft.

[0016] Furthermore, a sector-shaped wall surface is provided on the inner side surface of the inner wall of the combustion chamber, and the connecting ring is located between the inner side surface of the inclined surface at the end of the inner ring body and the outer edge of the sector-shaped wall surface.

[0017] Furthermore, the No. 1 flow resistance control panel and the No. 2 flow resistance control panel are provided with four 45° fan-shaped panels at equal intervals.

[0018] Furthermore, the nozzle is composed of a nozzle outer wall and a nozzle inner wall.

[0019] Furthermore, it further comprises an oil spray plate, through which the oil inlet ring is connected to the annular combustion chamber. Preferably, the oil inlet ring and the oil spray plate are connected by a flange.

[0020] Furthermore, the upstream section of the airflow channel is a rectifying section with a rectangular longitudinal cross-section, and the downstream section is a convergent section with a trapezoidal longitudinal cross-section.

[0021] Compared with the prior art, the present invention has the following advantages or technical effects:

[0022] It can switch between afterburner state and non-afterburner state. In afterburner state, the rotating detonation combustion chamber works. In non-afterburner state, the flow resistance panel is opened to reduce flow resistance and reduce total pressure loss. (2) It can be used as an afterburner combustion chamber for aircraft engines. The ring structure at the head and tail is more compact to match the upstream and downstream components. (3) The overall design has modular characteristics, which is easy to disassemble and assemble, convenient for maintenance and secondary improvement; (4) It is small in size and simple in structure. It does not require a flame stabilizer or rectifier inside. It only needs one ignition, which makes up for the shortcomings of ordinary rotating detonation combustion chambers and improves the combustion efficiency of traditional afterburner combustion chambers. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions implemented in the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0024] Figure 1 It is a front cross-sectional view of the present invention;

[0025] Figure 2 It is a left view and subjective cross-sectional view of the inner wall structure of the inner ring body of the present invention;

[0026] Figure 3 Schematic diagram of the three-dimensional structure of the inner ring body of the present invention;

[0027] Figure 4 It is a left view and a subjective cross-sectional view of the combustion chamber inner wall structure of the present invention;

[0028] Figure 5 It is a left side view and subjective cross-sectional view of the rotating assembly of the present invention;

[0029] Figure 6 It is a schematic diagram of the three-dimensional structure of the rotating assembly of the present invention;

[0030] Figure 7 This is a schematic diagram of the working of the rotating detonation combustion chamber under afterburner state;

[0031] Figure 8 This is a schematic diagram of the rotating detonation combustion chamber working in the non-afterburner state;

[0032] Figure 9 It is the pressure curve along the process in the non-forced state;

[0033] Figure 10 This is the total pressure cloud diagram of the numerical simulation section under the non-stressed state;

[0034] Figure 11 It is the pressure curve diagram along the working process of the combustion chamber under the afterburner state;

[0035] In the figure, 1. Outer wall of the channel, 2. Fuel injection disc, 3. Oil inlet ring, 4. Outer wall of the combustion chamber, 5. Annular combustion chamber, 6. Inner ring body, 6-1. Fan-shaped cavity, 6-2. Positioning ring, 6-3. Inner ring body wall flange, 7. No. 1 flow resistance control panel, 7-1. Positioning groove, 8. No. 2 flow resistance control panel, 8-1. Connecting ring, 9. Inner wall of the combustion chamber, 9-1. Fan-shaped wall surface, 9-2. Inner wall flange of the combustion chamber, 9-3. Fan-shaped blank area, 10. Air flow channel, 11. Control shaft, 11-1. Fan-shaped cavity, 12. Outer wall of the nozzle, 13. Inner wall of the nozzle. DETAILED DESCRIPTION

[0036] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only 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 making creative efforts are within the scope of protection of the present invention.

[0037] Please refer to the attached Figure 1 -Attached Figure 11The present invention provides a rotating detonation combustion chamber with variable flow resistance, comprising a detonation combustion chamber, an airflow regulating portion, a nozzle and a rotating assembly. The detonation combustion chamber comprises an inner combustion chamber wall 9, an outer combustion chamber wall 4 sleeved on an inner combustion chamber wall 6, an annular combustion chamber 5 is formed between the inner combustion chamber wall 6 and the outer combustion chamber wall 4, an oil inlet ring 3 is installed on the outer combustion chamber wall 4 and near the entrance of the annular combustion chamber 5, the oil inlet ring 3 is connected to the annular combustion chamber 5, and fuel is provided to the annular combustion chamber 5 at the throat of the combustion chamber. The airflow regulating portion is located at the left end of the detonation combustion chamber, comprising an inner ring body 6, an outer channel wall 1 sleeved on the inner ring body 6, an airflow channel 10 is formed between the inner ring body 6 and the outer channel wall 1, and the outlet of the airflow channel 10 is connected to the annular combustion chamber 5. The right end of the inner ring body 6 is inclined, and the inclined surface is located in the airflow channel 10, so that the downstream section of the airflow channel 10 has a convergent structure, which can increase the incoming flow velocity. In this embodiment, four 45° sector-shaped cavities 6-1 are evenly spaced on the inner wall surface (i.e., the inclined surface at the end) of the inner ring body 6. Figure 3 As shown, a positioning ring 6-2 is provided at the center of the inner wall of the inner ring body 6. In the afterburner state, the positioning ring 6-2 is embedded in a positioning groove 7-1 provided at the front end of the No. 1 flow resistance control panel 7. Where the No. 1 flow resistance control panel 7 enters the sector-shaped cavity 6-1, it coincides with the inclined surface of the inner wall of the inner ring body 6, forming a closed inclined surface. The nozzle is located at the right end of the detonation combustion chamber. It is composed of a nozzle outer wall 12 and a nozzle inner wall 13. The nozzle orifice communicates with the outlet of the annular combustion chamber 5.

[0038] The rotating assembly includes a control shaft 11 movably arranged in the middle of the inner ring body 6, a No. 1 flow resistance control panel 7 installed at the end of the control shaft 11, and a No. 2 flow resistance control panel 8 coaxially connected to the No. 1 flow resistance control panel 7. The No. 1 flow resistance control panel 7 and the No. 2 flow resistance control panel 8 are provided with four 45° fan-shaped panels at equal intervals and are located in the same axial direction (the fan-shaped panels of the No. 1 flow resistance control panel 7 and the No. 2 flow resistance control panel 8 overlap on the axis). The No. 2 flow resistance control panel 8 is coaxially connected to the No. 1 flow resistance control panel 7 through a connecting ring 8-1. Four fan-shaped blank areas 9-3 are provided on the inner wall surface of the inner wall 9 of the combustion chamber at equal intervals. The fan-shaped blank areas 9-3 are located in the same axial direction as the fan-shaped cavity 6-1 (overlap on the axis). The No. 2 flow resistance control panel 8 has the same shape as the fan-shaped blank area 9-3, as shown in the attached figure. Figure 6As shown, when control shaft 11 rotates, the fan-shaped panels of fluid resistance control panel No. 1 and fluid resistance control panel No. 2, 8, move synchronously. These panels are provided with positioning grooves 7-1. Under applied force, control shaft 11 drives fluid resistance control panel No. 1 to move axially toward the inclined surface at the end of inner ring body 6, causing positioning groove 7-1 of fluid resistance control panel No. 1 to enter positioning ring 6-2. Inner ring body 6 is connected to combustion chamber inner wall 9 via two connectors. The connection between control shaft 11 and fluid resistance control panel No. 1, 7, is symmetrically provided with two fan-shaped cavities 11-1 for the passage of these two connectors. To ensure proper rotation of the rotating components, the fan-shaped cavities are angled at no less than 90°.

[0039] The combustion chamber inner wall 9 and the combustion chamber outer wall 4 and the second flow resistance control panel 8 together constitute the detonation combustion zone. The inner wall surface of the combustion chamber inner wall 9 is composed of four fan-shaped panels 9-1 as shown in the attached figure. Figure 4 As shown, in the force-added state, the No. 2 flow resistance control panel 8 moves to the fan-shaped blank area 9-3, forming a closed circular wall with the fan-shaped wall 9-1. In the non-forced working state, the No. 2 flow resistance control panel 8 and the fan-shaped wall 9-1 are located in the same axial direction, opening the airflow channel.

[0040] The inner ring body inner wall flange 6-3 and the combustion chamber inner wall flange 9-2 are connected through the fan-shaped cavity 11-1 to form a complete structural wall surface; the connecting ring 8-1 is located between the right lower wall surface 6-3 of the inner ring body 6 and the combustion chamber inner wall 9 and the fan-shaped wall surface 9-1.

[0041] The upstream section of the airflow channel 10 is a rectifying section with a rectangular longitudinal cross-section, while the downstream section is a converging section with a trapezoidal longitudinal cross-section. High-temperature combustion gases after the turbine are mixed with the surrounding air in the rectifying section. Since the rotating detonation combustion chamber has certain requirements for the incoming flow velocity, the incoming gas velocity is increased to sonic and supersonic speeds through the converging section. Fuel is replenished at the throat of the combustion chamber, and the high-speed incoming flow fills the combustion chamber with fuel. After ignition, the flame propagates in a high-speed, stable rotation within the annular combustion chamber. Fresh reactants are continuously fed into the combustion chamber by the high-speed airflow, providing energy for the detonation wave. When the detonation combustion chamber is not operating, it switches to a non-afterburner state. The control shaft 11 drives the two flow resistance panels to axially move, causing the positioning ring 6-2 to exit the positioning groove 7-1 and rotate 45° clockwise. The airflow channel opens, the rotating detonation combustion chamber pressure decreases, the airflow rate increases, and the pressure loss decreases.

[0042] In the present invention, the control shaft 11 can be driven by a connecting rod or a motor. The flow resistance control panel is closed to activate the boosted state, and opened to activate the non-boosted state. In the non-boosted state, the control shaft 11 moves axially, causing the positioning ring 6-2 to exit the positioning groove 7-1 and rotate 45° along the inner ring cavity of the rotating assembly. When the boosted state is activated, the control shaft 11 moves 45° along the inner ring cavity of the rotating assembly, causing the positioning ring 6-2 to move axially and enter the positioning groove 7-1.

[0043] The present invention is provided with an injection disc 2. The fuel content in the high-temperature combustion gas after the turbine is relatively low, which is insufficient to support the detonation combustion in the afterburner. In order to ensure the normal operation of the rotating detonation combustion chamber, the injection disc 2 performs supplementary combustion at the throat position to keep the air-fuel ratio in the stable working range of the rotating detonation combustion chamber.

[0044] In the non-powered state, the present invention can effectively reduce the air flow resistance, speed up the air flow, and reduce the total pressure loss. Figure 9 、 10 As shown in the figure, the total pressure curve along the combustion chamber interface and the total pressure cloud diagram in the non-afterburning state are obtained according to the simulation results. It can be seen from the figure that the total pressure recovery coefficient in the non-afterburning state reaches 83.02%, which greatly improves the performance of the engine in the non-afterburning state. Figure 11 The figure shows the pressure curve along the afterburner when it is working. It can be seen from the figure that the maximum compression ratio of the afterburner in the working state reaches 104.5%. Compared with the traditional afterburner, the compression ratio is increased and the performance of the combustion chamber is improved.

[0045] The combustion chamber utilizes rotating detonation combustion to improve combustion efficiency and achieve flow resistance regulation. As an afterburner, it can switch between afterburner and non-afterburner modes. Engine air and high-temperature exhaust gas from the turbine are mixed in the rectifying section, accelerated in the convergent section, and secondary fuel injection is performed at the throat of the afterburner. After mixing, detonation combustion occurs in the detonation chamber, with detonation products discharged through the nozzle. When the afterburner is not in operation, the flow resistance panel of the present invention can be opened to reduce flow resistance, minimize total pressure loss, and accelerate gas discharge. This allows for switching between two operating modes, providing a new approach to improving engine performance.

[0046] Compared with traditional combustion chambers, rotating detonation combustion chambers have the characteristics of simple and compact structure, high cycle efficiency and small size. On this basis, the present invention provides switching between two different working modes, which can be applied to afterburner combustion chambers. When the afterburner combustion chamber is not working, it reduces the airflow loss, flexibly responds to the engine exiting the working state, and effectively solves the problem of total pressure loss caused by the combustion chamber structure.

[0047] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A rotating detonation combustion chamber with variable flow resistance, characterized in that: include: A detonation combustion chamber, the detonation combustion chamber having an annular combustion chamber (5), an oil inlet ring (3) being installed on the outer wall of the detonation combustion chamber and near the entrance of the annular combustion chamber (5), the oil inlet ring (3) being in communication with the annular combustion chamber (5); An airflow regulating portion is located at one end of the detonation combustion chamber, comprising an inner ring body (6), a channel outer wall (1) sleeved on the inner ring body (6), an airflow channel (10) formed between the inner ring body (6) and the channel outer wall (1), an outlet of the airflow channel (10) being in communication with the annular combustion chamber (5); an end of the inner ring body (6) close to the detonation combustion chamber is formed into an inclined surface, the inclined surface being located in the airflow channel (10), so that the downstream section of the airflow channel (10) is in a convergent structure; A nozzle, the nozzle being located at the other end of the detonation combustion chamber, the nozzle being connected to the outlet of the annular combustion chamber (5); A rotating assembly comprising a control shaft (11) movably arranged in the middle of the inner ring body (6), a first flow resistance control panel (7) mounted on the end of the control shaft (11), and a second flow resistance control panel (8) coaxially connected to the first flow resistance control panel (7); A plurality of fan-shaped panels are arranged at intervals on the first flow resistance control panel (7) and the second flow resistance control panel (8); a plurality of fan-shaped cavities (6-1) are arranged at intervals on the inclined surface of the end of the inner ring body (6); a plurality of fan-shaped blank areas (9-3) are arranged at intervals on the inner side surface of the detonation combustion chamber; the fan-shaped cavities (6-1) and the fan-shaped blank areas (9-3) are located in the same axial direction; the control shaft (11) is used to drive the first flow resistance control panel (7) and the second flow resistance control panel (8) to move axially and rotate axially, so that the first flow resistance control panel (7) and the fan-shaped cavity (6-1) are aligned or staggered, the first flow resistance control panel (7) and the inclined surface of the end of the inner ring body (6) are fitted or separated, the second flow resistance control panel (8) and the fan-shaped blank area (9-3) are aligned or staggered, and the second flow resistance control panel (8) and the inner side surface of the detonation combustion chamber are fitted or separated.

2. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: The detonation combustion chamber comprises an inner combustion chamber wall (9), an outer combustion chamber wall (4) sleeved on the inner combustion chamber wall (9), an annular combustion chamber (5) is formed between the inner combustion chamber wall (9) and the outer combustion chamber wall (4), and the side surface of the inner combustion chamber wall (9) close to the entrance of the annular combustion chamber (5) is an inner side surface.

3. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: A positioning ring (6-2) is provided at the center of the inclined surface at the end of the inner ring body (6), and a positioning groove (7-1) adapted to the positioning ring (6-2) is provided at the front end of the No. 1 flow resistance control panel (7). In a force-applied state, the positioning ring (6-2) is embedded in the positioning groove (7-1).

4. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: The second flow resistance control panel (8) is coaxially connected to the first flow resistance control panel (7) via a connecting ring (8-1), and the first flow resistance control panel (7) is coaxially connected to the control shaft (11).

5. The rotating detonation combustion chamber with variable flow resistance according to claim 4, characterized in that: A sector-shaped wall surface is provided on the inner side surface of the combustion chamber inner wall (9), and the connecting ring (8-1) is located between the inner side surface of the inclined surface at the end of the inner ring body (6) and the outer edge of the sector-shaped wall surface.

6. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: The No. 1 flow resistance control panel (7) and the No. 2 flow resistance control panel (8) are provided with four 45° sector-shaped panels at equal intervals.

7. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: The nozzle is composed of a nozzle outer wall (12) and a nozzle inner wall (13).

8. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: It also includes an oil injection disc (2), and the oil inlet ring (3) is connected to the annular combustion chamber (5) through the oil injection disc (2).

9. The rotating detonation combustion chamber with variable flow resistance according to claim 8, characterized in that: The oil inlet ring (3) and the oil spray plate (2) are connected by a flange.

10. The rotating detonation combustion chamber with variable flow resistance according to claim 1, characterized in that: The upstream section of the airflow channel (10) is a rectifying section with a rectangular longitudinal cross section, and the downstream section is a convergent section with a trapezoidal longitudinal cross section.

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