A gas-liquid two-phase rotating detonation combustion chamber for inhibiting pressure backflow

Abstract

A gas-liquid two-phase rotating detonation combustion chamber for inhibiting pressure back transmission relates to the technical field of combustion chamber pressure back transmission inhibition of air-breathing rotating detonation engine, and aims to solve the problem that the existing rotating detonation combustion cannot simultaneously consider pressure back transmission inhibition and ram loss. The utility model discloses the communication of air inlet pressure stabilizing section, pressure inhibition section and combustion section in proper order, one side of the Tesla valve flow channel in the pressure inhibition section is communicated with the gas oxidant channel of air inlet pressure stabilizing section, the other side is communicated with the combustion channel of combustion section, the clearance between the Tesla valve shell and the pressure inhibition section shell forms the main flow channel of the Tesla valve flow channel, the clearance between the Tesla valve shell and the combustion chamber inner column forms the pressure back transmission channel of the Tesla valve flow channel, and the liquid fuel cavity is located between the Tesla valve flow channel and the combustion channel. The utility model utilizes the 'fluid diode' characteristics of the Tesla valve to effectively inhibit the detonation pressure back transmission, reduces the total pressure loss of inlet air, and improves the performance of the rotating detonation combustion chamber.

Description

Technical Field

[0001] This utility model relates to the field of air-breathing rotary detonation engine technology, specifically to pressure backflow suppression technology for gas-liquid two-phase rotary detonation combustion chambers. Background Technology

[0002] With the rapid development of the field of propulsion, the performance requirements for thermal engines are increasing. In conventional propulsion systems, isobaric combustion is commonly used in the combustion chamber. Isobaric combustion is accompanied by a significant increase in entropy, which directly limits the cycle efficiency of modern Brayton cycle thermal engines, severely restricting their development due to limitations in new materials technology. Detonation combustion is a novel pressurized combustion method characterized by a high coupling between the leading shock wave and the chemical reaction zone. During combustion, pressure and temperature increase rapidly while volume remains essentially constant, approximating isochoric combustion. Its pressurization characteristics are significant, greatly reducing entropy increase during combustion and theoretically improving the cycle thermal efficiency of propulsion systems. The rotating detonation combustor, a pressurized combustor based on detonation combustion, offers advantages such as single ignition, compact structure, and stable power output, and has received widespread attention and research in recent years.

[0003] In actual operation of a rotating detonation combustor, high-frequency, high-intensity detonation wave pressure signals exist. Pressure backflow can severely affect the normal intake of the combustor and the stable operation of upstream components. Inlet pressure backflow suppression is an essential step in the application of two-phase rotating detonation engines. Traditional methods often use a shrinking-expanding inlet to generate a positive shock wave in the expansion section to suppress pressure backflow. However, this method results in a significant total pressure loss, which is detrimental to improving the total pressure gain of the combustor. Reducing the shock wave intensity in the expansion section can reduce the total pressure loss, but this leads to stronger detonation wave pressure backflow. Therefore, it is necessary to combine an effective pressure backflow suppression structure to improve the overall performance of the combustor. Utility Model Content

[0004] The purpose of this invention is to solve the problem that existing rotating detonation combustion cannot simultaneously suppress pressure backflow and ramming loss, resulting in a decline in the overall performance of the combustion chamber, and to provide a novel gas-liquid two-phase rotating detonation combustion chamber that suppresses pressure backflow.

[0005] This invention discloses a gas-liquid two-phase rotating detonation combustion chamber for suppressing pressure backflow, comprising an intake pressure stabilization section, a pressure suppression section, and a combustion section connected in sequence. The intake pressure stabilization section includes a gaseous oxidant inlet and a gaseous oxidant channel connected to the gaseous oxidant inlet. The combustion section includes a combustion channel. The pressure suppression section includes a liquid fuel inlet, a liquid fuel chamber, a liquid fuel orifice, and a Tesla valve flow channel. The liquid fuel inlet, the liquid fuel chamber, and the liquid fuel orifice are connected in sequence. One side of the Tesla valve flow channel is connected to the gaseous oxidant channel, and the other side is connected to the combustion channel. The gap between the Tesla valve housing and the outer shell of the pressure suppression section forms the main flow channel of the Tesla valve flow channel. The gap between the Tesla valve housing and the inner column of the combustion chamber forms the pressure backflow channel of the Tesla valve flow channel. The liquid fuel chamber is located between the Tesla valve flow channel and the combustion channel.

[0006] Optionally, the central axis of the pressure return channel coincides with the central axis of the combustion channel, and the angle between the central axis of the main channel and the central axis of the combustion channel is 30°-45°.

[0007] Optionally, the number of liquid fuel holes is 90 to 120, and they are arranged circumferentially around the combustion chamber inner column of the combustion chamber.

[0008] Optionally, the liquid fuel orifice is 0.3 to 0.5 mm.

[0009] Optionally, the outer casing of the combustion section has a pressure sensor mounting hole.

[0010] Optionally, the diameter of the pressure sensor mounting hole is 14 mm.

[0011] This invention adds a Tesla valve injection structure to a gas-liquid two-phase rotating detonation combustion chamber. This structure is divided into two parts: a main flow channel and a return flow channel. It has the characteristics of a "fluid diode" and can effectively suppress the backflow of detonation pressure, reduce the total intake pressure loss, and improve the performance of the rotating detonation combustion chamber. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the overall structure of a gas-liquid two-phase rotating detonation combustion chamber for suppressing pressure feedback according to an embodiment of this application.

[0013] Figure 2 This is a cross-sectional structural schematic diagram of a gas-liquid two-phase rotating detonation combustion chamber for suppressing pressure feedback according to an embodiment of this application.

[0014] Figure 3 This is a schematic diagram of the flow channel of a Tesla valve according to an embodiment of this application. Detailed Implementation

[0015] The following specific examples illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification. This utility model can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this utility model. It should be noted that, unless otherwise specified, the following embodiments and features described therein can be combined with each other.

[0016] As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context indicates otherwise. It should be further understood that the terms “comprising,” “including,” indicate the presence of the stated feature, operation, element, component, item, kind, and / or group, but do not preclude the presence, occurrence, or addition of one or more other features, operations, elements, components, items, kinds, and / or groups. The terms “or” and “and / or” as used herein are interpreted as inclusive, or mean any one or any combination thereof. Thus, “A, B, or C” or “A, B, and / or C” means “any one of: A; B; C; A and B; A and C; B and C; A, B, and C.” Exceptions to this definition occur only when combinations of elements, functions, or operations are inherently mutually exclusive in some manner.

[0017] To address the problem that existing rotating detonation combustion systems cannot simultaneously suppress pressure backflow and ram pressure loss, leading to a decline in the overall performance of the combustion chamber, this invention provides a gas-liquid two-phase rotating detonation combustion chamber that suppresses pressure backflow. This effectively suppresses detonation pressure backflow, reduces total intake pressure loss, and improves the performance of the rotating detonation combustion chamber.

[0018] like Figure 1 and Figure 2 As shown, the gas-liquid two-phase rotating detonation combustion chamber for suppressing pressure feedback in this embodiment of the application includes: an intake pressure stabilizing section 1, a pressure suppression section 2, and a combustion section 3.

[0019] The outer wall of the outlet of the intake pressure stabilizing section 1, the outer wall of the inlet and outlet of the pressure suppression section 2, and the outer wall of the inlet and outlet of the combustion section 3 are all welded with fixed flanges for connection between the three. The outlet of the combustion section 3 is welded with a fixed flange for connection to the exhaust gas recovery device.

[0020] The intake pressure regulating section 1 includes an oxidant inlet 11 and an oxidant passage 12. The combustion chamber column 4 is divided into a head, a middle, and a tail. The head is conical, with the tip of the cone facing outward from the combustion chamber. The tip of the cone is located at the center of the end face of the pressure regulating section housing 13. The end of the pressure regulating section housing 13 serves as the oxidant inlet 11 of the intake pressure regulating section 1. Inside the pressure regulating section housing 13, the gap between the pressure regulating section housing 13 and the head of the combustion chamber column 4 serves as the oxidant passage 12.

[0021] Combustion section 3 includes combustion channel 31, which is an annular channel formed by combustion section housing 32 and the middle of combustion chamber column 4. Combustion section housing 32 has a pressure sensor mounting hole 5, the diameter of which is preferably 14 mm.

[0022] Between the intake pressure stabilization section 1 and the combustion section 3 is the pressure suppression section 2. For example... Figure 2 and Figure 3 As shown, the pressure suppression section 2 includes a liquid fuel inlet 21, a liquid fuel chamber 22, a liquid fuel orifice 23, and a Tesla valve flow channel 24.

[0023] The liquid fuel inlet 21, liquid fuel chamber 22, and liquid fuel orifice 23 are all cavities / channels machined on the pressure suppression section outer shell 25. These three components are sequentially connected. The liquid fuel inlet 21 extends outward to the outer surface of the pressure suppression section outer shell 25, and the liquid fuel orifice 23 extends inward to the combustion channel 31. The liquid fuel chamber 22 is located between the Tesla valve flow channel 24 and the combustion channel 31. The Tesla valve flow channel 24 is located between the gaseous oxidant channel 12 and the combustion channel 31. The Tesla valve flow channel 24 is formed by the gap between the pressure suppression section outer shell 25, the combustion chamber column 4, and the Tesla valve housing 26. Specifically, the gap between the Tesla valve housing 26 and the pressure suppression section housing 25 forms the main flow channel 27 of the Tesla valve flow channel 24, and the gap between the Tesla valve housing 26 and the combustion chamber pillar 4 forms the pressure return channel 28 of the Tesla valve flow channel 24. The pressure return channel 28 is coaxial with the combustion channel 31, and the angle between the main flow channel 27 and the central axis of the combustion channel 31 is 30°-45°. Liquid fuel holes 23 connect the liquid fuel chamber 22 and the combustion channel 31. There are 90-120 liquid fuel holes 23 arranged circumferentially around the combustion chamber pillar 4, with a diameter of approximately 0.3-0.5 mm.

[0024] The working process and principle of the present invention are described below to facilitate understanding of its advantages. Gaseous fuel enters the intake pressure stabilizing section 1 through the gas oxidant inlet 11 and enters the Tesla valve mainstream channel 17 through the pressure suppression section 2, finally entering the combustion channel 31. Liquid fuel enters the combustion channel 31 through the liquid fuel hole 23 on the liquid fuel chamber 22 and is mixed and burned with the gaseous fuel. When detonation pressure returns, most of the returned pressure first enters the Tesla valve pressure return channel 28 through the combustion channel 31. During the propagation of the returned pressure within the pressure return channel (28), complex reflections and refractions occur. By the time it reaches the intersection with the main channel 27, the remaining returned pressure is very small. Then, through the flow guidance effect of the Tesla valve housing 25, it merges into the forward flow (entering the main channel 27). Finally, the remaining returned pressure is extremely small. This part of the returned pressure enters the gaseous oxidizer channel 12 of the intake pressure stabilization section 1. Due to the long return distance, the returned pressure is further dissipated, which can effectively suppress the disturbance of detonation pressure return to the gaseous oxidizer inlet 11. Part of the returned pressure can be further weakened in the intake pressure stabilization section 1, further enhancing the uniformity and stability of gaseous fuel injection and improving the operating performance of the rotating detonation combustion chamber.

[0025] In this invention, the combination of the intake pressure stabilizing section 1 and the pressure suppression section 2 can effectively weaken the detonation pressure return, reduce the total pressure loss at the inlet, improve the stability of the inlet flow field and the overall total pressure gain of the combustion chamber, and also improve the intake uniformity of the rotating detonation combustion chamber and reduce the intake recovery time.

[0026] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A gas-liquid two-phase rotating detonation combustion chamber for suppressing pressure backflow, characterized in that, It includes an intake pressure stabilization section (1), a pressure suppression section (2), and a combustion section (3) connected in sequence; The intake pressure stabilizing section (1) includes a gas oxidant inlet (11) and a gas oxidant channel (12) connected to the gas oxidant inlet (11); The combustion section (3) includes a combustion channel (31); The pressure suppression section includes a liquid fuel inlet (21), a liquid fuel chamber (22), a liquid fuel orifice (23), and a Tesla valve flow channel (24). The liquid fuel inlet (21), the liquid fuel chamber (22), and the liquid fuel orifice (23) are connected in sequence. One side of the Tesla valve flow channel (24) is connected to the gaseous oxidant channel (12), and the other side is connected to the combustion channel (31). The gap between the Tesla valve housing (26) and the pressure suppression section housing (25) forms the main flow channel (27) of the Tesla valve flow channel (24). The gap between the Tesla valve housing (26) and the combustion chamber column (4) forms the pressure return channel (28) of the Tesla valve flow channel (24). The liquid fuel chamber (22) is located between the Tesla valve flow channel (24) and the combustion channel (31).

2. The combustion chamber as described in claim 1, characterized in that, The central axis of the pressure return channel (28) coincides with the central axis of the combustion channel (31), and the angle between the central axis of the main channel (27) and the central axis of the combustion channel (31) is 30°-45°.

3. The combustion chamber as described in claim 1, characterized in that, The number of liquid fuel holes (23) is 90 to 120, and they are arranged circumferentially around the combustion chamber inner column (4) of the combustion chamber.

4. The combustion chamber as described in claim 3, characterized in that, The liquid fuel hole (23) has a diameter of 0.3 to 0.5 mm.

5. The combustion chamber as described in claim 1, characterized in that, The outer casing of the combustion section (3) has a pressure sensor mounting hole (5).

6. The combustion chamber as described in claim 5, characterized in that, The diameter of the pressure sensor mounting hole (5) is 14 mm.

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