Method and device for real-time active oxygen supplement control of scramjet engine combustion

Abstract

The application provides a real-time active oxygen supplementing regulation method and device for combustion of a scramjet engine, comprising the following steps: acquiring wall surface pressure data and flame self-luminous radiation data in a combustion chamber in real time; determining a current flame combustion state based on a flame combustion state discrimination criterion and the current acquired wall surface pressure data and flame self-luminous radiation data in the combustion chamber; and generating a corresponding control signal for the combustion chamber according to the current flame combustion state to realize active oxygen supplementing and combustion active regulation of the oxygen injection valve of the combustion chamber. The application can strengthen the combustion effect, improve the combustion efficiency, and improve the precision and stability of combustion control.

Description

Technical Field

[0001] This invention relates to the field of scramjet engine technology, and in particular to a method and device for real-time active oxygen supplementation control of scramjet engine combustion. Background Technology

[0002] Scramjet engines are among the fastest-developing power plants for hypersonic vehicles, characterized by high efficiency, high thrust, and high energy density. However, in hypersonic conditions, the high incoming flow velocity and short fuel residence time make ignition and stable combustion difficult for scramjet engines under extreme conditions, leading to a high risk of flameout. This can negatively impact engine performance and lifespan.

[0003] Currently, the most commonly used methods for enhancing ignition and stabilizing combustion include:

[0004] (1) Hydrogen-guided ignition

[0005] Hydrogen-guided ignition utilizes the high calorific value and flammability of hydrogen to form a high-temperature, high-pressure flame core in the combustion chamber, thereby achieving supersonic enhanced combustion. This can improve engine combustion efficiency and power output while reducing emissions. However, enhanced hydrogen ignition cannot solve the problem of ignition in lean air and near-blowout limits.

[0006] Hydrogen-guided ignition and other methods are passive controls that cannot be adjusted in real time according to the combustion state. Furthermore, their scope of application is limited. They enhance ignition from the perspective of input energy and fail to monitor and adjust the combustion state in real time, which can lead to energy waste and ineffectiveness.

[0007] (2) Spark plug ignition

[0008] When using spark plugs for enhanced ignition, the frequency of discharge is limited, and under extreme conditions such as near-lean combustion, it is difficult to achieve stable combustion in a scramjet engine.

[0009] For the scheme that uses spark plugs to enhance ignition and combustion, the spark plugs are severely eroded, and the discharge frequency is low due to the DC pulse discharge. The expansion of the kerosene flame stabilization boundary is limited. When the kerosene flow rate is constant, it is difficult to achieve enhanced ignition and stable combustion under near-lean combustion limit conditions, and the active control of the combustion state is not achieved.

[0010] (3) Achieving stable combustion by means of a concave flame stabilizer

[0011] When using a concave flame stabilizer to achieve stable combustion, factors such as incoming flow conditions, fuel type, injection method, and equivalence ratio can affect the ignition and flame stability of a specific concave configuration. As a passive combustion stabilization device, the concave flame stabilizer can cause ignition failure and flame extinction when these limits are exceeded. It cannot actively control the engine's combustion state and cannot provide real-time feedback and adjustment for the combustion status. Summary of the Invention

[0012] To address the technical problems existing in the prior art, this invention proposes a method and device for real-time active oxygen supplementation control of scramjet engine combustion.

[0013] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0014] A method for real-time active oxygen supplementation control of combustion in a scramjet engine, comprising:

[0015] Real-time acquisition of combustion chamber wall pressure data and flame self-luminous radiation data;

[0016] Based on the flame combustion state discrimination criteria and the currently acquired combustion chamber wall pressure data and flame self-luminous radiation data, the current flame combustion state is determined;

[0017] Based on the current flame combustion state, corresponding control signals are generated to the oxygen injection valve in the combustion chamber to achieve active oxygen replenishment and active combustion regulation.

[0018] Furthermore, the combustion chamber of the present invention is a concave combustion chamber, with a concave cavity provided on the lower wall of the combustion chamber, and the igniter is disposed on the bottom wall of the concave cavity. 。

[0019] Furthermore, in this invention: along the direction of the supersonic flow, multiple sets of pressure measuring points are set at different combustion chamber length positions on the lower wall of the combustion chamber to measure pressure data at different positions on the inner wall of the combustion chamber in real time; multiple sets of photoelectric probes are set at different combustion chamber length positions on the upper wall of the combustion chamber to measure flame self-luminous radiation data at different positions on the inner wall of the combustion chamber in real time.

[0020] Furthermore, in this invention: multiple sets of pressure measuring points are set on the lower wall of the combustion chamber upstream of the cavity, multiple sets of pressure measuring points are set on the bottom wall of the cavity, wherein at least one set of pressure measuring points is set on the bottom wall of the cavity upstream of the igniter, at least one set of pressure measuring points is set on the bottom wall of the cavity downstream of the igniter, and at least one set of pressure measuring points is set on the lower wall of the combustion chamber downstream of the cavity.

[0021] Furthermore, in this invention, a set of photoelectric probes is correspondingly arranged on the upper wall of the combustion chamber above each set of pressure measuring points, and the positions of the pressure measuring points and photoelectric probes are vertically corresponding.

[0022] Furthermore, in this invention, at least one set of oxygen injection holes is provided on the concave wall surface upstream of the igniter, and at least one set of oxygen injection holes is provided on the concave wall surface downstream of the igniter. An oxygen source supplies oxygen to each set of oxygen injection holes through an oxygen supply pipeline. Each set of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. An independent oxygen injection valve is provided on the oxygen supply branch corresponding to each set of oxygen injection holes, and independent control of each set of oxygen injection holes is achieved through the oxygen injection valve.

[0023] Furthermore, the cavity wall surface in this invention includes a cavity front wall, a cavity bottom wall, and a cavity rear wall. The cavity front wall is perpendicular to the combustion chamber lower wall surface upstream of the cavity, forming a vertical step with the cavity bottom wall. The cavity rear wall is inclined relative to the cavity bottom wall, forming an inclined transition between the cavity and the combustion chamber lower wall surface downstream of the cavity.

[0024] Furthermore, in this invention, at least one set of oxygen injection holes is provided on the front wall of the concave cavity, at least one set of oxygen injection holes is provided on the bottom wall of the concave cavity upstream of the igniter, and at least one set of oxygen injection holes is provided on the rear wall of the concave cavity.

[0025] Furthermore, the present invention determines the current flame combustion state through the following steps:

[0026] The wall pressure range and flame self-luminous radiation intensity range at different locations in the combustion chamber under different flame combustion states are set. The flame combustion states include normal flame combustion state, local weak flame combustion state, global flame extinguishing or near extinguishing state, and flame enhanced combustion state.

[0027] Based on the obtained wall pressure data at different locations within the combustion chamber and the flame self-luminous radiation intensity data, the current flame combustion state is determined.

[0028] Furthermore, in this invention, based on the current flame combustion state, a corresponding control signal is generated to the oxygen injection valve corresponding to the combustion chamber to achieve active oxygen replenishment and active combustion regulation, including:

[0029] Based on the real-time feedback of pressure data and photoelectric signal data at each measuring point, the opening / closing status of the oxygen injection valves of each group of oxygen injection holes is adjusted in real time. Specifically, the oxygen injection valves of each group of oxygen injection holes at measuring points with relatively lower pressure data and photoelectric signal data are opened, while the oxygen injection valves of each group of oxygen injection holes at measuring points with relatively higher pressure data and photoelectric signal data are closed. This adaptive adjustment continues until all measuring points are monitored to be in a stable and normal combustion state.

[0030] Furthermore, in this invention, based on the current flame combustion state, a corresponding control signal is generated to the oxygen injection valve corresponding to the combustion chamber to achieve active oxygen replenishment and active combustion regulation, including:

[0031] If the wall pressure data measured by the pressure measuring point at a certain location is within the wall pressure range of the corresponding local weak combustion state of the flame, or the flame self-luminous radiation intensity data measured by the photoelectric probe at that location is within the flame self-luminous radiation intensity range of the corresponding local weak combustion state of the flame, then the oxygen injection valve corresponding to the set of oxygen injection holes closest to that location is opened to inject oxygen until the wall pressure data measured by the pressure measuring point at that location is within the wall pressure range of the corresponding normal combustion state of the flame, then the oxygen injection valve corresponding to the set of oxygen injection holes closest to that location is closed.

[0032] If the wall pressure data measured by all pressure measuring points is within the wall pressure range of the corresponding flame global extinguishing or near-extinguishing state, or if the flame self-luminous radiation intensity data measured by all photoelectric probes is within the flame self-luminous radiation intensity range of the corresponding flame global extinguishing or near-extinguishing state, then open the oxygen injection valves corresponding to all groups of oxygen injection holes to inject oxygen until the wall pressure data measured by all pressure measuring points is within the wall pressure range of the corresponding flame normal combustion state, then close the oxygen injection valves corresponding to each group of oxygen injection holes.

[0033] If it is necessary to improve the combustion performance of the combustion chamber, open the igniter and the oxygen injection valves corresponding to all oxygen injection holes, so that the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure range of the corresponding flame-enhanced combustion state, thereby achieving enhanced combustion.

[0034] On the other hand, the present invention provides a real-time active oxygen supplementation control device for scramjet engine combustion, comprising:

[0035] The combustion chamber is a concave combustion chamber, with a concave cavity formed on the lower wall of the combustion chamber, and the igniter is disposed on the bottom wall of the concave cavity. ；Following the direction of the supersonic flow, multiple pressure measuring points are set at different combustion chamber length positions on the lower wall of the combustion chamber to measure pressure data at different positions on the inner wall of the combustion chamber in real time; multiple photoelectric probes are set at different combustion chamber length positions on the upper wall of the combustion chamber to measure flame self-luminous radiation data at different positions on the inner wall of the combustion chamber in real time; at least one set of oxygen injection holes is set on the concave wall upstream of the igniter, and at least one set of oxygen injection holes is set on the concave wall downstream of the igniter. The oxygen source supplies oxygen to each set of oxygen injection holes through the oxygen supply pipeline. Each set of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. An independent oxygen injection valve is set on the oxygen supply branch corresponding to each set of oxygen injection holes, and the oxygen injection valve realizes independent control of each set of oxygen injection holes.

[0036] The signal control system determines the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired combustion chamber wall pressure data, and the flame self-luminous radiation data. Based on the current flame combustion state, it generates corresponding control signals to the oxygen injection valves in the combustion chamber to achieve active oxygen replenishment and active combustion regulation.

[0037] This invention enables scramjet engines to avoid flameout during high-speed flight, while simultaneously monitoring the combustion status in real time and actively supplementing oxygen to regulate the combustion state, offering the following advantages:

[0038] (1) Real-time combustion status monitoring. The combustion status is monitored by pressure sensors and photoelectric probes and fed back to the signal control system in real time. The monitoring and control position is adjustable and the number of monitoring and control is variable. It has high programmability and reconfigurability. Therefore, the combustion monitoring system and feedback control algorithm can be optimized according to actual needs, thereby improving the accuracy and stability of combustion control.

[0039] (2) Real-time active control. It responds quickly to changes in signals transmitted by sensors during combustion, adjusts the oxygen supply valve in a timely and rapid manner to supply oxygen, and can monitor the combustion status in real time, and close the oxygen supply valve in a timely manner when the flame is stable.

[0040] (3) Enhanced active combustion. By supplementing oxygen to increase the local equivalence ratio, enhanced combustion is achieved, which compensates for the insufficient air mass exchange rate in the cavity, improves the local equivalence ratio of ignition, enhances the combustion effect, and improves combustion efficiency. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0042] Figure 1 Here is a flowchart of one embodiment;

[0043] Figure 2 This is a schematic diagram of the combustion chamber structure in one embodiment;

[0044] Figure 3 This is a schematic diagram of the structure of one embodiment;

[0045] Figure 4 This is a schematic diagram showing the distribution of pressure measuring points and photoelectric probes in one embodiment;

[0046] Figure 5 This is a control flowchart of one embodiment.

[0047] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Detailed Implementation

[0048] The embodiments described in this section are merely some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0049] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0050] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0051] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0052] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0053] Reference Figure 1 One embodiment provides a method for real-time active oxygen supplementation control of a scramjet engine, comprising:

[0054] Real-time acquisition of combustion chamber wall pressure data and flame self-luminous radiation data;

[0055] Based on the flame combustion state discrimination criteria and the currently acquired combustion chamber wall pressure data and flame self-luminous radiation data, the current flame combustion state is determined;

[0056] Based on the current flame combustion state, corresponding control signals are generated to the oxygen injection valve in the combustion chamber to achieve active oxygen replenishment and active combustion regulation.

[0057] In the above embodiments, by acquiring the pressure data of the combustion chamber wall and the flame self-luminous radiation data, and based on the established combustion state discrimination criteria, the current flame combustion state is determined, thereby realizing real-time dynamic monitoring of the engine combustion state. Based on the current flame combustion state, a corresponding control signal is generated to the oxygen injection valve corresponding to the combustion chamber to realize active oxygen replenishment and active combustion control. That is, the oxygen replenishment valve is dynamically opened according to the combustion state and demand, and based on the real-time combustion state signal feedback, real-time active oxygen replenishment and real-time active control of the combustion state are realized.

[0058] The above solution solves the problem of unstable combustion in scramjet engines under extreme operating conditions, while also achieving enhanced combustion and improved engine combustion efficiency under weak combustion conditions.

[0059] To obtain real-time data on combustion chamber wall pressure and flame self-luminous radiation, refer to Figure 2In one embodiment, a combustion chamber is provided, which is a concave combustion chamber. A concave cavity 20 is provided on the lower wall of the combustion chamber, an igniter 5 is provided on the bottom wall of the concave cavity 20, and a plurality of fuel injection holes 1 are provided on the lower wall of the combustion chamber upstream of the concave cavity 20. Figure 2 In the combustion chamber, four fuel injection holes 1 are arranged on the same straight line in the width direction of the combustion chamber and the four fuel injection holes 1 are equally spaced.

[0060] Multiple pressure measuring points are set at different combustion chamber length positions on the lower wall of the upstream cavity 20, following the direction of the supersonic flow, to measure pressure data at different positions on the inner wall of the combustion chamber in real time. Multiple photoelectric probes are set at different combustion chamber length positions on the upper wall of the combustion chamber to measure flame self-luminous radiation data at different positions on the inner wall of the combustion chamber in real time. It is understood that the number of pressure measuring points and photoelectric probes is not limited, and those skilled in the art can make reasonable adjustments according to the length, structure, and measurement accuracy requirements of the combustion chamber; this invention does not impose any limitations. A corresponding set of photoelectric probes is set on the upper wall of the combustion chamber above each set of pressure measuring points, with the pressure measuring points and photoelectric probes positioned vertically. In this way, the pressure measuring points and their corresponding photoelectric probes detect the wall pressure data and flame self-luminous radiation data at the same length position within the combustion chamber.

[0061] Without loss of generality, multiple sets of pressure measuring points are set on the lower wall of the combustion chamber upstream of the cavity, and multiple sets of pressure measuring points are set on the bottom wall of the cavity. Among them, at least one set of pressure measuring points is set on the bottom wall of the cavity upstream of the igniter, at least one set of pressure measuring points is set on the bottom wall of the cavity downstream of the igniter, and at least one set of pressure measuring points is set on the lower wall of the combustion chamber downstream of the cavity.

[0062] like Figure 2 As shown, seven sets of pressure measuring points are provided. The first set of pressure measuring points, 6, is located on the lower wall of the combustion chamber upstream of the fuel injection hole 1. The second set of pressure measuring points, 7 and the third set, 8, are located on the lower wall of the combustion chamber downstream of the fuel injection hole 1 and upstream of the concave cavity. The fourth set of pressure measuring points, 9, is located on the bottom wall of the concave cavity upstream of the igniter 5. The fifth set of pressure measuring points, 10 and the sixth set, 11, are located on the bottom wall of the concave cavity downstream of the igniter 5. The seventh set of pressure measuring points, 12, is located on the lower wall of the combustion chamber downstream of the concave cavity. Each set of pressure measuring points has two pressure sensors, and the two pressure sensors in the same set are positioned on the same straight line along the width direction of the combustion chamber. Correspondingly, seven sets of photoelectric probes are provided, each set of photoelectric probes has two photoelectric sensors, and the two photoelectric sensors in the same set correspond to the two pressure sensors in the same set of pressure measuring points directly below them. Figure 2The seven sets of photoelectric probes are designated as photoelectric probe 13, photoelectric probe 14, photoelectric probe 15, photoelectric probe 16, photoelectric probe 17, photoelectric probe 18, and photoelectric probe 19. Fuel injection port 1 is connected to the kerosene storage tank via a pipeline. The pipeline is equipped with fuel valves F1-i, where the number of 'i's is unlimited and determined according to requirements, representing a single fuel injection port within a set of fuel injection ports.

[0063] In this invention, at least one set of oxygen injection holes is provided on the concave wall surface upstream of the igniter 5, and at least one set of oxygen injection holes is provided on the concave wall surface downstream of the igniter. An oxygen source supplies oxygen to each set of oxygen injection holes through an oxygen supply pipeline. Each set of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. An independent oxygen injection valve is provided on the oxygen supply branch corresponding to each set of oxygen injection holes, and independent control of each set of oxygen injection holes is achieved through the oxygen injection valve.

[0064] The cavity wall in this invention includes a front wall, a bottom wall, and a rear wall. The front wall is perpendicular to the lower wall of the combustion chamber upstream of the cavity, forming a vertical step with the bottom wall. The rear wall is inclined relative to the bottom wall, forming an inclined transition between the cavity and the lower wall of the combustion chamber downstream of the cavity. At least one set of oxygen injection holes is provided on the front wall, the bottom wall upstream of the igniter, and the rear wall.

[0065] like Figure 2 As shown, a first set of oxygen injection holes 2 is provided on the front wall of the concave cavity, a second set of oxygen injection holes 3 is provided on the bottom wall of the concave cavity upstream of the igniter 5, and a third set of oxygen injection holes 4 is provided on the rear wall of the concave cavity. Each set of oxygen injection holes has 4 holes, and the 4 oxygen injection holes in the same set are arranged on the same straight line in the width direction of the combustion chamber and are equidistant. Oxygen source (e.g. Figure 3 The oxygen storage tank in the middle supplies oxygen to each group of oxygen injection holes through oxygen supply pipelines. Each group of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. Each group of oxygen injection holes is equipped with an independent oxygen injection valve on its corresponding oxygen supply branch, and the oxygen injection valve enables independent control of each group of oxygen injection holes.

[0066] Furthermore, the present invention determines the current flame combustion state through the following steps:

[0067] The wall pressure range and flame self-luminous radiation intensity range at different locations in the combustion chamber under different flame combustion states are set. The flame combustion states include normal flame combustion state, local weak flame combustion state, global flame extinguishing or near extinguishing state, and flame enhanced combustion state.

[0068] Based on the obtained wall pressure data at different locations within the combustion chamber and the flame self-luminous radiation intensity data, the current flame combustion state is determined.

[0069] When a scramjet engine undergoes flight condition transitions or extreme operating conditions, the flame state within the combustion chamber changes, leading to variations in combustion heat release and consequently, changes in wall pressure. Real-time dynamic monitoring of wall pressure changes at different locations within the combustion chamber is achieved using pressure sensors at seven pressure measurement points to determine the flame combustion state. Furthermore, photoelectric sensors mounted on the top of the combustion chamber record the flame's self-luminous radiation and position. When the flame is nearing extinction, the self-luminous intensity is weak, allowing for real-time dynamic monitoring of the flame's state.

[0070] One embodiment proposes an active oxygen supply and active combustion control scheme as follows: If the engine experiences rapid flameout, it leads to incomplete combustion, reduced wall pressure, and weakened flame self-luminous radiation intensity. A signal control system performs threshold judgment on the collected pressure data and extracts a pressure feature matrix. Convolution kernels are calculated on the collected flame self-luminous image data to extract an image feature matrix. The pressure feature matrix and the image feature matrix are processed to obtain a multi-source feature matrix. By comparing this matrix with a combustion state category database, the combustion state is determined, and control is output to the oxygen valve to inject oxygen into the engine combustion chamber, increasing the oxygen concentration. This effectively controls rapid flameout by providing oxygen to enhance combustion and ensure normal engine operation. When the combustion state changes, the data signal is compared and judged against a set threshold, and a control signal is output to the oxygen pipeline valve to achieve active oxygen supply and active combustion control.

[0071] Reference Figure 5 In one embodiment, a method for real-time active oxygen supplementation control of scramjet engine combustion is proposed, comprising:

[0072] First, establish combustion state discrimination criteria, such as setting the wall pressure range and flame self-luminous radiation intensity range at different locations in the combustion chamber under different flame combustion states. The flame combustion states include normal flame combustion state, local weak flame combustion state, global flame extinguishing or near-extinguishing state, and enhanced flame combustion state.

[0073] Based on the obtained wall pressure data and flame self-luminous radiation intensity data at different locations within the combustion chamber, the current combustion status of each area is determined.

[0074] When the combustion state is abnormal, if there is no combustion in a certain area, oxygen is supplemented in a specific area by opening the oxygen supply valve closest to that area and turning on the igniter to achieve directional combustion enhancement.

[0075] If there is no combustion globally, then global oxygen supply will be performed by opening all oxygen supply valves and turning on the igniter to achieve enhanced global combustion.

[0076] When the combustion state is normal, if further improvement of engine performance and combustion efficiency is required, global oxygen supplementation is performed, all oxygen supplementation valves are opened and the igniter is turned on to achieve global combustion enhancement; otherwise, the igniter and valves are closed, and the pressure and photoelectric signals in the combustion chamber are monitored in real time. The combustion state is adjusted in real time based on the feedback of the pressure and photoelectric signals.

[0077] In another embodiment, it is proposed to generate a corresponding control signal to the oxygen injection valve in the combustion chamber based on the current flame combustion state to achieve active oxygen replenishment and active combustion regulation, including:

[0078] Based on the real-time feedback of pressure data and photoelectric signal data at each measuring point, the opening / closing status of the oxygen injection valves of each group of oxygen injection holes is adjusted in real time. For example, the oxygen injection valves of each group of oxygen injection holes at measuring points with relatively lower pressure data and photoelectric signal data are opened, while the oxygen injection valves of each group of oxygen injection holes at measuring points with relatively higher pressure data and photoelectric signal data are closed. This adaptive adjustment continues until all measuring points are monitored to be in a stable and normal combustion state.

[0079] If the wall pressure data measured by the pressure measuring point at a certain location is within the wall pressure range of the corresponding local weak combustion state of the flame, or the flame self-luminous radiation intensity data measured by the photoelectric probe at that location is within the flame self-luminous radiation intensity range of the corresponding local weak combustion state of the flame, then the oxygen injection valve corresponding to the set of oxygen injection holes closest to that location is opened to inject oxygen until the wall pressure data measured by the pressure measuring point at that location is within the wall pressure range of the corresponding normal combustion state of the flame, then the oxygen injection valve corresponding to the set of oxygen injection holes closest to that location is closed.

[0080] If the wall pressure data measured by all pressure measuring points is within the wall pressure range of the corresponding flame global extinguishing or near-extinguishing state, or if the flame self-luminous radiation intensity data measured by the corresponding photoelectric probes is within the flame self-luminous radiation intensity range of the corresponding flame global extinguishing or near-extinguishing state, then at the same time as turning on the igniter, at least the oxygen injection valves corresponding to each group of oxygen injection holes adjacent to the igniter will be opened to inject oxygen, until the wall pressure data measured by all pressure measuring points is within the wall pressure range of the corresponding flame normal combustion state, then the igniter and the oxygen injection valves corresponding to each group of oxygen injection holes will be closed.

[0081] If it is necessary to improve the combustion performance of the combustion chamber, open the igniter and the oxygen injection valves corresponding to all oxygen injection holes, so that the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure range of the corresponding flame-enhanced combustion state, thereby achieving enhanced combustion.

[0082] Reference Figure 2 , Figure 3 and Figure 4 A real-time active oxygen supplementation control device for scramjet engine combustion is provided, comprising:

[0083] The combustion chamber is a concave combustion chamber, with a concave cavity formed on the lower wall of the combustion chamber, and the igniter is disposed on the bottom wall of the concave cavity. ； Following the direction of the supersonic flow, multiple pressure measuring points are set at different combustion chamber length positions on the lower wall of the combustion chamber to measure pressure data at different positions on the inner wall of the combustion chamber in real time; multiple photoelectric probes are set at different combustion chamber length positions on the upper wall of the combustion chamber to measure flame self-luminous radiation data at different positions on the inner wall of the combustion chamber in real time; at least one set of oxygen injection holes is set on the concave wall upstream of the igniter, and at least one set of oxygen injection holes is set on the concave wall downstream of the igniter. An oxygen source (such as an oxygen storage tank) supplies oxygen to each set of oxygen injection holes through an oxygen supply pipeline. Each set of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. An independent oxygen injection valve is set on the oxygen supply branch corresponding to each set of oxygen injection holes, and independent control of each set of oxygen injection holes is achieved through the oxygen injection valve.

[0084] The signal control system determines the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired combustion chamber wall pressure data, and the flame self-luminous radiation data. Based on the current flame combustion state, it generates corresponding control signals to the oxygen injection valves in the combustion chamber to achieve active oxygen replenishment and active combustion regulation.

[0085] like Figure 2 As shown, seven sets of pressure measuring points are provided. The first set of pressure measuring points, 6, is located on the lower wall of the combustion chamber upstream of the fuel injection hole 1. The second set of pressure measuring points, 7 and the third set, 8, are located on the lower wall of the combustion chamber downstream of the fuel injection hole 1 and upstream of the concave cavity. The fourth set of pressure measuring points, 9, is located on the bottom wall of the concave cavity upstream of the igniter 5. The fifth set of pressure measuring points, 10 and the sixth set, 11, are located on the bottom wall of the concave cavity downstream of the igniter 5. The seventh set of pressure measuring points, 12, is located on the lower wall of the combustion chamber downstream of the concave cavity. Each set of pressure measuring points has two pressure sensors, and the two pressure sensors in the same set are positioned on the same straight line along the width direction of the combustion chamber. Correspondingly, seven sets of photoelectric probes are provided, each set of photoelectric probes has two photoelectric sensors, and the two photoelectric sensors in the same set correspond to the two pressure sensors in the same set of pressure measuring points directly below them. Figure 2The seven groups of photoelectric probes are the first group photoelectric probe 13, the second group photoelectric probe 14, the third group photoelectric probe 15, the fourth group photoelectric probe 16, the fifth group photoelectric probe 17, the sixth group photoelectric probe 18, and the seventh group photoelectric probe 19.

[0086] Fuel injection port 1 is connected to the kerosene storage tank via a pipeline. The pipeline is equipped with fuel valves F1-i, where the number of i is unlimited and can be set according to requirements. Each i represents a single fuel injection port in a group of fuel injection ports.

[0087] The pressure sensors in pressure measuring points 6, 7, 8, 9, 10, and 11 of the first, second, third, fourth, and fifth groups are defined as P1-j, P2-j, P3-j, P4-j, P5-j, P6-j, and P7-j, respectively, where j = 1 and 2, representing a single pressure sensor in each group of pressure measuring points. The photoelectric sensors in photoelectric probes 13, 14, 15, 16, 17, 18, and 19 of the first, second, third, and fourth groups are defined as G1-j, G2-j, G3-j, G4-j, G5-j, G6-j, and Gj, respectively, where j = 1 and 2, representing a single photoelectric sensor in each group of photoelectric probes.

[0088] like Figure 2 As shown, a first set of oxygen injection holes 2 is provided on the front wall of the concave cavity, a second set of oxygen injection holes 3 is provided on the bottom wall of the concave cavity upstream of the igniter 5, and a third set of oxygen injection holes 4 is provided on the rear wall of the concave cavity. Each set of oxygen injection holes has 4 holes, and the 4 oxygen injection holes in the same set are arranged on the same straight line in the width direction of the combustion chamber and are equidistant. Oxygen source (e.g. Figure 3 The oxygen storage tank supplies oxygen to each group of oxygen injection holes via oxygen supply pipelines. Each group of oxygen injection holes corresponds to an independent oxygen supply branch connected to an oxygen source. Each oxygen supply branch corresponding to a group of oxygen injection holes is equipped with an independent oxygen injection valve, which enables independent control of each group of oxygen injection holes. The first group of oxygen injection holes 2 corresponds to the first oxygen supply branch 01, and the first oxygen supply branch 01 is equipped with the first oxygen injection valve 01-i. The second group of oxygen injection holes 3 corresponds to the second oxygen supply branch 02, and the first oxygen supply branch 02 is equipped with the second oxygen injection valve 02-i. The third group of oxygen injection holes 4 corresponds to the third oxygen supply branch 03, and the third oxygen supply branch 03 is equipped with the third oxygen injection valve 03-i. i = 1, 2, 3, 4, representing a single oxygen injection hole in each group of oxygen injection holes.

[0089] The real-time active oxygen supplementation control device for scramjet engine combustion provided in the above embodiments controls combustion based on real-time active oxygen supplementation using pressure and photoelectric signal feedback. This enables dynamic monitoring of the combustion of the scramjet engine and timely oxygen supplementation, thereby achieving active control of the combustion state.

[0090] In one embodiment, the signal control system operates as follows:

[0091] (1) Localized weak combustion of flame (pressure reduced by 50% or photoelectric signal intensity reduced by 50%)

[0092] By monitoring the pressure data and photoelectric signal intensity data at the set measuring points, when the pressure data or photoelectric signal intensity data measured at a local measuring point decreases by more than 50%, the oxygen injection valve of the corresponding oxygen injection orifice is adaptively selected and opened to achieve directional control. When the pressure data or photoelectric signal intensity data measured at the local measuring point returns to normal combustion status, the corresponding oxygen injection valve is closed to complete combustion control. Preferably, directional control is achieved by selectively opening the oxygen injection valves of at least one set of oxygen injection orifices near the igniter; or, directional control is achieved by selectively opening the oxygen injection valves of at least one set of oxygen injection orifices near the local measuring point where the measured pressure data or photoelectric signal intensity data has decreased. Alternatively, first open the oxygen injection valves of at least one set of oxygen injection holes near the igniter. Then, based on the pressure data and photoelectric signal data from each measuring point, adjust the opening / closing status of the oxygen injection valves of each set of oxygen injection holes in real time. Specifically, open the oxygen injection valves of each set of oxygen injection holes near measuring points with relatively low pressure and photoelectric signal data, and close the oxygen injection valves of each set of oxygen injection holes near measuring points with relatively high pressure and photoelectric signal data. This adaptive adjustment continues until all measuring points are detected to be in a stable and normal combustion state. Alternatively, first open the oxygen injection valves of at least one group of oxygen injection holes at local measuring points where the measured pressure data or photoelectric signal intensity data has decreased. Then, based on the real-time feedback of pressure data and photoelectric signal data at each measuring point, adjust the opening / closing status of the oxygen injection valves of each group of oxygen injection holes in real time. Specifically, open the oxygen injection valves of each group of oxygen injection holes at measuring points where the pressure data and photoelectric signal intensity data are relatively low, and close the oxygen injection valves of each group of oxygen injection holes at measuring points where the pressure data and photoelectric signal intensity data are relatively high. This adaptive adjustment continues until all measuring points are monitored to be in a stable and normal combustion state.

[0093] (2) The flame is about to extinguish (pressure decreases by 90%, photoelectric signal intensity decreases by 90%)

[0094] By monitoring pressure and photoelectric signal data at designated measuring points, when the combustion state is detected as near flameout (i.e., a decrease of more than 90% in pressure or photoelectric signal intensity at each measuring point), the oxygen injection valve is selectively opened via the signal control system. When the combustion state is detected as stable and normal, the signal control system automatically closes the oxygen injection valve, thereby achieving real-time active oxygen supplementation regulation of the scramjet engine combustion and improving its stable performance under flight and extreme conditions. Preferably, the oxygen injection valves of at least one group of oxygen injection holes near the igniter are selected to be opened; or, all groups of oxygen injection holes are selected to be opened; or, the oxygen injection valves of each group of oxygen injection holes are opened sequentially according to their distance from the igniter, either from near to far or from far to near; or, all groups of oxygen injection holes are opened first, and then the opening / closing status of each group of oxygen injection holes is adjusted in real time according to the pressure data and photoelectric signal data of each measuring point location fed back in real time. Specifically, the oxygen injection valves of each group of oxygen injection holes near the measuring point location with relatively small pressure data and photoelectric signal data are opened, and the oxygen injection valves of each group of oxygen injection holes near the measuring point location with relatively large pressure data and photoelectric signal data are closed. This adaptive adjustment is continued until all measuring point locations are monitored to be in a stable and normal combustion state.

[0095] (3) Actively enhance combustion

[0096] When improved engine combustion performance is required, all oxygen injection valves and the igniter are opened to enhance combustion, and dynamic adjustments are made based on signals from pressure and photoelectric sensors. Specifically, based on real-time feedback of pressure and photoelectric signal data at each measuring point, the opening / closing status of the oxygen injection valves at each group of oxygen injection orifices is adjusted in real time. Specifically, the oxygen injection valves at measuring points with relatively lower pressure and photoelectric signal data are opened, while the valves at measuring points with relatively higher pressure and photoelectric signal data are closed. This dynamic adjustment achieves enhanced combustion throughout the combustion chamber.

[0097] Real-time monitoring of the combustion state in the combustion chamber is achieved through real-time monitoring and dynamic feedback of pressure and photoelectric signals from the scramjet engine combustion chamber; active combustion enhancement and control of the combustion state are achieved through oxygen supplementation in the combustion chamber cavity.

[0098] Matters not covered in this invention are common knowledge.

[0099] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0100] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A method for real-time active oxygen supplementation control in a scramjet engine, characterized in that, include: Real-time acquisition of combustion chamber wall pressure data and flame self-luminous radiation data; Based on the flame combustion state discrimination criteria and the currently acquired wall pressure data and flame self-luminous radiation data inside the combustion chamber, the current flame combustion state is determined. This includes setting wall pressure ranges and flame self-luminous radiation intensity ranges at different locations inside the combustion chamber under different flame combustion states. The flame combustion states include normal flame combustion state, locally weak flame combustion state, globally extinguished or near-extinguished flame state, and enhanced flame combustion state. The current flame combustion state is determined based on the currently acquired wall pressure data and flame self-luminous radiation intensity data at different locations inside the combustion chamber. Based on the current flame combustion state, corresponding control signals are generated to the oxygen injection valve in the combustion chamber to achieve active oxygen replenishment and active combustion regulation.

2. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 1, characterized in that, The combustion chamber is a concave combustion chamber, with a concave cavity provided on the lower wall of the combustion chamber, and the igniter is located on the bottom wall of the concave cavity.

3. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 2, characterized in that, Following the direction of the supersonic flow, multiple pressure measuring points are set at different combustion chamber length positions on the lower wall of the combustion chamber to measure pressure data at different positions on the inner wall of the combustion chamber in real time; multiple photoelectric probes are set at different combustion chamber length positions on the upper wall of the combustion chamber to measure flame self-luminous radiation data at different positions on the inner wall of the combustion chamber in real time.

4. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 2, characterized in that, Multiple pressure measuring points are set on the lower wall of the combustion chamber upstream of the cavity, and multiple pressure measuring points are set on the bottom wall of the cavity. Among them, at least one pressure measuring point is set on the bottom wall of the cavity upstream of the igniter, at least one pressure measuring point is set on the bottom wall of the cavity downstream of the igniter, and at least one pressure measuring point is set on the lower wall of the combustion chamber downstream of the cavity.

5. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 3 or 4, characterized in that, Each pressure measuring point is equipped with a set of photoelectric probes on the upper wall of the combustion chamber above it, and the positions of the pressure measuring points and photoelectric probes are vertically aligned.

6. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 5, characterized in that, At least one set of oxygen injection holes is provided on the concave wall surface upstream of the igniter, and at least one set of oxygen injection holes is provided on the concave wall surface downstream of the igniter. An oxygen source supplies oxygen to each set of oxygen injection holes through an oxygen supply pipeline. Each set of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. An independent oxygen injection valve is provided on the oxygen supply branch corresponding to each set of oxygen injection holes, and independent control of each set of oxygen injection holes is achieved through the oxygen injection valve.

7. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 6, characterized in that, The cavity wall includes a front wall, a bottom wall, and a rear wall. The front wall is perpendicular to the lower wall of the combustion chamber upstream of the cavity, forming a vertical step with the bottom wall. The rear wall is inclined relative to the bottom wall, forming an inclined transition between the cavity and the lower wall of the combustion chamber downstream of the cavity.

8. The method for real-time active oxygen supplementation control of scramjet engine combustion according to claim 7, characterized in that, At least one set of oxygen injection holes is provided on the front wall of the cavity, at least one set of oxygen injection holes is provided on the bottom wall of the cavity upstream of the igniter, and at least one set of oxygen injection holes is provided on the rear wall of the cavity.

9. The method for real-time active oxygen supplementation control of a scramjet engine according to any one of claims 3 to 8, characterized in that, Based on the current flame combustion state, corresponding control signals are generated to the oxygen injection valves in the combustion chamber to achieve active oxygen replenishment and active combustion control. This includes: adjusting the opening / closing status of the oxygen injection valves of each group of oxygen injection holes in real time based on the pressure data and photoelectric signal data of each measuring point location fed back in real time; opening the oxygen injection valves of each group of oxygen injection holes at measuring points with relatively lower pressure data and photoelectric signal data, and closing the oxygen injection valves of each group of oxygen injection holes at measuring points with relatively higher pressure data and photoelectric signal data. This adaptive adjustment continues until all measuring points are monitored to be in a stable and normal combustion state.

10. The method for real-time active oxygen supplementation control of a scramjet engine according to claim 9, characterized in that, If the wall pressure data measured by the pressure measuring point at a certain location is within the wall pressure range of the corresponding local weak combustion state of the flame, or the flame self-luminous radiation intensity data measured by the photoelectric probe at that location is within the flame self-luminous radiation intensity range of the corresponding local weak combustion state of the flame, then the oxygen injection valve corresponding to the set of oxygen injection holes closest to that location is opened to inject oxygen until the wall pressure data measured by the pressure measuring point at that location is within the wall pressure range of the corresponding normal combustion state of the flame, then the oxygen injection valve corresponding to the set of oxygen injection holes closest to that location is closed. If the wall pressure data measured by all pressure measuring points is within the wall pressure range of the corresponding flame global extinguishing or near-extinguishing state, or if the flame self-luminous radiation intensity data measured by all photoelectric probes is within the flame self-luminous radiation intensity range of the corresponding flame global extinguishing or near-extinguishing state, then open the oxygen injection valves corresponding to all groups of oxygen injection holes to inject oxygen until the wall pressure data measured by all pressure measuring points is within the wall pressure range of the corresponding flame normal combustion state, then close the oxygen injection valves corresponding to each group of oxygen injection holes. If it is necessary to improve the combustion performance of the combustion chamber, open the igniter and the oxygen injection valves corresponding to all oxygen injection holes, so that the wall pressure data measured by the pressure measuring points at all positions are in the wall pressure range of the corresponding flame-enhanced combustion state, thereby achieving enhanced combustion.

11. A real-time active oxygen supplementation control device for scramjet engine combustion, characterized in that, include: The combustion chamber is a concave combustion chamber, with a concave cavity provided on the lower wall of the combustion chamber, and the igniter is disposed on the bottom wall of the concave cavity; Following the direction of the supersonic flow, multiple pressure measuring points are set at different locations along the length of the combustion chamber on the lower wall of the combustion chamber to measure the pressure data at different locations on the inner wall of the combustion chamber in real time. Multiple sets of photoelectric probes are installed at different combustion chamber length positions on the upper wall of the combustion chamber to measure the flame self-luminous radiation data at different positions on the inner wall of the combustion chamber in real time; at least one set of oxygen injection holes is provided on the concave wall upstream of the igniter and at least one set of oxygen injection holes is provided on the concave wall downstream of the igniter. The oxygen source supplies oxygen to each set of oxygen injection holes through the oxygen supply pipeline. Each set of oxygen injection holes corresponds to an independent oxygen supply branch connected to the oxygen source. An independent oxygen injection valve is provided on the oxygen supply branch corresponding to each set of oxygen injection holes, and the independent control of each set of oxygen injection holes is achieved through the oxygen injection valve. The signal control system determines the current flame combustion state based on the flame combustion state discrimination criteria, the currently acquired combustion chamber wall pressure data, and the flame self-luminous radiation data. Based on the current flame combustion state, it generates corresponding control signals to the oxygen injection valves in the combustion chamber to achieve active oxygen replenishment and active combustion regulation.

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