Device for efficiently coupling jet igniter and combustion chamber and implementation method

Abstract

The invention discloses a jet igniter and combustion chamber efficient coupling device and an implementation method.The jet igniter and combustion chamber efficient coupling device comprises an igniter body and a gas inlet nozzle, the end, in the length direction, of the igniter body is in threaded connection with a combustion chamber, and the gas inlet nozzle is arranged on the side wall of the igniter body so that gas can conveniently enter the igniter body along the gas inlet nozzle; an included angle is formed between the air inlet nozzle and the igniter body so that air inlet resistance can be reduced, the included angle comprises a radial included angle and an axial included angle, the radial included angle is an included angle between radial airflow and a perpendicular line, and the axial included angle is an included angle between axial airflow and the axis of the igniter body. And the air flow enters the igniter body along the air inlet nozzle to form a radial air inlet angle or an axial air inlet angle. The gas inlet nozzle is arranged on the side wall of the igniter body, and the included angle is formed between the gas inlet nozzle and the igniter body, so that the gas flow utilization rate is increased, the gas flow loss is reduced, and the purpose of improving the ignition efficiency is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a device and an implementation method for efficiently coupling a jet igniter with a combustion chamber. Background Art

[0002] As the power source of an aircraft, the performance of an aircraft engine directly affects its flight performance and safety. The ignition system, a key component in the engine starting and combustion process, has a significant impact on the engine's starting speed, combustion efficiency, and emissions control. With the continuous improvement of fighter aircraft performance, higher requirements are being placed on the starting reliability and combustion stability of aircraft engines under extreme conditions. Traditional spark ignition technology is insufficient to meet these requirements. Plasma ignition technology, with its significant advantages such as short ignition delay, high ignition energy, and strong penetration, has a significant impact on improving engine performance. Current igniter designs mostly focus on improving power supply control and overall structure to enhance jet stiffness. The coupling between the igniter and the combustion chamber is closely related to ignition performance, and the igniter's bleed air is also a crucial component. The bleed air structure not only affects the flow field around the igniter, but the quality of the bleed air also determines the ignition performance. Therefore, it is necessary to design a device and implementation method for efficiently coupling the jet igniter with the combustion chamber. Experimental exploration of the optimal igniter installation angle range is of great significance for improving ignition performance and overall engine performance. Summary of the Invention

[0003] The purpose of the present invention is to overcome the deficiencies in the above-mentioned prior art and to provide a device and implementation method for efficiently coupling a jet igniter with a combustion chamber. By arranging an air inlet nozzle on the side wall of the igniter body and an angle between the air inlet nozzle and the igniter body, it is convenient to improve the airflow utilization rate and reduce the airflow loss, thereby achieving the purpose of improving the ignition efficiency.

[0004] To achieve the above-mentioned purpose, the technical solution adopted by the present invention is: a device for efficiently coupling a jet igniter with a combustion chamber, comprising an igniter body and an air inlet nozzle, wherein the end of the igniter body along the length direction is threadedly connected to the combustion chamber, and the air inlet nozzle is arranged on the side wall of the igniter body to facilitate the gas to enter the igniter body along the air inlet nozzle, and there is an angle between the air inlet nozzle and the igniter body to facilitate reducing the intake resistance.

[0005] Preferably, the cross section of the air inlet nozzle is circular, and a distance is left between the air inlet nozzle and the end of the igniter body.

[0006] Preferably, the angle includes a radial angle and an axial angle, the radial angle is the angle between the radial airflow and the vertical line, the axial angle is the angle between the axial airflow and the axis of the igniter body, and the airflow enters the igniter body along the air inlet nozzle to form a radial air inlet angle or an axial air inlet angle.

[0007] The present invention also discloses a method for realizing efficient coupling of a jet igniter and a combustion chamber, comprising: step S1: building an experimental platform to design the intake angle parameters of the igniter and determine the deflection direction and deflection angle of the intake nozzle; step S2: verifying the ignition effect based on the experimental platform built in step S1 and recording relevant working parameters; step S3: analyzing the influence of the intake velocity on the jet characteristics of the jet igniter based on the relevant working parameters of step S2; and step S4: determining the intake angle of the igniter based on step S3.

[0008] Preferably, the relevant working parameters include jet length, jet area and air intake angle of the igniter, and the air intake angle of the igniter includes an axial air intake angle and a radial air intake angle.

[0009] Preferably, the experimental platform includes a jet igniter, a power supply system, an air supply system, an air flow control device, and a data acquisition system. The air supply system is connected to the jet igniter through a pipeline to facilitate the supply of air to the jet igniter; the air flow control device is installed on the pipeline connecting the jet igniter and the air supply system to facilitate the control of the air intake of the jet igniter; the power supply system is connected to the jet igniter to facilitate the provision of excitation to the jet igniter for ignition; and the data acquisition system is connected to the jet igniter for collecting ignition data.

[0010] Preferably, the data acquisition system includes an oscilloscope and a high-speed camera. The oscilloscope is connected to the surface of the igniter body through a line to facilitate measuring the current and voltage on the surface of the igniter body. The high-speed camera is arranged at the outlet of the igniter body to facilitate collecting the jet length and jet area of ​​the gas.

[0011] Preferably, the data acquisition system further comprises a data processor and a display, wherein the data processor is connected to the oscilloscope and the high-speed camera to receive data, and the display is connected to the data processor to display data processing results.

[0012] Compared with the prior art, the present invention has the following advantages:

[0013] 1. The present invention sets an air inlet nozzle on the side wall of the igniter body, and there is an angle between the air inlet nozzle and the igniter body, which is convenient for improving the airflow utilization rate and reducing the airflow loss, thereby achieving the purpose of improving the ignition efficiency.

[0014] 2. The present invention explores the influence of the air intake angle on the igniter jet characteristics by building an experimental platform. By adjusting the air intake speed and the air intake angle, the corresponding jet length and jet area are obtained. The optimal air intake speed and air intake angle are determined according to the jet length and jet area, thereby reducing material waste and improving construction efficiency.

[0015] 3. The present invention combines an igniter with plasma technology, using gas discharge to produce ionization, causing the gas temperature to rise rapidly to form a local high-temperature zone, and generating a large amount of plasma rich in high-temperature and high-speed active particles, thereby achieving rapid ignition of the combustible mixture or enhanced combustion. It has the advantages of high ignition energy, short delay time, wide ignition boundary, simple structure, and light weight.

[0016] The present invention is further described in detail below through the accompanying drawings and examples. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a structural schematic diagram of the jet igniter of the present invention;

[0018] Figure 2 This is a structural diagram of the connection between the igniter and the combustion chamber of the present invention;

[0019] Figure 3 Schematic diagram of the effect of the air intake angle on the jet length of the present invention;

[0020] Figure 4 Schematic diagram of the effect of the air intake angle on the jet area of ​​the present invention.

[0021] Description of the accompanying drawings:

[0022] 1—Ignition device body; 2—Air intake nozzle; 3—Combustion chamber. DETAILED DESCRIPTION

[0023] like Figure 1 、 Figure 2 As shown, the present invention discloses a device for efficiently coupling a jet igniter with a combustion chamber, comprising an igniter body 1 and an air inlet nozzle 2. The end of the igniter body 1 along the length direction is threadedly connected to the combustion chamber 3. The air inlet nozzle 2 is arranged on the side wall of the igniter body 1 to facilitate the gas to enter the igniter body 1 along the air inlet nozzle 2. There is an angle between the air inlet nozzle 2 and the igniter body 1 to facilitate reducing the intake resistance.

[0024] The jet igniter of the present application is a self-entrained jet igniter, which includes an igniter body 1 and an air inlet nozzle 2. The igniter body 1 and the air inlet nozzle 2 are made as one piece, and there is an angle between the air inlet nozzle 2 and the igniter body 1. The end of the air inlet nozzle 2 along the length direction is connected to the side wall of the igniter body 1, which is convenient for the gas to enter the igniter body 1 along the air inlet nozzle 2. Based on the different connection angles between the air inlet nozzle 2 and the igniter body 1, the air flow velocity and air intake volume entering the igniter body 1 are different, which in turn affects the combustion effect of the combustion chamber 3. The end of the igniter body 1 along the length direction is threadedly connected to the combustion chamber 3, and a sealing ring is provided at the connection between the igniter body 1 and the combustion chamber 3 to prevent gas leakage. The detachable connection between the igniter body 1 and the combustion chamber 3 is convenient for replacing the jet igniter, ensuring the ignition effect and improving the ignition efficiency.

[0025] The cross section of the air inlet nozzle 2 is circular, and a distance is left between the air inlet nozzle 2 and the end of the igniter body 1 .

[0026] In this embodiment, the air inlet nozzle 2 and the igniter body 1 are both hollow cylindrical structures, which reduce the air intake resistance of the gas and improve the combustion efficiency; the air inlet nozzle 2 is installed on the side wall of the igniter body 1 and a distance is left between it and the end of the igniter body 1, so that the gas has a certain jet length.

[0027] The self-entrained jet igniter uses air as the medium and discharges in the form of a sliding arc. It has strong penetration ability, high ignition energy and simple structure. During the design stage of the self-entrained jet igniter, based on the current processing feasibility, multiple air intake angles and the position of the air intake nozzle 2 on the side wall of the igniter body 1 are determined, that is, the positional relationship between the air intake nozzle 2 and the igniter body 1 is determined. Based on the positional relationship between the air intake nozzle 2 and the igniter body 1, multiple self-entrained jet igniters are processed. The angles and positional relationships between the air intake nozzle 2 and the igniter body 1 in these multiple self-entrained jet igniters are different.

[0028] The angle includes a radial angle and an axial angle. The radial angle is the angle between the radial airflow and the vertical line, and the axial angle is the angle between the axial airflow and the axis of the igniter body 1. The airflow enters the igniter body 1 along the air inlet nozzle 2 to form a radial intake angle or an axial intake angle.

[0029] In this embodiment, the air inlet nozzle 2 and the igniter body 1 are both hollow cylindrical structures, and each igniter body 1 is provided with an air inlet nozzle 2. The igniter body 1 is placed horizontally along the length direction, and the air inlet nozzle 2 is provided on the outer wall of the igniter body 1, and the central axis of the air inlet nozzle 2 has an angle with the vertical direction, so that a radial angle is formed between the air inlet nozzle 2 and the igniter body 1. The degree of the radial angle can be preset in advance based on experience, and the self-entrained jet igniter is processed according to the preset radial angle, so that the angle between the air inlet nozzle 2 and the igniter body 1 in each self-entrained jet igniter is different, and it is stipulated that the radial angle is positive when the air inlet nozzle 2 is located on the left side of the igniter body 1, and the radial angle is negative when the air inlet nozzle 2 is located on the right side of the igniter body 1, so the preset radial angle can be -30°, -10°, 0°, 10°, 30°, etc., and this application does not impose any restrictions on this;

[0030] The igniter body 1 is placed vertically along the length direction, and the air inlet nozzle 2 is arranged on the outer wall of the igniter body 1. If the central axis of the air inlet nozzle 2 has an angle with the horizontal direction, an axial angle is formed between the air inlet nozzle 2 and the igniter body 1. The degree of the axial angle can be preset in advance based on experience. The self-entrained jet igniter is processed according to the preset axial angle, so that the angle between the air inlet nozzle 2 and the igniter body 1 in each self-entrained jet igniter is different, and it is stipulated that the axial angle is positive when the air inlet nozzle 2 is deflected upward, and the axial angle is negative when the air inlet nozzle 2 is deflected downward. Therefore, the degree of the preset axial angle can be -60°, -45°, 0°, 45°, 60°, etc., and this application does not impose any restrictions on this.

[0031] In a possible embodiment, the igniter body 1 is provided with a plurality of air inlet nozzles 2 at intervals along the circumferential direction, each air inlet nozzle 2 is connected to the igniter body 1, and the radial angles of each air inlet nozzle 2 and the igniter body 1 are different. A connecting plate is provided at the intersection of each air inlet nozzle 2 and the igniter body 1, and the curvature of the connecting plate is consistent with that of the side wall of the igniter body 1. The connecting plate can slide along the side wall of the igniter body 1. When the connecting plate is slid in a direction away from the air inlet nozzle 2, the air inlet nozzle 2 is connected to the igniter body 1, and the air flow enters the igniter body 1 along the air inlet nozzle 2; when the connecting plate is slid in a direction close to the air inlet nozzle 2 so that the end of the connecting plate is tightly attached to the igniter body 1, the air inlet nozzle 2 and the igniter body 1 are disconnected, and the air flow cannot enter the igniter body 1 along the air inlet nozzle 2. If the air flow needs to enter the igniter body 1 along the air inlet nozzle 2, at least one connecting plate at the connection between the air inlet nozzle 2 and the igniter body 1 is opened;

[0032] Specifically, four air inlet nozzles 2 are arranged at intervals along the circumferential direction of the igniter body 1, and the radial angles of each air inlet nozzle 2 and the igniter body 1 are different. The end of the igniter body 1 along the length direction is threadedly connected to the combustion chamber 3. The working environment of multiple radial air inlet angles is simulated by one igniter body 1, thereby improving the utilization efficiency of the self-entrained jet igniter; the number of air inlet nozzles 2 on the igniter body 1 can also be two, and there is no restriction on this, which is determined according to the length, diameter and current working environment of the igniter body 1.

[0033] In another possible embodiment, different from the above embodiment, the axial angles between each air inlet nozzle 2 and the igniter body 1 are different;

[0034] Specifically, the igniter body 1 is provided with four air inlet nozzles 2 at intervals along the circumferential direction, and the axial angle between each air inlet nozzle 2 and the igniter body 1 is different. The end of the igniter body 1 along the length direction is threadedly connected to the combustion chamber 3. The working environment of multiple axial air inlet angles is simulated by one igniter body 1, thereby improving the utilization efficiency of the self-entrained jet igniter. The number of air inlet nozzles 2 on the igniter body 1 can also be two, that is, an air inlet nozzle 2 is provided on both sides of the length direction of the igniter body 1. This application does not impose any restrictions on this. The number of air inlet nozzles 2 on the igniter body 1 is determined according to the length, diameter and current working environment of the igniter body 1.

[0035] like Figures 1 to 4 As shown, the present invention also discloses a method for realizing efficient coupling between a jet igniter and a combustion chamber, comprising:

[0036] Step S1: Building an experimental platform to design the igniter intake angle parameters and determine the deflection direction and deflection angle of the intake nozzle;

[0037] Step S2: Verify the ignition effect based on the experimental platform built in step S1 and record relevant working parameters;

[0038] The relevant working parameters include inlet velocity, jet length and jet area.

[0039] Step S3: Based on the relevant working parameters of step S2, analyzing the influence of the intake velocity on the jet characteristics of the jet igniter;

[0040] Step S4: Based on step S3, determine the igniter air intake angle.

[0041] Under the condition of the same intake air velocity, the intake angle of the igniter is determined based on the jet length and jet area.

[0042] Example 1

[0043] Adjust the air intake speed to 15m / s, select the self-priming jet igniter with the axial angles of -60°, -45°, 0°, 45°, and 60° between the air intake nozzle 2 and the igniter body 1, first, select the self-priming jet igniter with the axial angle of -60° between the air intake nozzle 2 and the igniter body 1, thread the end of the igniter body 1 to the combustion chamber 3, and the gas enters the igniter body 1 along the air intake nozzle 2. The jet length and jet area of ​​the gas are collected by a high-speed camera. After the data collection is completed, the self-priming jet igniter is separated from the combustion chamber 3; then, select the self-priming jet igniter with the axial angle of -45° between the air intake nozzle 2 and the igniter body 1 For a self-entrained air jet igniter, after the igniter body 1 is threadedly connected to the combustion chamber 3, the axial angle between the gas and the igniter body 1 after the gas enters the air inlet nozzle 2 is -45°. The jet length and jet area of ​​the gas are collected by a high-speed camera. After the data collection is completed, the self-entrained air jet igniter is separated from the combustion chamber 3; the self-entrained air jet igniter with axial angles of 0°, 45°, and 60° between the air inlet nozzle 2 and the igniter body 1 is threadedly connected to the combustion chamber 3 in turn, and the jet length and jet area of ​​the gas are collected respectively; thus, it is concluded that when the intake speed is 15m / s, the changing trends of the jet length and jet area follow the changes of the intake angle.

[0044] Example 2

[0045] Different from Example 1, the intake speed is adjusted to 30 m / s, and the jet length and jet area of ​​the gas are collected when the axial angles between the intake nozzle 2 and the igniter body 1 are -60°, -45°, 0°, 45°, and 60°, respectively. It is found that when the intake speed is 30 m / s, the changing trends of the jet length and jet area with the change of the intake angle are obtained.

[0046] Example 3

[0047] Different from Example 1, the intake speed is adjusted to 45 m / s, and the jet length and jet area of ​​the gas are collected when the axial angles between the intake nozzle 2 and the igniter body 1 are -60°, -45°, 0°, 45°, and 60°, respectively. It is found that when the intake speed is 45 m / s, the changing trends of the jet length and jet area with the change of the intake angle are obtained.

[0048] Example 4

[0049] Different from Example 1, the intake speed is adjusted to 60m / s, and the jet length and jet area of ​​the gas are collected when the axial angles between the intake nozzle 2 and the igniter body 1 are -60°, -45°, 0°, 45°, and 60°, respectively. It is found that when the intake speed is 60m / s, the changing trends of the jet length and jet area with the change of the intake angle are obtained.

[0050] Combining Examples 1 to 4, we can conclude Figure 3 (a) and Figure 4 (b) Figure 3 (a) and Figure 4 (b) It can be seen that when the intake speed is 15m / s, the jet length takes the maximum value when the axial angle between the air intake nozzle 2 and the igniter body 1 is 0°, and the jet area takes the maximum value when the axial angle between the air intake nozzle 2 and the igniter body 1 is -45°; when the intake speed is 30m / s, the jet length takes the maximum value when the axial angle between the air intake nozzle 2 and the igniter body 1 is -45°, and the jet area takes the maximum value when the axial angle between the air intake nozzle 2 and the igniter body 1 is -45°; when the intake speed is 45m / s, the jet length takes the maximum value when the axial angle between the air intake nozzle 2 and the igniter body 1 is -45°, and the jet area takes the maximum value when the axial angle between the air intake nozzle 2 and the igniter body 1 is -45°; when the intake speed is 60m / s, with the change of the axial angle between the air intake nozzle 2 and the igniter body 1, the jet length and jet area do not change significantly.

[0051] Example 5

[0052] Adjust the air intake speed to 15m / s, select the self-priming jet igniter with the radial angles of -30°, -10°, 0°, 10°, and 30° between the air intake nozzle 2 and the igniter body 1, first, select the self-priming jet igniter with the radial angle of -30° between the air intake nozzle 2 and the igniter body 1, thread the end of the igniter body 1 to the combustion chamber 3, and the gas enters the igniter body 1 along the air intake nozzle 2. The jet length and jet area of ​​the gas are collected by a high-speed camera. After the data collection is completed, the self-priming jet igniter is separated from the combustion chamber 3; then, select the self-priming jet igniter with the radial angle of -10° between the air intake nozzle 2 and the igniter body 1. For a self-entrained air jet igniter, after the igniter body 1 is threadedly connected to the combustion chamber 3, the radial angle between the gas and the igniter body 1 after the gas enters the air inlet nozzle 2 is -10°. The jet length and jet area of ​​the gas are collected by a high-speed camera. After the data collection is completed, the self-entrained air jet igniter is separated from the combustion chamber 3; the self-entrained air jet igniter with axial angles of 0°, 10°, and 30° between the air inlet nozzle 2 and the igniter body 1 is threadedly connected to the combustion chamber 3 in turn, and the jet length and jet area of ​​the gas are collected respectively, so that it can be concluded that when the intake speed is 15m / s, the changing trends of the jet length and jet area change with the change of the intake angle.

[0053] Example 6

[0054] Different from Example 5, the intake speed is adjusted to 30 m / s, and the jet length and jet area of ​​the gas are collected when the radial angles between the intake nozzle 2 and the igniter body 1 are -30°, -10°, 0°, 10°, and 30°, respectively. It is found that when the intake speed is 30 m / s, the changing trends of the jet length and jet area with the change of the intake angle are obtained.

[0055] Example 7

[0056] Different from Example 5, the intake speed is adjusted to 45 m / s, and the jet length and jet area of ​​the gas are collected when the radial angles between the intake nozzle 2 and the igniter body 1 are -30°, -10°, 0°, 10°, and 30°, respectively. It is found that when the intake speed is 45 m / s, the changing trends of the jet length and jet area with the change of the intake angle are obtained.

[0057] Example 8

[0058] Different from Example 5, the intake speed is adjusted to 60m / s, and the jet length and jet area of ​​the gas are collected when the radial angles between the intake nozzle 2 and the igniter body 1 are -30°, -10°, 0°, 10°, and 30°, respectively. It is found that when the intake speed is 60m / s, the changing trends of the jet length and jet area with the change of the intake angle are obtained.

[0059] Combining Examples 5 to 8, we can conclude Figure 3 (b) and Figure 4 (a), by Figure 3 (b) Figure 4 (a) It can be seen that when the intake speed is 15m / s, the jet length takes the maximum value when the radial angle between the air intake nozzle 2 and the igniter body 1 is 0°, and the jet area takes the maximum value when the radial angle between the air intake nozzle 2 and the igniter body 1 is -30°; when the intake speed is 30m / s, the jet length takes the maximum value when the radial angle between the air intake nozzle 2 and the igniter body 1 is 30°, and the jet area takes the maximum value when the radial angle between the air intake nozzle 2 and the igniter body 1 is 30°; when the intake speed is 45m / s, the jet length takes the maximum value when the radial angle between the air intake nozzle 2 and the igniter body 1 is 10°, and the jet area takes the maximum value when the radial angle between the air intake nozzle 2 and the igniter body 1 is -10°; when the intake speed is 60m / s, with the change of the axial angle between the air intake nozzle 2 and the igniter body 1, the jet length and jet area do not change significantly.

[0060] From 3 and Figure 4 It can be seen that the jet length caused by the intake angle varies in the range of 15% to 57.1%, and the jet area caused by the intake angle varies in the range of 56.2% to 79.4%.

[0061] The relevant working parameters include jet length, jet area and the air intake angle of the igniter, and the air intake angle of the igniter includes an axial air intake angle and a radial air intake angle.

[0062] The experimental platform includes a jet igniter, a power supply system, an air supply system, an air flow control device, and a data acquisition system.

[0063] The air supply system is connected to the jet igniter through a pipeline to facilitate the supply of air to the jet igniter;

[0064] The airflow control device is installed on the pipe connecting the jet igniter and the air supply system to facilitate the control of the air intake of the jet igniter;

[0065] The power supply system is connected to the jet igniter to facilitate providing excitation to the jet igniter for ignition;

[0066] The data acquisition system is connected to the jet igniter for collecting ignition data.

[0067] In this embodiment, the air supply system is connected to the air intake nozzle 2 through a pipe to facilitate the supply of air to the air intake nozzle 2. The airflow control device is installed between the connecting pipe of the air intake nozzle 2 and the air supply system to facilitate the control of the airflow speed entering the air intake nozzle 2. The power supply system is connected to the igniter body 1 and the combustion chamber 3 respectively. The power supply system stimulates the igniter body 1 to ignite. The data acquisition system collects the jet length and jet area in real time, which is convenient for determining the relationship between the intake angle, jet length and jet area when the intake speed of the air intake nozzle 2 is fixed, and determining the optimal intake speed and the optimal intake angle range.

[0068] The gas supply system is equipped with an air filter, which filters dust and impurities in the gas, thereby increasing the purity of the gas entering the jet igniter, reducing experimental errors and improving experimental reliability.

[0069] The data acquisition system includes an oscilloscope and a high-speed camera. The oscilloscope is connected to the surface of the igniter body 1 through a line to facilitate measuring the current and voltage on the surface of the igniter body 1. The high-speed camera is arranged at the outlet of the igniter body 1 to facilitate collecting the jet length and jet area of ​​the gas.

[0070] The oscilloscope is connected to the igniter body 1 through the leads of the voltage and current probes respectively, so as to collect the current and voltage during the ignition process of the igniter body 1. The high-speed camera collects and saves the jet length and jet area of ​​the gas and transmits the data to the data processor.

[0071] The data acquisition system further comprises a data processor and a display. The data processor is connected to the oscilloscope and the high-speed camera to facilitate receiving data. The display is connected to the data processor to display data processing results.

[0072] The data processor receives the current and voltage collected by the oscilloscope for processing. The data processor analyzes the discharge characteristics of the jet igniter through the current and voltage peaks during excitation, and sends the processing results to the display for display; at the same time, the data processor processes the jet length and jet area of ​​the gas collected by the high-speed camera, and analyzes the influence of factors such as the intake speed and the deflection angle of the intake nozzle 2 on the jet characteristics.

[0073] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any way. Any simple modification, change and equivalent structural transformation made to the above embodiment based on the technical essence of the present invention shall still fall within the scope of protection of the technical solution of the present invention.

Claims

1. A device for efficiently coupling a jet igniter with a combustion chamber, characterized in that: The invention comprises an igniter body (1) and an air inlet nozzle (2), wherein the end of the igniter body (1) along the length direction is threadedly connected to the combustion chamber (3), and the air inlet nozzle (2) is arranged on the side wall of the igniter body (1) to facilitate gas to enter the igniter body (1) along the air inlet nozzle (2), and an angle is formed between the air inlet nozzle (2) and the igniter body (1) to facilitate reducing air intake resistance.

2. A device for efficiently coupling a jet igniter to a combustion chamber according to claim 1, characterized in that: The cross section of the air inlet nozzle (2) is circular, and a distance is left between the air inlet nozzle (2) and the end of the igniter body (1).

3. The device for efficiently coupling a jet igniter to a combustion chamber according to claim 1, characterized in that: The angle includes a radial angle and an axial angle. The radial angle is the angle between the radial airflow and the vertical line, and the axial angle is the angle between the axial airflow and the axis of the igniter body (1). The airflow enters the igniter body (1) along the air inlet nozzle (2) to form a radial air inlet angle or an axial air inlet angle.

4. A method for achieving coupling of a device for efficiently coupling a jet igniter to a combustion chamber according to any one of claims 1 to 3, comprising: Step S1: Building an experimental platform to design the igniter intake angle parameters and determine the deflection direction and deflection angle of the intake nozzle; Step S2: Verify the ignition effect based on the experimental platform built in step S1 and record relevant working parameters; Step S3: Based on the relevant working parameters of step S2, analyzing the influence of the intake velocity on the jet characteristics of the jet igniter; Step S4: Based on step S3, determine the igniter air intake angle.

5. A method for realizing efficient coupling between a jet igniter and a combustion chamber according to claim 4, characterized in that: The relevant working parameters include jet length, jet area and the air intake angle of the igniter, and the air intake angle of the igniter includes an axial air intake angle and a radial air intake angle.

6. A method for realizing efficient coupling between a jet igniter and a combustion chamber according to claim 4, characterized in that: The experimental platform includes a jet igniter, a power supply system, an air supply system, an air flow control device, and a data acquisition system. The air supply system is connected to the jet igniter through a pipeline to facilitate the supply of air to the jet igniter; The airflow control device is installed on the pipe connecting the jet igniter and the air supply system to facilitate the control of the air intake of the jet igniter; The power supply system is connected to the jet igniter to facilitate providing excitation to the jet igniter for ignition; The data acquisition system is connected to the jet igniter for collecting ignition data.

7. A method for realizing efficient coupling between a jet igniter and a combustion chamber according to claim 6, characterized in that: The data acquisition system comprises an oscilloscope and a high-speed camera. The oscilloscope is connected to the surface of the igniter body (1) via a circuit to facilitate measurement of the current and voltage on the surface of the igniter body (1). The high-speed camera is arranged at the outlet of the igniter body (1) to facilitate collection of the jet length and jet area of ​​the gas.

8. A method for realizing efficient coupling between a jet igniter and a combustion chamber according to claim 7, characterized in that: The data acquisition system further comprises a data processor and a display. The data processor is connected to the oscilloscope and the high-speed camera to facilitate receiving data. The display is connected to the data processor to display data processing results.

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