Plasma ignition circuit for ignition electric nozzle of aero-engine
By designing the plasma ignition circuit of the aircraft engine ignition nozzle, combined with high-voltage arc-induced and high-frequency arc-dimensional circuit, the problem of poor ignition effect of high-power and high-altitude high-altitude aircraft engines is solved, and reliable ignition function and stable arc maintenance are achieved.
Patent Information
- Application Number
- CN202411972735.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-30
- Publication Date
- 2025-04-15
AI Technical Summary
The existing aero engine ignition system has good effect in low-power ignition systems, but is not good at high-power high-altitude ignition, and the plasma ignition method does not meet the high-altitude ignition needs of aero engines.
A plasma ignition circuit for the ignition nozzle of the aircraft engine is designed, combining high-voltage arc-induced circuit and high-frequency arc-dimensional circuit, and a high-voltage arc-induced circuit is used to generate a high-voltage and small current voltage pulse breakdown discharge gap, and a high-frequency arc-induced circuit is used to generate a low-voltage and large current high-frequency voltage source, continuously provide electrical energy to maintain the arc and realize the ignition function.
Effectively ensure the high-power high-altitude ignition effect of aircraft engines, ensure ignition reliability and stability, and adapt to ignition needs under different airflow conditions.
Smart Images
Figure CN119834643A_ABST
Abstract
Description
Technical Field
[0001] The present application belongs to the technical field of ignition design of aircraft engine ignition nozzles, and specifically relates to a plasma ignition circuit of an aircraft engine ignition nozzle. Background Art
[0002] At present, aircraft engines mainly use capacitor energy storage ignition. The principle is to store a certain amount of energy in a capacitor, discharge it at a certain frequency according to the discharge control circuit, and ignite the ignition nozzle. The ignition effect is related to the energy storage size and the discharge frequency. The capacitor energy storage ignition circuit has a good application effect in a low-power ignition system with a power of less than 100w, but has a poor effect on high-power and high-altitude ignition of aircraft engines.
[0003] Another ignition method is plasma ignition, the principle of which is to convert a 220V / 50Hz DC power supply into high voltage electricity through a transformer, or to rectify, invert, and boost a 220V / 50Hz AC power supply, and output it to the ignition nozzle to form a plasma flame. This plasma ignition method is currently only used in gas turbines, and this plasma ignition method does not meet the requirements for high-altitude ignition of aircraft engines.
[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention
[0005] The purpose of the present application is to provide a plasma ignition circuit for an aircraft engine ignition nozzle to overcome or alleviate at least one of the known technical deficiencies.
[0006] The technical solution of this application is:
[0007] An aircraft engine ignition nozzle plasma ignition circuit, comprising a high-voltage arc starting circuit and a high-frequency arc maintaining circuit;
[0008] The input end of the high-voltage arc ignition circuit is connected to a DC power supply, and the output end is connected to an ignition nozzle, so as to generate high voltage and low current, and output voltage pulses to the ignition nozzle at a certain frequency to break through the discharge gap of the ignition nozzle;
[0009] The input end of the high-frequency arc maintenance circuit is connected to a DC power supply, and the output end is connected to an ignition nozzle to generate low voltage and high current, output a high-frequency voltage source to the ignition nozzle, and after the discharge gap of the ignition nozzle is broken down, the ignition nozzle generates an arc, thereby realizing the ignition function of the ignition nozzle.
[0010] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, the input end of the high-voltage arc ignition circuit is connected to a DC power supply through a wiring terminal;
[0011] The high-voltage arc striking circuit outputs a voltage pulse frequency to the ignition nozzle that is less than 10HZ, a voltage greater than 5KV, and a current less than 0.2A.
[0012] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, the high-frequency arc maintenance circuit is connected to a DC power supply through a wiring terminal;
[0013] The high-voltage arc striking circuit outputs a high-frequency voltage source with a frequency greater than 50kHZ, a voltage less than 1KV, and a current greater than 1A to the ignition nozzle.
[0014] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, the high-voltage arc ignition circuit includes a discharge frequency control circuit, a flyback circuit, and an arc ignition transformer connected in sequence;
[0015] The discharge frequency control circuit controls the on-off of the DC power supply at a certain frequency. Each time it is turned on, the flyback circuit converts the DC power supply into an AC power supply, and the arc-starting transformer boosts the AC power supply to generate high voltage and low current, and outputs voltage pulses to the ignition nozzle.
[0016] The arc striking transformer uses a 30W low-power transformer.
[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, the high-frequency arc pilot circuit includes a half-bridge drive circuit and an arc pilot transformer connected in sequence, wherein the half-bridge drive circuit converts a DC power supply into an AC power supply, and the arc pilot transformer boosts the AC power supply to generate a low voltage and a large current, and outputs a high-frequency voltage source to the ignition nozzle;
[0018] The arc transformer uses a 400W high power transformer.
[0019] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, a protection circuit is provided for the high-voltage arc starting circuit and the high-frequency arc maintaining circuit to prevent crosstalk between the high-voltage arc starting circuit and the high-frequency arc maintaining circuit, thereby preventing damage to circuit components.
[0020] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, the protection circuit includes a high-voltage silicon stack and a full-bridge rectifier circuit, wherein the high-voltage silicon stack is arranged at the output end of the high-voltage arc ignition circuit, and performs half-wave rectification on the voltage pulse output by the high-voltage arc ignition circuit; the full-bridge rectifier circuit is arranged at the output end of the high-frequency arc maintaining circuit, and performs full-wave rectification on the high-frequency voltage source output by the high-frequency arc maintaining circuit.
[0021] According to at least one embodiment of the present application, in the above-mentioned aircraft engine ignition nozzle plasma ignition circuit, the forward conduction current of the high-voltage silicon stack is selected to be 0.1A;
[0022] The bridge current of the full-bridge rectifier circuit is selected to be 1.5 times the secondary current of the arc transformer.
[0023] This application has at least the following beneficial technical effects:
[0024] Provided is a plasma ignition circuit for an aircraft engine ignition nozzle. The circuit is designed to generate high voltage and low current with a high-voltage arc starting circuit, output a voltage pulse to the ignition nozzle to break down the ignition nozzle to complete the discharge, and then generate low voltage and high current with a high-frequency arc maintaining circuit, output a high-frequency voltage source to the ignition nozzle, continuously provide electrical energy along the discharge gap, generate an arc, and realize the ignition function of the ignition nozzle, which can effectively ensure the high-power and high-altitude ignition effect of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] Figure 1 It is a schematic diagram of a plasma ignition circuit of an aircraft engine ignition nozzle provided in an embodiment of the present application;
[0026] Figure 2 It is a schematic diagram of the ignition nozzle provided in the embodiment of the present application spraying a plasma flame.
[0027] Figure 3 It is a schematic diagram of the ignition nozzle provided in the embodiment of the present application spraying plasma flame under different airflow conditions.
[0028] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION
[0029] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.
[0030] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.
[0031] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.
[0032] A plasma ignition circuit for an aircraft engine ignition nozzle, such as Figure 1 As shown, it includes a high-voltage arc starting circuit and a high-frequency arc maintaining circuit.
[0033] The input end of the high-voltage arc ignition circuit is connected to a DC power supply, specifically through a terminal block, and the output end is connected to an ignition nozzle to generate high voltage and low current, and output voltage pulses to the ignition nozzle to break through the discharge gap of the ignition nozzle. The frequency of the voltage pulse output by the high-voltage arc ignition circuit to the ignition nozzle is controllable, specifically designed to be less than 10HZ, the voltage is greater than 5KV, and the current is less than 0.2A. The output of the repetitive frequency is used for the arc ignition circuit to re-ignite the arc when the arc is extinguished.
[0034] The input end of the high-frequency arc-maintaining circuit is connected to a DC power supply, specifically through a terminal block, and the output end is connected to an ignition nozzle to generate low voltage and high current, and output a high-frequency voltage source to the ignition nozzle. After the discharge gap of the ignition nozzle is broken down, the ignition nozzle generates an arc to realize the ignition function of the ignition nozzle. The frequency of the high-frequency voltage source output by the high-voltage arc-maintaining circuit to the ignition nozzle can be designed to be greater than 50kHZ, the voltage is less than 1KV, and the current is greater than 1A.
[0035] The plasma ignition circuit of the aircraft engine ignition nozzle disclosed in the above embodiment is designed to first generate high voltage and low current with a high-voltage arc starting circuit, output a voltage pulse to the ignition nozzle to break down the ignition nozzle to complete the discharge, and then generate low voltage and high current with a high-frequency arc maintaining circuit, output a high-frequency voltage source to the ignition nozzle, continuously provide electrical energy along the discharge gap, generate an arc, and realize the ignition function of the ignition nozzle, which can effectively ensure the high-power and high-altitude ignition effect of the aircraft engine.
[0036] The high-voltage arc striking circuit includes a discharge frequency control circuit, a flyback circuit, and an arc striking transformer connected in sequence. The discharge frequency control circuit controls the on-off of the DC power supply at a certain frequency. Each time it is turned on, the flyback circuit converts the DC power supply into an AC power supply. The arc striking transformer boosts the AC power supply to generate high voltage and low current, and outputs high voltage pulses to the ignition nozzle at a certain frequency. The arc striking transformer can use a 30W low-power transformer.
[0037] The high-frequency arc pilot circuit includes a half-bridge drive circuit and an arc pilot transformer connected in sequence. The half-bridge drive circuit converts the DC power supply into an AC power supply, and the arc pilot transformer boosts the AC power supply to generate a low voltage and a large current, and outputs a high-frequency voltage source to the ignition nozzle. The arc pilot transformer can be a 400W high-power transformer.
[0038] The half-bridge drive circuit has a simple structure and low control difficulty. Compared with the forward and flyback circuits, it can output higher power and can well meet the power requirements for maintaining arc burning.
[0039] If the high-voltage arc starting circuit and the high-frequency arc pilot circuit are directly connected to the two ends of the ignition nozzle, the high voltage output by the high-voltage arc starting circuit may damage the components of the high-frequency arc pilot circuit, and the high current output by the high-frequency arc pilot circuit may burn the components of the high-voltage arc starting circuit. For this reason, protection circuits are set in the high-voltage arc starting circuit and the high-frequency arc pilot circuit to prevent crosstalk between the high-voltage arc starting circuit and the high-frequency arc pilot circuit, which may cause damage to the circuit components.
[0040] The protection circuit includes a high-voltage silicon stack and a full-bridge rectifier circuit, wherein the high-voltage silicon stack is arranged at the output end of the high-voltage arc ignition circuit to perform half-wave rectification on the voltage pulse output by the high-voltage arc ignition circuit; the full-bridge rectifier circuit is arranged at the output end of the high-frequency arc maintenance circuit to perform full-wave rectification on the high-frequency voltage source output by the high-frequency arc maintenance circuit.
[0041] The high-voltage arc-starting circuit uses a high-voltage silicon stack for half-wave rectification, which has low cost and simple circuit structure. After half-wave rectification, it can still ensure the output of high-voltage pulses to break through the discharge gap. The high-frequency arc-maintaining circuit uses a full-bridge rectifier circuit for full-wave rectification, which can ensure output efficiency while realizing the rectification function. After rectification, the outputs of the high-voltage arc-starting circuit and the high-frequency arc-maintaining circuit are both DC outputs. The output of the high-frequency arc-maintaining circuit will be cut off by the high-voltage silicon stack and will not burn the components of the high-voltage arc-starting circuit. The output of the high-voltage arc-starting circuit will be protected by the full-bridge rectifier circuit and will not damage the components of the high-frequency arc-maintaining circuit, thereby realizing the protection of the high-voltage arc-starting circuit and the high-frequency arc-maintaining circuit.
[0042] The high-voltage silicon stack is used to withstand the high-voltage reverse voltage output by the high-voltage arc-starting circuit transformer. Due to the low reliability of the high-voltage silicon stack, the voltage margin should be fully considered during selection. Specifically, it can be considered as 2 times the voltage margin. Due to the low power of the high-voltage arc-starting circuit, the forward current of the high-voltage silicon stack is at the mA level. Therefore, the forward conduction current of the high-voltage silicon stack can be selected as 0.1A.
[0043] The full-bridge rectifier of the high-voltage arc-maintaining circuit must be able to rectify the AC output of the transformer and conduct the large current of the arc burning. Therefore, the reverse voltage of the rectifier bridge should also be twice the output voltage of the transformer. The bridge current of the full-bridge rectifier circuit is selected as 1.5 times the secondary current of the arc-maintaining transformer.
[0044] The above embodiment discloses the plasma ignition circuit of the aircraft engine ignition nozzle, wherein the high-voltage arc starting circuit can generate high-voltage pulses at a certain frequency to break through the discharge gap of the ignition nozzle. When the arc is extinguished due to external reasons, the high-voltage arc starting circuit can re-ignite the arc, repeatedly generate high-voltage pulses, break through the discharge gap again, and combine with the high-frequency arc maintenance circuit to make the arc burn again, thereby ensuring the ignition effect. After multiple tests, the high-voltage arc starting circuit and the high-frequency arc maintenance circuit did not cause crosstalk.
[0045] In a specific experiment, an ignition nozzle connected to the rear end of the ignition circuit is used to ignite the oil-gas mixture. The airflow in the simulated combustion chamber is 100L / min, the ignition system power supply voltage is 28VDC, and the plasma ejected by the ignition nozzle is as follows: Figure 2 As shown, it can be seen that the plasma is in the shape of a torch outside the ignition nozzle, and the flame length is about 3 cm.
[0046] The gas flow rate in the engine combustion chamber was changed to 50L / min, 100L / min, 150L / min and 200L / min, and ignition tests were carried out respectively. The arc plasma was photographed as follows: Figure 3 As shown, it can be seen that the airflow size has little effect on the plasma jet length, and the ignition jet length fluctuates within the range of (2 to 2.5) cm. When the airflow becomes larger, the arc can still continue to burn, and when the arc is blown out by the strong airflow, it can continue to ignite under the action of the high-voltage arc ignition circuit, ensuring the ignition effect.
[0047] Under different airflow conditions, the ignition system based on the plasma ignition circuit of the aircraft engine ignition nozzle disclosed in the above embodiment can ignite the oil-gas mixture in the combustion chamber, and can successfully ignite under both lean and heavy oil conditions, with reliable operation, good ignition performance, and good use effect. In addition, the plasma ignition circuit of the aircraft engine ignition nozzle disclosed in the above embodiment has been tested for high-altitude ignition in the engine combustion chamber, which can significantly improve the ignition height of the engine.
[0048] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.
Claims
1. A plasma ignition circuit for an aircraft engine ignition nozzle, characterized in that: Including high-voltage arc starting circuit and high-frequency arc maintaining circuit; The input end of the high-voltage arc ignition circuit is connected to a DC power supply, and the output end is connected to an ignition nozzle, so as to generate high voltage and low current, and output voltage pulses to the ignition nozzle at a certain frequency to break through the discharge gap of the ignition nozzle; The input end of the high-frequency arc maintenance circuit is connected to a DC power supply, and the output end is connected to an ignition nozzle to generate low voltage and high current, output a high-frequency voltage source to the ignition nozzle, and after the discharge gap of the ignition nozzle is broken down, the ignition nozzle generates an arc, thereby realizing the ignition function of the ignition nozzle.
2. The aircraft engine ignition nozzle plasma ignition circuit according to claim 1, characterized in that: The input end of the high-voltage arc ignition circuit is connected to a DC power supply through a wiring terminal; The high-voltage arc striking circuit outputs a voltage pulse frequency to the ignition nozzle that is less than 10HZ, a voltage greater than 5KV, and a current less than 0.2A.
3. The aircraft engine ignition nozzle plasma ignition circuit according to claim 2, characterized in that: The high-frequency arc-maintaining circuit is connected to a DC power supply through a terminal block; The high-voltage arc striking circuit outputs a high-frequency voltage source with a frequency greater than 50kHZ, a voltage less than 1KV, and a current greater than 1A to the ignition nozzle.
4. The aircraft engine ignition nozzle plasma ignition circuit according to claim 3, characterized in that: The high-voltage arc-starting circuit includes a discharge frequency control circuit, a flyback circuit, and an arc-starting transformer connected in sequence; The discharge frequency control circuit controls the on-off of the DC power supply at a certain frequency. Each time it is turned on, the flyback circuit converts the DC power supply into an AC power supply, and the arc-starting transformer boosts the AC power supply to generate high voltage and low current, and outputs voltage pulses to the ignition nozzle. The arc striking transformer uses a 30W low-power transformer.
5. The aircraft engine ignition nozzle plasma ignition circuit according to claim 4, characterized in that: The high-frequency arc pilot circuit includes a half-bridge drive circuit and an arc pilot transformer connected in sequence, wherein the half-bridge drive circuit converts a DC power supply into an AC power supply, and the arc pilot transformer boosts the AC power supply to generate a low voltage and a large current, and outputs a high-frequency voltage source to the ignition nozzle; The arc transformer uses a 400W high power transformer.
6. The aircraft engine ignition nozzle plasma ignition circuit according to claim 5, characterized in that: A protection circuit is provided for the high-voltage arc striking circuit and the high-frequency arc piloting circuit to prevent crosstalk between the high-voltage arc striking circuit and the high-frequency arc piloting circuit, thereby preventing damage to circuit components.
7. The aircraft engine ignition nozzle plasma ignition circuit according to claim 6, characterized in that: The protection circuit includes a high-voltage silicon stack and a full-bridge rectifier circuit, wherein the high-voltage silicon stack is arranged at the output end of the high-voltage arc ignition circuit to perform half-wave rectification on the voltage pulse output by the high-voltage arc ignition circuit; the full-bridge rectifier circuit is arranged at the output end of the high-frequency arc maintenance circuit to perform full-wave rectification on the high-frequency voltage source output by the high-frequency arc maintenance circuit.
8. The aircraft engine ignition nozzle plasma ignition circuit according to claim 7, characterized in that: The forward conduction current of the high voltage silicon stack is selected as 0.1A; The bridge current of the full-bridge rectifier circuit is selected to be 1.5 times the secondary current of the arc transformer.