A broadband ignition device for aircraft engines

Abstract

The application relates to the field of engine ignition technology and discloses a wide-frequency ignition device for an aero-engine, which inputs power through an alternator, saves secondary conversion and frequency stabilization equipment of engine power, improves energy conversion efficiency, and reduces the weight of the engine; a combined transformer is adopted, different magnetic core materials are used in different frequency bands, the use frequency range of the ignition device is widened; a spark extension circuit is adopted, the spark duration is prolonged, and the engine ignition difficulty problem is solved to a certain extent.

Description

Technical Field

[0001] This invention relates to the field of aero-engine ignition technology, specifically, to a broadband ignition device for aero-engines. Background Technology

[0002] Existing ignition systems for aircraft engines require a stable power supply to operate reliably. When power is directly supplied from an alternator, the output voltage will vary significantly as the alternator's speed and load change over a wide range, causing the ignition system to malfunction. Summary of the Invention

[0003] The purpose of this invention is to address the above-mentioned problems by providing a broadband ignition device for aero engines.

[0004] This invention is achieved through the following technical solution:

[0005] A broadband ignition device for an aero-engine includes a voltage conversion circuit, a voltage multiplier rectifier circuit, an energy storage circuit, a discharge circuit, a spark extension circuit, and an electric nozzle connected in sequence.

[0006] The voltage conversion circuit includes a choke coil component L1 and a transformer T1, wherein the choke coil component L1 is connected in series with the primary coil of the series transformer T1.

[0007] The voltage multiplier rectifier circuit comprises a voltage multiplier capacitor C1, a voltage multiplier capacitor C2, a rectifier silicon stack D1, and a rectifier silicon stack D2. The voltage multiplier capacitor C1 and the rectifier silicon stack D1, connected in series, form the first branch. The voltage multiplier capacitor C2 and the rectifier silicon stack D2, connected in series, form the second branch. The first branch and the second branch are connected in parallel across the secondary coil of the transformer T1.

[0008] The energy storage circuit includes a resistor R1 and an energy storage capacitor C3 connected in series, and the energy storage circuit is connected in parallel across the silicon stack D2l.

[0009] The discharge point includes a high-voltage discharge tube G1, a resistor R2, and a resistor R3. The high-voltage discharge tube G1 and the resistor R3 are connected in series to form a third branch, and the resistors R2 and R3 are connected in series to form a fourth branch. Both the third and fourth branches are connected in parallel with the energy storage capacitor C3.

[0010] The spark extension circuit includes an inductor L2, one end of which is connected between the high-voltage discharge tube G1 and the resistor R3, and the other end of which is connected to the electrode nozzle.

[0011] To better realize the present invention, the operating voltage frequency range of the wideband ignition device is further defined as 0~1GHz.

[0012] To better realize the present invention, the transformer T1 is a combined transformer, including an iron core, a locking device, a spring and a coil component, the coil component being wound on the iron core, and the iron core being pressed onto the locking device by the spring.

[0013] To better realize the present invention, the iron core further includes silicon steel sheet magnetic core, ferrite magnetic core and amorphous magnetic core.

[0014] To further realize the present invention, the silicon steel sheet magnetic core, ferrite magnetic core and amorphous magnetic core are all in the form of rings.

[0015] To further realize the present invention, the silicon steel sheet magnetic core includes two U-shaped silicon steel blocks with opposite openings, and a thermal expansion and contraction element is provided between the two U-shaped silicon steel blocks; the amorphous magnetic core includes two U-shaped amorphous blocks with opposite openings, and a thermal expansion and contraction element is provided between the two U-shaped amorphous blocks.

[0016] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0017] This invention provides a wideband ignition device for aircraft engines. By using an AC generator as the power input, it eliminates the need for secondary power conversion and frequency stabilization equipment in the engine, thereby improving energy conversion efficiency and reducing engine weight. It adopts a combined transformer and utilizes the difference in operating frequency bands of different magnetic core materials to widen the operating frequency range of the ignition device. It also employs a spark extension circuit to extend the spark duration, thus solving the problem of difficult engine ignition to a certain extent. Attached Figure Description

[0018] The technical solution will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0019] Figure 1 A schematic diagram of a broadband ignition device for an aero-engine provided by the present invention;

[0020] Figure 2 This is a schematic diagram of the circuit component connections for a broadband ignition device for an aero-engine according to the present invention.

[0021] Figure 3 This is a schematic diagram of the structure of the transformer T1 provided by the present invention.

[0022] The components include: 1. Silicon steel sheet magnetic core; 2. Ferrite magnetic core; 3. Amorphous magnetic core; 4. Thermal expansion and contraction components; 5. Locking device; 6. Spring; 7. Coil components. Detailed Implementation

[0023] The following detailed description, in conjunction with specific embodiments, further illustrates the above-described content of the present invention. However, this should not be construed as limiting the scope of the present invention to the following examples. Various substitutions or modifications made based on ordinary technical knowledge and conventional methods in the art without departing from the above-described technical concept of the present invention should be included within the scope of the present invention.

[0024] Example:

[0025] This embodiment provides a wideband ignition device for an aero-engine, comprising a voltage conversion circuit, a voltage multiplier rectifier circuit, an energy storage circuit, a discharge circuit, a spark extension circuit, and an electric nozzle connected in sequence.

[0026] The voltage conversion circuit includes a choke coil component L1 and a transformer T1, wherein the choke coil component L1 is connected in series with the primary coil of the series transformer T1.

[0027] The voltage multiplier rectifier circuit comprises a voltage multiplier capacitor C1, a voltage multiplier capacitor C2, a rectifier silicon stack D1, and a rectifier silicon stack D2. The voltage multiplier capacitor C1 and the rectifier silicon stack D1, connected in series, form the first branch. The voltage multiplier capacitor C2 and the rectifier silicon stack D2, connected in series, form the second branch. The first branch and the second branch are connected in parallel across the secondary coil of the transformer T1.

[0028] The energy storage circuit includes a resistor R1 and an energy storage capacitor C3 connected in series, and the energy storage circuit is connected in parallel across the silicon stack D2l.

[0029] The discharge point includes a high-voltage discharge tube G1, a resistor R2, and a resistor R3. The high-voltage discharge tube G1 and the resistor R3 are connected in series to form a third branch, and the resistors R2 and R3 are connected in series to form a fourth branch. Both the third and fourth branches are connected in parallel with the energy storage capacitor C3.

[0030] The spark extension circuit includes an inductor L2, one end of which is connected between the high-voltage discharge tube G1 and the resistor R3, and the other end of which is connected to the electrode nozzle.

[0031] The operating voltage frequency range of the broadband ignition device is 0~1GHz.

[0032] The transformer T1 is a combined transformer, including an iron core, a locking device 5, a spring 6, and a coil assembly. The coil assembly is wound on the iron core, and the iron core is pressed against the locking device 5 by the spring 6. The iron core includes a silicon steel sheet magnetic core 1, a ferrite magnetic core 2, and an amorphous magnetic core 3. The silicon steel sheet magnetic core 1, the ferrite magnetic core 2, and the amorphous magnetic core 3 are all annular. The silicon steel sheet magnetic core 1 includes two U-shaped silicon steel blocks with opposite openings, and a thermal expansion and contraction element 4 is placed between the two U-shaped silicon steel blocks. The amorphous magnetic core 3 includes two U-shaped amorphous blocks with opposite openings, and a thermal expansion and contraction element 4 is placed between the two U-shaped amorphous blocks.

[0033] In this embodiment, the core is composed of silicon steel sheet core 1, ferrite core 2 and amorphous core 3. The space between the two U-shaped silicon steel blocks and the space between the two U-shaped amorphous blocks is filled with thermally expanding and contracting solid material 4. The three materials are stacked together and fixed externally by springs 6 and locking device 5. The locking device 5 has fixing grooves on both sides for fixing the four springs 6.

[0034] When the input power frequency is below 400Hz, the silicon steel core 1 mainly functions. When the input power frequency is between 400Hz and 10kHz, the overheating caused by magnetic saturation causes the thermal expansion and contraction component 4 to expand, thereby opening the two U-shaped silicon steel blocks and exiting the electromagnetic conversion process. At the same time, the amorphous core 3 starts to work. Similarly, when the input power frequency is greater than 10kHz, the amorphous core 3 stops working, and the ferrite core 2 starts working. Finally, when the input power frequency returns to a low frequency, all the cores of the combined transformer exit magnetic saturation, thereby reducing the temperature. At this time, the thermal expansion and contraction component 4 begins to contract, and the spring 6 presses the opened cores back into place.

[0035] The voltage multiplier rectifier circuit consists of voltage multiplier capacitors C1 and C2, rectifier silicon stacks D1 and D2; the energy storage circuit consists of resistor R1 and energy storage capacitor C3; the discharge circuit consists of high-voltage discharge tube G1, resistor R2, and resistor R3, where resistors R2 and R3 provide a protection circuit for energy storage capacitor C3 under no-load conditions; the spark extension circuit consists of inductor L2, which uses the inductance delay effect to delay the duration of the product's output current, thereby extending the spark duration; one end of inductor L2 is connected to high-voltage discharge tube G1, and the other end is connected to the electrode nozzle.

[0036] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A broadband igniter for an aeroengine, characterized in that, The wideband ignition device comprises a voltage conversion circuit, a voltage doubling rectification circuit, an energy storage circuit, a discharge circuit, a spark extension circuit and an electric nozzle connected in sequence. The voltage conversion circuit comprises a choke coil component L1 and a transformer T1, and the choke coil component L1 is connected in series with a primary coil of the transformer T1. The voltage doubling rectification circuit comprises a voltage doubling capacitor C1, a voltage doubling capacitor C2, a rectification silicon stack D1 and a rectification silicon stack D2, the voltage doubling capacitor C1 and the rectification silicon stack D1 connected in series constitute a first branch, the voltage doubling capacitor C2 and the rectification silicon stack D2 connected in series constitute a second branch, and the first branch and the second branch are connected in parallel at both ends of a secondary coil of the transformer T1. The energy storage circuit comprises a resistor R1 and an energy storage capacitor C3 connected in series, and the energy storage circuit is connected in parallel at both ends of the rectification silicon stack D2l. The discharge circuit comprises a high-voltage discharge tube G1, a resistor R2 and a resistor R3, the high-voltage discharge tube G1 and the resistor R3 connected in series constitute a third branch, the resistor R2 and the resistor R3 connected in series constitute a fourth branch, and the third branch and the fourth branch are connected in parallel with the energy storage capacitor C3. The spark extension circuit comprises an inductor L2, one end of the inductor L2 is connected between the high-voltage discharge tube G1 and the resistor R3, and the other end of the inductor L2 is connected with the electric nozzle. The transformer T1 is a combined transformer comprising a core, a locking device (5), a spring (6) and a coil component (7), the coil component (7) is wound on the core, and the core is pressed on the locking device (5) by the spring (6).

2. A broadband igniter for an aeroengine according to claim 1, characterized in that, The working voltage frequency range of the wideband ignition device is 0-1 GHz.

3. A broadband igniter for an aeroengine according to claim 1, characterized in that The core comprises a silicon steel sheet magnetic core (1), a ferrite magnetic core (2) and an amorphous magnetic core (3).

4. A broadband igniter for an aeroengine according to claim 3, characterized in that The silicon steel sheet magnetic core (1), the ferrite magnetic core (2) and the amorphous magnetic core (3) are all annular.

5. A broadband igniter for an aeroengine according to claim 4, characterized in that The silicon steel sheet magnetic core (1) comprises two U-shaped silicon steel blocks with opposite openings, and a thermal expansion and contraction piece (4) is arranged between the two U-shaped silicon steel blocks; the amorphous magnetic core (3) comprises two U-shaped amorphous blocks with opposite openings, and a thermal expansion and contraction piece (4) is arranged between the two U-shaped amorphous blocks.

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