Integrated stable and efficient aero-engine ion flame detector

Abstract

The invention relates to the technical field of aero-engine flame detection equipment, and particularly discloses an integrated stable and efficient aero-engine ion flame detector which comprises a shell, the rear end of the shell is movably connected with a mounting seat, a central guide rod is arranged in the shell, and an insulating mechanism is nested on the central guide rod. One end of the central guide rod is movably connected with an inner detection electrode extending out of the shell, an outer detection electrode which is not in contact with the inner detection electrode is nested outside the inner detection electrode, and one end of the outer detection electrode is buckled with the end part of the shell and abuts against the end part of an insulating mechanism in the shell; meshes for flame ion flow to pass through are uniformly distributed on the surfaces of the inner detection electrode and the outer detection electrode; and the other end of the central guide rod extends into the mounting seat and is electrically connected with the power socket. The detection electrodes are integrated, the current detection stability and efficiency are improved, the influence of the installation position and distance between the detection electrodes is avoided, and the service life is long.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine flame detection equipment, and in particular to an integrated stable and efficient aircraft engine ion flame detector. Background Art

[0002] The ion flame detector is one of the key components in the afterburner ignition system of an aircraft engine. Its function is to sense the flame signal in the afterburner combustion chamber of the engine and send the ion current signal of corresponding intensity to the signal control box to detect whether the afterburner combustion chamber is successfully ignited.

[0003] The ion fire and smoke detector is installed on the shell of the engine afterburner. The flame detector probe goes deep into the flow channel of the afterburner. When the afterburner ignition is successful, the burning oil and gas separate positive and negative ions, and the ion flow forms a loop between the positive and negative poles of the flame detector. When the loop current reaches a certain value, the signal controller transmits the flame control signal to the engine.

[0004] At present, traditional integrated ion flame detectors for aircraft engines mostly use a single detection electrode, such as Figure 1 As shown, when the engine is ignited, the flame ions conduct between the first detection electrode and the engine wall, and the current signal between them is collected by the signal controller. This method requires adjusting the relative position of the flame between the first detection electrode and the engine wall to ensure that the flame forms a loop between the two. At the same time, this method is greatly affected by the stability of the flame signal, which is easy to cause problems such as inaccurate detection current and false alarm of the boost signal light. In addition to the traditional integrated ion flame detector, there is also a combined ion flame detector with positive and negative pole separation. A second detection electrode is added to the engine wall, and the second detection electrode is connected to the engine wall. The flame ions form a loop with the first detection electrode and the second detection electrode. The combination increases the stability of the conduction loop, but it is still necessary to adjust the relative distance between the first detection electrode and the second detection electrode, and it is necessary to increase the installation position on the engine wall. The first detection electrode and the second detection electrode of the existing aircraft engine ion flame detector mostly use an integrated stainless steel material through pipe, which has a short service life in the high temperature environment of the combustion chamber flame, and there will be problems such as unstable detection current signal caused by unstable flame signal. It is easily affected by the installation position and distance between the detection electrodes, the current detection stability is poor, the efficiency is low, and there are high requirements for engine use and maintenance. Summary of the invention

[0005] In view of the deficiencies in the prior art, an object of the present invention is to provide an integrated, stable and efficient aircraft engine ion flame detector which is not affected by flame signals and has a long service life.

[0006] In order to achieve the above-mentioned purpose, the present invention is implemented through the following technical scheme: an integrated stable and efficient aircraft engine ion flame detector, comprising a shell, a mounting seat is movably connected to the rear end of the shell, a center guide rod is arranged in the shell, an insulating mechanism is nested on the center guide rod, one end of the center guide rod is movably connected to an inner detection electrode extending out of the shell, an outer detection electrode that does not contact the inner detection electrode is nested outside the inner detection electrode, one end of the outer detection electrode is buckled with the end of the shell and abuts against the end of the insulating mechanism in the shell, and mesh holes for flame ion flow to pass through are evenly distributed on the surfaces of the inner detection electrode and the outer detection electrode; a power socket is arranged on the upper part of the mounting seat, and the other end of the center guide rod extends into the mounting seat and is electrically connected to the power socket.

[0007] The working principle of this technical solution is that the outer detection electrode, the mounting seat and the outer shell are connected to the engine wall by bolts to form an outer detection circuit; the inner detection electrode, the central guide rod and the power socket form an inner detection circuit; the outer detection electrodes are connected by a mesh structure to achieve a stable flame ion flow channel to guide the flame flow to the inner detection electrode; the flame ions contact the inner detection electrode through the large mesh of the outer detection electrode, thereby forming a stable conduction circuit. Since the surface of the inner detection electrode has mesh holes, the flame forms a stable ion flow in the middle channel, and part of the flame ion flow can flow back to the outer detection electrode through the mesh holes, enhancing the stability of the detection circuit connection after the flame is generated, and efficiently collecting the flame signal in the detection area. The multiple mesh holes prevent the flame flow from causing local overheating on the surface of the outer detection electrode and the inner detection electrode to cause thermal expansion and cracking.

[0008] In order to better implement the present invention, further, the mesh aperture of the inner detection electrode is smaller than the mesh aperture of the outer detection electrode.

[0009] In order to better implement the present invention, further, the mesh aperture of the inner detection electrode is half of the mesh aperture of the outer detection electrode.

[0010] In order to better realize the present invention, further, the insulating mechanism includes a porcelain tube placed in the outer shell and an insulating part fixedly installed in the mounting seat, a spring nested on the center guide rod is arranged between the porcelain tube and the insulating part, one end of the porcelain tube abuts against the end of the external detection electrode, and the other end abuts against the spring; one end of the spring abuts against the porcelain tube, and the other end abuts against the insulating part, and the center guide rod is fixed to the mounting seat and the inside of the outer shell through the insulating part.

[0011] In order to better implement the present invention, further, a gasket is provided between the spring and the porcelain tube, and between the spring and the insulating member.

[0012] In order to better implement the present invention, further, a rear cover that can be opened is provided on the side of the mounting seat, and an opening of the rear cover when opened faces the central guide rod.

[0013] In order to better implement the present invention, further, the material of the external detection electrode is silicon carbide semiconductor material.

[0014] In order to better implement the present invention, further, the material of the inner detection electrode is high temperature alloy steel.

[0015] Compared with the prior art, the present invention has the following advantages and beneficial effects: (1) The present invention integrates the detection electrodes together in a nested manner, thereby avoiding the problem of unstable detection current signal caused by unstable flame signal, and realizing large-scale flame detection in the combustion chamber. A stable flame ion circuit can be formed between the two, thereby improving the stability and efficiency of current detection; (2) The present invention uses an external detection electrode and an internal detection electrode with a differential mesh structure to detect the flame in the combustion chamber, which is not affected by the relative distance and installation position between the external detection electrode and the internal detection electrode, thereby improving the assemblability of the product; (3) By optimizing the materials of the outer detection electrode and the inner detection electrode, the present invention can increase the service life of the ion flame detector, improve the reliability of the engine, reduce the number of maintenance times during the service life of the engine, and reduce the maintenance cost, which is suitable for wide promotion and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments with reference to the following drawings: Figure 1 The schematic diagram of the structure of the ion flame detector of the existing aircraft engine is as follows; Figure 2 It is a schematic diagram of the cross-sectional structure of the present invention; Figure 3 It is a schematic diagram of an enlarged cross section of part of the structure of the present invention.

[0017] Among them: 1 - shell, 2 - mounting base, 3 - center guide rod, 4 - inner detection electrode, 5 - outer detection electrode, 6 - power socket, 7 - porcelain tube, 8 - insulating part, 9 - spring, 10 - gasket, 11 - back cover. DETAILED DESCRIPTION

[0018] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0019] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, it is limited that "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance or implicitly including one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0020] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] Embodiment 1: The main structure of this embodiment is as follows: Figure 2 As shown, it includes a shell 1, and the rear end of the shell 1 is movably connected to a mounting seat 2, a center guide rod 3 is arranged in the shell 1, and an insulating mechanism is nested on the center guide rod 3, one end of the center guide rod 3 is movably connected to an inner detection electrode 4 extending out of the shell 1, and an outer detection electrode 5 that does not contact the inner detection electrode 4 is nested outside the inner detection electrode 4, one end of the outer detection electrode 5 is buckled with the end of the shell 1, and abuts against the end of the insulating mechanism in the shell 1, and mesh holes for flame ion flow to pass through are evenly distributed on the surfaces of the inner detection electrode 4 and the outer detection electrode 5; a power socket 6 is arranged on the upper part of the mounting seat 2, and the other end of the center guide rod 3 extends into the mounting seat 2 and is electrically connected to the power socket 6.

[0022] The specific implementation method is that the external detection electrode 5, the mounting base 2 and the outer shell 1 are connected to the engine wall by bolts to form an external detection circuit; the internal detection electrode 4, the center guide rod 3, and the power socket 6 form an internal detection circuit; the center conductor 3 is welded to the insulating structure by circular laser welding, and is connected to the internal detection electrode 4 by threads; the external detection electrode 5 is fixed by pressing the porcelain tube 7 with a spring 9.

[0023] The ion flame generated by the aircraft engine flows from the mesh on the surface of the outer detection electrode 5 to the inner detection electrode 4. The flame ions contact the inner detection electrode 4 through the mesh of the outer detection electrode 5, and then flow back to the outer detection electrode 5 through the mesh of the inner detection electrode 4, thereby forming a stable conduction circuit, thereby realizing the detection process of the ion flame.

[0024] Embodiment 2: Based on the above embodiments, this embodiment further defines the mesh aperture relationship between the inner detection electrode 4 and the outer detection electrode 5, such as Figure 3 As shown, the mesh aperture of the inner detection electrode 4 is smaller than the mesh aperture of the outer detection electrode 5. The outer detection electrodes 5 are provided with a differential mesh structure to realize a stable flame ion flow channel. The outer detection electrode 5 is provided with large meshes evenly distributed on the surface of the flame detection area to guide the flame flow to the inner detection electrode 4; the inner detection electrode 4 is provided with small meshes evenly distributed on the surface of the flame detection area, and the flame ions contact the inner detection electrode 4 through the large mesh of the outer detection electrode 5, thereby forming a stable conduction loop. Since the mesh size on the surface of the inner detection electrode 4 is very small, the flame forms a stable ion flow in the middle channel, and part of the ion flow can flow back to the outer detection electrode 4 through the small mesh, thereby enhancing the stability of the detection loop connection after the flame is generated, efficiently collecting the flame signal in the detection area, and the multiple meshes prevent the flame flow from generating local overheating and thermal expansion cracking on the surface of the outer detection electrode 5 and the inner detection electrode 4. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0025] Embodiment 3: Based on the above embodiments, this embodiment further defines the mesh aperture relationship between the inner detection electrode 4 and the outer detection electrode 5, such as Figure 3 As shown, the mesh aperture of the inner detection electrode 4 is half of the mesh aperture of the outer detection electrode 5. After actual use tests, it is preferred that the mesh aperture of the inner detection electrode 4 is half of the mesh aperture of the outer detection electrode 5, so that when the flame ions contact the inner detection electrode 4 through the large mesh of the outer detection electrode 3, they can flow back to the outer detection electrode 3 through the small mesh, thereby forming a stable conduction loop and avoiding the phenomenon of local overheating. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0026] Embodiment 4: Based on the above embodiments, this embodiment further defines the structure of the insulation mechanism, such as Figure 2As shown, the insulating mechanism includes a porcelain tube 7 placed in the housing 1, an insulating member 8 fixedly installed in the mounting seat 2, a spring 9 nested on the center guide rod 3 is arranged between the porcelain tube 7 and the insulating member 8, one end of the porcelain tube 7 abuts against the end of the external detection electrode 5, and the other end abuts against the spring 9; one end of the spring 9 abuts against the porcelain tube 7, and the other end abuts against the insulating member 8, and the center guide rod 3 is fixed to the mounting seat 2 and the inside of the housing 1 through the insulating member 8. The insulating member 8 is fixedly installed in the mounting seat 2, and can be used to fix the center guide rod 3 inserted inside it, and the porcelain tube 7 and the external detection electrode 5 are pressed by the spring 9 to achieve the fixation of the two. The insulating mechanism is arranged in this way, so that the insulating mechanism contacts the external detection electrode 5, and the rigid abutment is changed to elastic abutment, so that the external detection electrode 5 is abutted and fixed under the premise of ensuring insulation. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0027] Embodiment 5: Based on the above embodiments, this embodiment further defines the structure of the insulation mechanism, such as Figure 2 As shown, a gasket 10 is further provided between the spring 9 and the porcelain tube 7, and between the spring 9 and the insulating member 8. The function of the gasket 10 is to protect the porcelain tube 7 and the insulating member 8, and to prevent the porcelain tube 7 and the insulating member 8 from being damaged by direct contact with the spring 9. The other parts of this embodiment are the same as those of the above embodiment, and will not be described in detail.

[0028] Embodiment 6: Based on the above embodiment, this embodiment further defines the structure of the mounting seat 2, such as Figure 2 As shown, the side of the mounting seat 2 is also provided with an openable rear cover 11, and the opening of the rear cover 11 is opened to face the central guide rod 3. The rear cover 11 is mainly provided to facilitate the installation, removal and maintenance of the insulating member 8, the central guide rod 3 and other structures through the opening of the rear cover 11. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0029] Embodiment 7: Based on the above embodiment, this embodiment further defines the material of the external detection electrode 5, and the material of the external detection electrode 5 is silicon carbide semiconductor material. The external detection electrode 5 is made of silicon carbide semiconductor material to improve the detector's tolerance to external temperature environment, enhance the conductivity under high temperature conditions in the afterburner, and greatly reduce the ablation of the internal detection electrode 4 by the engine flame. The external detection electrode 5 is made of silicon carbide semiconductor material through cutting, grinding, perforation and other processes. After the rear end step surface contacts the outer shell 1 and the porcelain tube 7, it is fixed with a spring 3 to ensure that the contact position of the external detection circuit has good conductivity. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0030] Embodiment 8: Based on the above embodiment, this embodiment further defines the material of the inner detection electrode 4, and the material of the inner detection electrode 4 is high temperature alloy steel. The inner detection electrode 4 is machined from high temperature alloy steel and is threadedly connected to the central guide rod 3 to enhance the service life under high temperature impact. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0031] It can be understood that the working principle and working process of the aircraft engine ion flame detector structure according to an embodiment of the present invention, such as the power socket 6 and the spring 9 and other components are all prior art and are well known to technicians in this field, and will not be described in detail here.

[0032] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. An integrated stable and efficient aircraft engine ion flame detector, characterized in that: The invention comprises a shell (1), wherein the rear end of the shell (1) is movably connected to a mounting seat (2), a central guide rod (3) is arranged inside the shell (1), an insulating mechanism is nested on the central guide rod (3), one end of the central guide rod (3) is movably connected to an inner detection electrode (4) extending out of the shell (1), an outer detection electrode (5) not in contact with the inner detection electrode (4) is nested outside the inner detection electrode (4), one end of the outer detection electrode (5) is buckled with the end of the shell (1) and abuts against the end of the insulating mechanism inside the shell (1), and mesh holes for flame ion flow to pass through are evenly distributed on the surfaces of the inner detection electrode (4) and the outer detection electrode (5); a power socket (6) is arranged on the upper part of the mounting seat (2), and the other end of the central guide rod (3) extends into the mounting seat (2) and is electrically connected to the power socket (6).

2. The integrated stable and efficient aircraft engine ion flame detector according to claim 1 is characterized in that: The mesh aperture of the inner detection electrode (4) is smaller than the mesh aperture of the outer detection electrode (5).

3. The integrated stable and efficient aircraft engine ion flame detector according to claim 2 is characterized in that: The mesh aperture of the inner detection electrode (4) is half the mesh aperture of the outer detection electrode (5).

4. An integrated stable and efficient aircraft engine ion flame detector according to any one of claims 1 to 3, characterized in that: The insulating mechanism comprises a porcelain tube (7) placed in the housing (1) and an insulating member (8) fixedly mounted in the mounting seat (2); a spring (9) nested on the central guide rod (3) is arranged between the porcelain tube (7) and the insulating member (8); one end of the porcelain tube (7) abuts against the end of the external detection electrode (5), and the other end abuts against the spring (9); one end of the spring (9) abuts against the porcelain tube (7), and the other end abuts against the insulating member (8); the central guide rod (3) is fixed to the mounting seat (2) and the inside of the housing (1) through the insulating member (8).

5. The integrated stable and efficient aircraft engine ion flame detector according to claim 4, characterized in that: A gasket (10) is also provided between the spring (9) and the porcelain tube (7), and between the spring (9) and the insulating member (8).

6. An integrated stable and efficient aircraft engine ion flame detector according to any one of claims 1 to 3, characterized in that: An openable rear cover (11) is also provided on the side of the mounting seat (2), and the opening of the rear cover (11) when opened faces the central guide rod (3).

7. An integrated stable and efficient aircraft engine ion flame detector according to any one of claims 1 to 3, characterized in that: The material of the external detection electrode (5) is silicon carbide semiconductor material.

8. An integrated stable and efficient aircraft engine ion flame detector according to any one of claims 1 to 3, characterized in that: The material of the inner detection electrode (4) is high-temperature alloy steel.

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