Reducing exploring tube structure of aviation high-temperature-resistant ion flame detector

Abstract

The invention belongs to the field of flame detector structure design, and particularly relates to a reducing probe structure of an aviation high-temperature-resistant ion flame detector. The structure comprises a cooling air inlet pipe (1), the cooling air inlet pipe (1) comprises a large-drift-diameter section (11), a small-drift-diameter section (12) and a reducing section (13) located between the large-drift-diameter section (11) and the small-drift-diameter section (12), and a cooling air inlet hole (14) is formed in the reducing section (13); the probe (2) is arranged at the end part of the small-drift-diameter section (12) of the cooling air inlet pipe (1), the probe (2) is of a hollow cone structure, the vertex of the cone is a spherical surface, and a plurality of small holes (21) are formed in the head (2). The cooling effect of the cooling airflow on the ion flame detector probe tube is improved, the ablation influence of the hot airflow on the ion flame detector probe tube is reduced, and the high temperature resistance of the ion flame detector is further improved.

Description

Technical Field

[0001] The present application belongs to the field of flame detector structure design, and specifically relates to a variable diameter probe tube structure of an aviation high temperature resistant ion flame detector. Background Art

[0002] The ion flame detector is mainly composed of a probe tube, an insulator, a conduit shell, a socket, etc. The principle is as follows: the ion flame detector can detect the presence of flames by utilizing the conductive effect of fuel combustion products. It uses two electrodes, the probe tube as the positive electrode and the conduit shell as the negative electrode. The two electrodes are physically insulated by an insulator, and the two electrodes are insulated in the natural state. When alternating current is applied between the two electrodes, the medium (air) between the two electrodes is insulated when there is no flame, and the current in the detection circuit is leakage current; when there is a flame, the medium (air and fuel mixture) between the two electrodes is in a conductive state, and the current in the detection circuit is an ion current. Therefore, the size of the current in the detection circuit can be used to determine whether there is a flame in the probe area.

[0003] Since the probe is in the high temperature area of ​​the flame for a long time, especially the end of the probe is an open structure, the end of the probe is often ablated and deformed. The ablation of the probe end of the ion flame detector brings certain safety hazards to the normal operation of the engine. Summary of the invention

[0004] In order to solve the above problems, the present application provides a variable diameter probe tube structure of an aviation high temperature resistant ion flame detector, which mainly includes:

[0005] A cooling air intake pipe, comprising a large diameter section, a small diameter section and a variable diameter section between the large diameter section and the small diameter section, wherein the variable diameter section is provided with a cooling air intake hole;

[0006] The probe is arranged at the end of the small diameter section of the cooling air intake pipe, the probe is a hollow cone structure, the apex of the cone is set as a spherical surface, and a plurality of small holes are set on the head;

[0007] The probe is located in the flame zone, the cooling air intake pipe is located outside the flame zone, and the cooling air enters the cooling air intake pipe from the cooling air intake hole outside the flame zone.

[0008] Preferably, the diameter-changing section is a funnel structure, and the maximum diameter-changing ratio is 2.

[0009] Preferably, the cooling air inlet hole is a strip hole, and the long side of the strip hole extends along the axial direction of the cooling air inlet pipe.

[0010] Preferably, the cooling air inlet holes include a plurality of cooling air inlet holes, and the plurality of cooling air inlet holes are arranged circumferentially along the diameter-changing section.

[0011] Preferably, the cooling air intake pipe and the probe are both made of GH3044 high temperature alloy.

[0012] Preferably, the probe is welded to the end of the cooling air intake pipe.

[0013] Preferably, the small hole is provided on a side of the probe facing the windward side of the flame.

[0014] Preferably, the cone angle of the probe is 45°.

[0015] The present application improves the cooling effect of the cooling airflow on the ion flame detector probe tube, reduces the ablation effect of the hot airflow on the ion flame detector probe tube, and thus improves the high temperature resistance of the ion flame detector. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of a preferred embodiment of the variable diameter probe tube structure of the aviation high temperature resistant ion flame detector of the present application.

[0017] Figure 2 yes Figure 1 Schematic diagram of the cooling air intake pipe structure of the illustrated embodiment.

[0018] Figure 3 yes Figure 1 A schematic diagram of the probe structure of the illustrated embodiment.

[0019] Among them, 1-cooling air inlet pipe, 11-large diameter section, 12-small diameter section, 13-variable diameter section, 14-cooling air inlet hole, 2-probe, 21-small hole. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0021] The present application provides a variable diameter probe tube structure of an aviation high temperature resistant ion flame detector, such as Figure 1-Figure 3 As shown, it mainly includes:

[0022] The cooling air intake pipe 1 comprises a large diameter section 11, a small diameter section 12 and a diameter reducing section 13 between the large diameter section 11 and the small diameter section 12, wherein the diameter reducing section 13 is provided with a cooling air intake hole 14;

[0023] The probe 2 is arranged at the end of the small diameter section 12 of the cooling air intake pipe 1. The probe 2 is a hollow cone structure, the top of the cone is set as a spherical surface, and a plurality of small holes 21 are set on the head 2;

[0024] Among them, the probe 2 is located in the flame zone, and the cooling air intake pipe 1 is located outside the flame zone. The cooling gas is outside the flame zone and is generally physically isolated from the probe 2. After the cooling gas enters the cooling air intake pipe 1 through the cooling air intake hole 14, it flows to both sides. Due to the existence of the variable diameter section 13, it mainly flows to the small diameter section 12, thereby blocking the heat and preventing the ablation damage to some non-heat-resistant parts in the large diameter section 11.

[0025] The cooling air intake pipe 1 of the present application is designed as a three-section structure, and the three sections are respectively a large diameter section 11, a variable diameter section 13, and a small diameter section 12. In some optional embodiments, the variable diameter section 13 is a funnel structure with a maximum variable diameter ratio of 2. For example, the large diameter section 11 has a diameter of 18 mm, the small diameter section 12 has a diameter of 9 mm, and the three sections have a uniform wall thickness of 1.5 mm. A cooling air intake hole 14 is designed in the middle of the variable diameter section 13. In some optional embodiments, the cooling air intake hole 14 is a strip hole, and the long side of the strip hole extends along the axial direction of the cooling air intake pipe 1, such as Figure 2 As shown, the cooling air inlet 14 is 20 mm long and 7 mm wide. The biggest feature of this structure is the design of the variable diameter section 13. The variable diameter section 13 is similar to the shape of a "funnel". The cold flow flows in from the cooling air inlet 14. Due to the presence of the conical surface of the variable diameter section 13, the cold flow will flow to the small diameter section 12 at a faster speed and more flow, that is, to the probe 2 located in the hot flow area, which is more conducive to consuming the energy of the hot flow and reducing the ablation of the probe tube by the hot flow.

[0026] The probe 2 is designed to be similar to a "bullet head". In some optional embodiments, the cone taper of the probe 2 is 45°. There are multiple φ1.5mm small holes designed on the conical surface, for example, 8 small holes, and the cone vertex is SR3mm. The biggest feature of this structure is the design of the small holes on the conical surface and the spherical design of the cone vertex. First, compared with the opening on the left side of the cooling intake pipe 1 in the prior art, the present application adds a probe with a small hole at the left end of the cooling intake pipe 1. With the help of the small hole, it can prevent the excessive cold flow from flowing into the engine flame zone to a large extent, and prevent the excessive flame heat flow from flowing into the probe tube. That is, the cold flow will be more inside the probe tube, and the corresponding heat flow will be less, which greatly ensures the cooling effect of the cold flow on the probe tube. Second, the spherical design of the cone vertex, the outer surface of the sphere is a smooth arc shape. According to Bernoulli's principle, when the fluid flows through the arc surface, the flow rate increases. Therefore, when the heat flow flows through the outer surface of the probe, the flow rate will be faster, and the influence time of the heat flow on the probe will be shorter, that is, the burning time of the heat flow on the probe is reduced.

[0027] In some optional embodiments, the cooling air inlet hole 14 includes a plurality of cooling air inlet holes 14 , and the plurality of cooling air inlet holes 14 are arranged circumferentially along the diameter-changing section 13 .

[0028] In this embodiment, a plurality of cooling air inlet holes 14 may be provided, and the plurality of cooling air inlet holes are arranged circumferentially along the variable diameter section 13, so that the cold flow can be introduced into the cooling air inlet pipe 1 from all directions. In an alternative embodiment, one or more cooling air inlet holes 14 may also be provided on the windward surface.

[0029] In some optional implementations, the cooling air intake pipe 1 and the probe 2 are both made of GH3044 high-temperature alloy, and the probe 2 is welded to the end of the cooling air intake pipe 1 .

[0030] In this embodiment, the maximum temperature resistance of the material can reach about 1100° C., and the melting temperature is about 1300° C. The probe is consistent with the cooling air intake pipe material, which is more conducive to welding.

[0031] In some optional embodiments, reference Figure 3 The small hole 21 is provided on the side of the probe 2 facing the windward side of the flame. In this embodiment, the cooling airflow is mainly used to cool the side of the probe 2 facing the windward side of the flame, so the small holes are mainly provided on this side to enhance the cooling effect of the structure.

[0032] The present application uses a conical surface design of the inner cavity of the cooling inlet pipe 1 to allow the cold flow to flow faster and more to the hot flow area of ​​the probe; a small hole is opened on the probe 2 to allow more cold flow to remain inside the probe tube and less hot flow to enter the probe tube; the top of the conical surface of the probe 2 is an arc shape, allowing the hot flow to flow faster through the surface of the probe 2. In summary, the present application solves the ablation problem of the probe tube of the ion flame detector and improves the high temperature resistance of the probe tube.

[0033] Although the present application has been described in detail above with general descriptions and specific implementation schemes, it is obvious to those skilled in the art that some modifications or improvements may be made to the present application. Therefore, these modifications or improvements made without departing from the spirit of the present application all fall within the scope of protection claimed in the present application.

Claims

1. A variable diameter probe tube structure for aviation high temperature resistant ion flame detector, characterized in that: include: A cooling air intake pipe (1), comprising a large diameter section (11), a small diameter section (12), and a diameter-reducing section (13) located between the large diameter section (11) and the small diameter section (12), wherein a cooling air intake hole (14) is provided on the diameter-reducing section (13); The probe (2) is arranged at the end of the small diameter section (12) of the cooling air intake pipe (1), the probe (2) is a hollow cone structure, the apex of the cone is set as a spherical surface, and a plurality of small holes (21) are arranged on the head (2); The probe (2) is located in the flame zone, the cooling air intake pipe (1) is located outside the flame zone, and the cooling air enters the cooling air intake pipe (1) from the cooling air intake hole (14) outside the flame zone.

2. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 1 is characterized in that: The diameter-changing section (13) is a funnel structure, and the maximum diameter-changing ratio is 2.

3. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 1 is characterized in that: The cooling air inlet hole (14) is a strip-shaped hole, and the long side of the strip-shaped hole extends along the axial direction of the cooling air inlet pipe (1).

4. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 3 is characterized in that: The cooling air inlet holes (14) include a plurality of cooling air inlet holes (14), which are arranged circumferentially along the diameter-changing section (13).

5. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 1 is characterized in that: The cooling air intake pipe (1) and the probe (2) are both made of GH3044 high-temperature alloy.

6. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 1, characterized in that: The probe (2) is welded to the end of the cooling air intake pipe (1).

7. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 1, characterized in that: The small hole (21) is provided on the side of the probe (2) facing the windward side of the flame.

8. The variable diameter probe tube structure of the aviation high temperature resistant ion flame detector according to claim 1, characterized in that: The cone angle of the probe (2) is 45°.

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