Aerospace high-temperature-resistant ion flame detector reducer probe structure

Abstract

The application belongs to the field of flame detector structure design, and particularly relates to a variable-diameter probe structure of an aviation high-temperature-resistant ion flame detector. The structure comprises a cooling air inlet pipe (1) which comprises a large-diameter section (11), a small-diameter section (12) and a variable-diameter section (13) between the large-diameter section (11) and the small-diameter section (12), wherein the variable-diameter section (13) is provided with cooling air inlet holes (14); a probe head (2) is arranged at the end of the small-diameter section (12) of the cooling air inlet pipe (1), the probe head (2) is a hollow cone structure, the apex of the cone is provided with a spherical surface, and a plurality of small holes (21) are arranged on the probe head (2). The application improves the cooling effect of the cooling air flow on the probe of the ion flame detector, reduces the ablation influence of the hot air flow on the probe of the ion flame detector, and further improves the high-temperature resistance of the ion flame detector.

Description

Technical Field

[0001] This application belongs to the field of flame detector structural design, specifically relating to a variable diameter probe structure for an aerospace high-temperature ion flame detector. Background Technology

[0002] An ionization flame detector mainly consists of a probe, an insulator, a busbar housing, and a socket. Its principle is as follows: The ionization flame detector detects the presence of a flame by utilizing the conductivity effect of fuel combustion products. It uses two electrodes: the probe as the positive electrode and the busbar housing as the negative electrode. The two electrodes are physically insulated from each other by an insulator, and under normal conditions, they are insulated from each other. When an alternating current is applied between the two electrodes, in the absence of a flame, the medium (air) between the electrodes is insulated, and the current in the detection circuit is leakage current; when a flame is present, the medium (a mixture of air and fuel) between the two electrodes is conductive, and the current in the detection circuit is ion current. Therefore, the presence of a flame in the probe area can be determined by the magnitude of the current in the detection circuit.

[0003] Because the probe is exposed to the high temperature of the flame for a long time, especially since the probe end is an open structure, the probe end often suffers from ablation and deformation. The ablation of the probe end of the ion flame detector poses a certain safety hazard to the normal operation of the engine. Summary of the Invention

[0004] To address the aforementioned problems, this application provides a variable-diameter probe structure for an airborne high-temperature ion flame detector, mainly comprising:

[0005] A cooling intake pipe includes a large-diameter section, a small-diameter section, and a variable-diameter section located between the large-diameter section and the small-diameter section, wherein a cooling intake hole is provided on the variable-diameter section.

[0006] The probe is located at the end of the small-diameter section of the cooling intake pipe. The probe has a hollow cone structure with the apex of the cone set as a spherical surface. Several small holes are provided on the probe head.

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

[0008] Preferably, the variable diameter section has a funnel structure with a maximum variable diameter ratio of 2.

[0009] Preferably, the cooling air inlet is a strip-shaped hole, with the long side of the strip-shaped hole extending along the axial direction of the cooling air inlet pipe.

[0010] Preferably, the cooling air inlet includes multiple cooling air inlets, which are arranged circumferentially along the variable diameter section.

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

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

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

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

[0015] This application improves the cooling effect of the cooling airflow on the probe of the ion flame detector, reduces the erosion effect of the hot airflow on the probe of the ion flame detector, and thus improves the high temperature resistance of the ion flame detector. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of a preferred embodiment of the variable diameter probe structure of the high-temperature ion flame detector for aviation applications.

[0017] Figure 2 yes Figure 1 A schematic diagram of the cooling intake pipe structure in the embodiment shown.

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

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

[0020] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0021] This application provides a variable diameter probe structure for an airborne high-temperature ion flame detector, such as... Figures 1-3 As shown, it mainly includes:

[0022] Cooling intake pipe 1 includes a large diameter section 11, a small diameter section 12, and a variable diameter section 13 located between the large diameter section 11 and the small diameter section 12. Cooling intake hole 14 is provided on the variable diameter section 13.

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

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

[0025] The cooling inlet pipe 1 of this application is designed with a three-section structure, namely 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 has a funnel structure with a maximum diameter ratio of 2. For example, the diameter of the large-diameter section 11 is 18mm, the diameter of the small-diameter section 12 is 9mm, and the wall thickness of all three sections is uniformly 1.5mm. A cooling inlet hole 14 is designed in the middle of the variable-diameter section 13. In some optional embodiments, the cooling inlet hole 14 is a strip-shaped hole, with its long side extending axially along the cooling inlet pipe 1, such as... Figure 2 As shown, the cooling inlet 14 has a length of 20mm and a width of 7mm. The most distinctive feature of this structure is the design of the variable diameter section 13, which is shaped like a funnel. The cold air flows in through the cooling inlet 14. Due to the presence of the conical surface of the variable diameter section 13, the cold air flows to the small diameter section 12 at a faster speed and with a greater flow rate, which is to the probe 2 located in the hot flow region. This is more conducive to consuming the energy of the hot flow and reducing the erosion of the probe tube by the hot flow.

[0026] The probe 2 is designed in a shape similar to a "bullet head." In some optional embodiments, the cone of the probe 2 has a taper of 45°. Multiple φ1.5mm holes, for example, eight holes, are designed on the conical surface, and the apex of the cone is SR3mm. The most significant feature of this structure lies in the design of the small holes on the conical surface and the spherical design of the apex. First, compared to the existing technology with an opening on the left side of the cooling intake pipe 1, this application adds a probe with small holes at the left end of the cooling intake pipe 1. These small holes can significantly prevent excessive cold flow into the engine flame zone and also prevent excessive heat flow into the probe. This means that more cold flow remains inside the probe, and correspondingly less heat flow, greatly ensuring the cooling effect of the cold flow on the probe. Second, the spherical design of the apex of the cone, with its smooth, curved outer surface, increases the flow velocity according to Bernoulli's principle. Therefore, when heat flows over the outer surface of the probe, the flow velocity is faster, and the time the heat flow affects the probe is shorter, thus reducing the burning time of the probe.

[0027] In some alternative embodiments, the cooling air inlet 14 includes a plurality of cooling air inlets 14 arranged circumferentially along the variable diameter section 13.

[0028] In this embodiment, multiple cooling air inlets 14 can be provided, and the multiple cooling air inlets are arranged circumferentially along the variable diameter section 13, so that cold air can be introduced into the cooling air inlet pipe 1 from various directions. In an alternative embodiment, one or more cooling air inlets 14 can also be provided on the windward side.

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

[0030] In this embodiment, the material has a maximum temperature resistance of approximately 1100°C and a melting temperature of approximately 1300°C. The probe and cooling intake pipe are made of the same material, which is more conducive to welding.

[0031] In some alternative implementations, refer to Figure 3 The small hole 21 is formed on the side of the probe 2 facing the flame. In this embodiment, the cooling airflow is mainly used to cool the side of the probe 2 facing the flame, so the small hole is mainly formed on this side to enhance the cooling effect of the structure.

[0032] This application utilizes a conical design within the cooling inlet pipe 1 to allow cold air to flow more quickly and abundantly to the probe's hot air region. Small holes on the probe 2 allow more cold air to remain inside the probe tube, reducing the amount of hot air entering. The arc-shaped apex of the conical surface of the probe 2 further facilitates faster flow of hot air across its surface. In summary, this application addresses the probe tube erosion issue in ion flame detectors and improves the probe tube's high-temperature resistance.

[0033] Although this application has been described in detail above with general descriptions and specific embodiments, some modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, such modifications or improvements made without departing from the spirit of this application are all within the scope of protection claimed in this application.

Claims

1. A variable diameter probe structure for an aerospace high-temperature ion flame detector, characterized in that, include: The cooling intake pipe (1) includes a large diameter section (11), a small diameter section (12) and a variable diameter section (13) located between the large diameter section (11) and the small diameter section (12), and the variable diameter section (13) is provided with a cooling intake hole (14). The probe (2) is set at the end of the small diameter section (12) of the cooling air inlet pipe (1). The probe (2) is a hollow cone structure with the top of the cone set as a spherical surface. Several small holes (21) are provided on the probe (2). The probe (2) is located in the flame zone, the cooling air inlet pipe (1) is located outside the flame zone, and the cooling air enters the cooling air inlet pipe (1) through the cooling air inlet hole (14) outside the flame zone.

2. The variable diameter probe structure of the aerospace high-temperature ion flame detector as described in claim 1, characterized in that, The variable diameter section (13) has a funnel structure with a maximum diameter ratio of 2.

3. The variable diameter probe structure of the aerospace high-temperature ion flame detector as described in claim 1, characterized in that, The cooling air inlet (14) is a strip-shaped hole, with the long side of the strip-shaped hole extending along the axial direction of the cooling air inlet pipe (1).

4. The variable diameter probe structure of the aerospace high-temperature ion flame detector as described in claim 3, characterized in that, The cooling air inlet (14) includes multiple cooling air inlets (14) arranged circumferentially along the variable diameter section (13).

5. The variable diameter probe structure of the aerospace high-temperature ion flame detector as described in claim 1, characterized in that, Both the cooling air intake pipe (1) and the probe (2) are made of GH3044 high-temperature alloy.

6. The variable diameter probe structure of the aerospace high-temperature ion flame detector as described in 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 structure of the aerospace high-temperature ion flame detector as described in claim 1, characterized in that, A small hole (21) is made on the side of the probe (2) facing the windward side of the flame.

8. The variable diameter probe structure of the aerospace high-temperature ion flame detector as described in claim 1, characterized in that, The cone of the probe (2) has a taper of 45°.

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