Aerial ignition electrode

Abstract

The present application belongs to the technical field of ion flame detector assembly. Specifically relates to an aviation ignition electrode. It includes: first shell (1), second shell (2), third shell (3), first porcelain (4), second porcelain (5), locking contact (6), center electrode (7), rubber sleeve (8), sealing glass (10), the lower end of the first shell (1) is welded with the second shell (2); the upper end of the second shell (2) is mechanically closed with the lower end of the third shell (3); the first porcelain (4) is arranged in the first shell (1) and the second shell (2); the lower end of the second porcelain (5) is sleeved on the outer side of the upper end of the first porcelain (4); the center electrode (7) is arranged in the first porcelain (4) and the second porcelain (5); the rubber sleeve (8) is arranged between the locking contact (6) and the inner wall of the second porcelain (5); the second shell (2) and the second porcelain (5) are sealed by the sealing glass (10).

Description

Technical Field

[0001] This invention belongs to the field of ion flame detector assembly technology. Specifically, it relates to an aviation ignition nozzle. Background Technology

[0002] The aviation ignition nozzle, along with the aviation ignition cable and aviation ignition device, constitutes the aviation ignition system. On the engine or auxiliary power unit, it plays the role of converting the high-voltage pulse electricity transmitted from the aviation ignition cable and generated by the aviation ignition device into an electric spark, thereby igniting the fuel-air mixture in the combustion chamber.

[0003] When the fuel-air mixture is ignited, high-temperature, high-pressure gas is generated in the combustion chamber, which constantly impacts the aviation ignition nozzle. Under this condition, the aviation ignition nozzle is required to have good airtightness in addition to fulfilling its ignition function, in order to prevent the high-temperature, high-pressure gas in the combustion chamber from leaking back through the nozzle, thereby burning the aviation ignition cable or other aviation components.

[0004] Currently, most aviation ignition nozzle sealing modules adopt a straight-cylinder glass sealing structure and process, which mainly has the following risks and failure modes: ① After glass sealing, the first-pass airtightness of the product is low; ② Low resistance to temperature shock, the glass sealing area is prone to failure and leakage when subjected to temperature shock environment or welding operations near the sealing module; ③ Low vibration resistance, the glass sealing area is prone to failure and leakage when the product is subjected to large vibration loads; ④ When the product is installed and locked, the glass sealing area is prone to failure and leakage when the product is subjected to torsion and compression.

[0005] Once a product leaks air, it is considered a defective product. Rework and repair costs are high, and the quality stability is poor. Therefore, there is an urgent need to invent an aviation ignition nozzle with a stepped segmented sealing structure to eliminate the many risks, hidden dangers, and failure modes of ordinary straight-tube glass sealing structures. Summary of the Invention

[0006] Purpose of the invention: To provide an aviation ignition nozzle with improved sealing performance.

[0007] Technical solution:

[0008] An aviation ignition nozzle includes: a first housing 1, a second housing 2, a third housing 3, a first ceramic component 4, a second ceramic component 5, a locking contact 6, a center electrode 7, a rubber sleeve 8, and a sealing glass 10.

[0009] The first housing 1 is welded to the lower end of the second housing 2; the upper end of the second housing 2 is mechanically closed to the lower end of the third housing 3; the first ceramic component 4 is disposed inside the first housing 1 and the second housing 2; the second ceramic component 5 is located inside the second housing 2 and the third housing 3, and the lower end of the second ceramic component 5 is fitted outside the upper end of the first ceramic component 4; an annular boss is provided on the outer side of the central electrode 7, the central electrode 7 is disposed inside the first ceramic component 4 and the second ceramic component 5, and the lower end face of the central electrode 7 boss contacts the upper end face of the second ceramic component 5; a rubber sleeve 8 is disposed between the locking contact 6 and the inner wall of the second ceramic component 5; the internal thread at the lower end of the locking contact 6 cooperates with the external thread at the upper end of the central electrode 7 to press the rubber sleeve 8; the second housing 2 and the second ceramic component 5 are sealed by a sealing glass 10.

[0010] Furthermore, an organic sealant 14 is provided between the inner wall of the second ceramic part 5 and the lower end of the locking contact 6, and between the second ceramic part 5 and the upper part of the protrusion of the center electrode 7.

[0011] Furthermore, a sealing gasket 15 is provided between the upper edge of the protrusion of the central electrode 7 and the inner wall of the second ceramic part 5.

[0012] Furthermore, the first ceramic component 4 and the first housing 1 are sealed with inorganic sealant 9, and the upper end of the first housing 1 is mechanically closed.

[0013] Furthermore, the inner wall of the second housing 2 and the outer wall of the second ceramic component 5 are provided with threads or serrated grooves.

[0014] Furthermore, an overflow cavity 11 and an annular gap of 0.1-0.5mm are provided between the inner wall of the upper end of the second housing 2 and the outer wall of the second ceramic part 5, so that the sealing glass 10 melts and overflows upward from the annular gap to the overflow cavity 11.

[0015] Furthermore, a sealing ring 12 is provided between the lower end face of the third housing 3 and the contact surface of the second ceramic part 5.

[0016] Furthermore, a sealing gasket 13 is provided between the upper end of the second housing 2 and the contact surface of the third housing 3.

[0017] Beneficial effects:

[0018] By providing threads or serrated grooves on the inner wall of the second housing 2 and the outer wall of the second ceramic component 5, and setting up an air passage labyrinth structure, the sealing area between the sealing glass 10 and the second housing 2 and the second ceramic component 5 can be increased, and the bonding force of the sealing area under temperature shock and mechanical external loads can be resisted, thus comprehensively improving the glass sealing performance of the product. In addition, the sealing glass 10 can fix the second ceramic component 5. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of an aviation ignition nozzle according to an embodiment of the present invention;

[0020] The components include: first housing 1, second housing 2, third housing 3, first ceramic component 4, second ceramic component 5, second ceramic component 6, locking contact 6, center electrode 7, rubber sleeve 8, inorganic sealant 9, sealing glass 10, overflow cavity 11, sealing ring 12, sealing pad 13, organic sealant 14, and sealing gasket 15. Detailed Implementation

[0021] 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 inventive 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.

[0022] In the description of this invention, it should be understood that the terms "center", "axial", "vertical", "upper", "lower", "upper end", "bottom end", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this invention.

[0023] The aviation ignition nozzle of the present invention is used to achieve the sealing of the aviation ignition nozzle, ensure the airtightness of the product, and thus withstand the high temperature and high pressure conditions of aviation engines.

[0024] This invention provides a sealing structure and process method for aviation ignition nozzles, used to achieve sealing of aviation ignition nozzles, ensuring product airtightness, and thus withstanding the high temperature and high pressure conditions of aero-engines. The aviation ignition nozzle sealing structure includes an external sealing channel and an internal sealing channel. The external sealing channel is characterized by being composed of four sealing structures, which are connected by welding, sealing, and closing. The four sealing structures are designed with different sealing forms and processes according to different temperature tolerance zones, including an inorganic adhesive potting and closing sealing structure, a threaded cavity plus overflow cavity glass sealing structure, a sealing ring pressing sealing structure, and a sealing gasket closing sealing structure. The internal sealing channel is characterized by potting organic adhesive into the cavity, followed by a threaded tightening process that compresses and deforms the rubber block. The organic adhesive sealing and the rubber compression deformation together achieve the internal channel seal. This application realizes a graded sealing process for aviation ignition nozzle products, ensuring the high airtightness requirements of the product under high temperature and high pressure conditions.

[0025] like Figure 1 The aviation ignition nozzle of the present invention includes an external sealing channel and an internal sealing channel. The external sealing channel includes a first ceramic component 4, a first housing 1, an inorganic sealant 9, a second housing 2, a sealing glass 10, a second ceramic component 5, a third housing 3, an overflow cavity 11, a sealing ring 12, and a sealing gasket 13. The cavity formed by the first ceramic component 4 and the first housing 1 is sealed by potting with inorganic sealant; the cavity formed by the second housing 2 and the second ceramic component 5 is sealed by glass sealing; the bottom of the third housing 3 is sealed by pressing the sealing ring 12; a sealing gasket 13 is installed between the second housing 2 and the third housing 3, and the connection, pressing, and sealing of the second housing 2 and the third housing 3 are achieved through a sealing process. The first housing 1 and the second housing 2 are connected by argon arc welding.

[0026] The internal sealing channel includes a first ceramic component 4, a central electrode 7, a second ceramic component 5, a sealing gasket 15, an organic sealant 14, a rubber sleeve 8, and a locking contact 6.

[0027] refer to Figure 1This application discloses a sealing structure and process method for an aviation ignition nozzle, used to achieve sealing of the aviation ignition nozzle, ensuring the product's airtightness, and thus withstanding the high temperature and high pressure conditions of aero-engines. The aviation ignition nozzle sealing structure includes an external sealing channel and an internal sealing channel. The external sealing channel includes a first ceramic component 4, a first housing 1, an inorganic sealant 9, a second housing 2, a sealing glass 10, a second ceramic component 5, a third housing 3, an overflow cavity 11, a sealing ring 12, and a sealing gasket 13. The cavity formed by the first ceramic component 4 and the first housing 1 is sealed by potting with inorganic sealant; the cavity formed by the second housing 2 and the second ceramic component 5 is sealed by glass sealing; the bottom of the third housing 3 is pressed against the sealing ring 12 to achieve sealing; a sealing gasket 13 is installed between the second housing 2 and the third housing 3, and the connection, compression, and sealing of the second housing 2 and the third housing 3 are achieved through a closing process. The first housing 1 and the second housing 2 are connected by argon arc welding. The internal sealing channel includes a first ceramic component 4, a central electrode 7, a second ceramic component 5, a sealing gasket 15, an organic sealant 14, a rubber sleeve 8, and a locking contact 6. The locking contact 6 is connected to the central electrode 7 via internal and external threads. Simultaneously, the sealing gasket 15 is compressed, achieving the first seal of the internal sealing channel. The organic sealant 14 is applied between the inner wall of the second ceramic component 5 and the lower end of the locking contact 6, and between the second ceramic component 5 and the upper part of the protrusion of the central electrode 7, forming the second sealing line of the internal sealing channel. The rubber sleeve 8 is positioned between the locking contact 6 and the inner wall of the second ceramic component 5. When the rubber sleeve 8 is pressed downwards, it deforms, thus forming the third sealing line of the internal sealing channel.

[0028] 1. By filling the space between the first ceramic component 4 and the first housing 1 with inorganic sealant 9, the following effects are achieved: ① forming the first sealing line of the external sealing channel of the product, blocking the reverse leakage of high temperature and high pressure gas; ② ensuring good airtightness under the condition of withstanding the high temperature of the combustion chamber ≈800℃; ③ ensuring good airtightness when welding at the joint between the first housing 1 and the second housing 2 under the condition of withstanding the welding high temperature ≈1000℃; ④ fixing the ceramic component 14.

[0029] 2. By closing the opening at the upper end of the first housing 1, the inorganic sealant 9 of the product is pressed downwards.

[0030] 3. By providing threaded or serrated grooves on the inner wall of the second housing 2 and the outer wall of the second ceramic component 5, a labyrinth structure for the air passage is created. This increases the sealing area between the sealing glass 10 and the second housing 2 and the second ceramic component 5, and also withstands the bonding force of the sealing area under temperature shock and mechanical external loads, thus comprehensively improving the glass sealing performance of the product. Furthermore, the sealing glass 10 can fix the second ceramic component 5.

[0031] 4. An annular gap of 0.1-0.5mm is provided between the inner wall of the upper end of the second housing 2 and the outer wall of the second ceramic part 5 to increase the sealing area between the sealing glass 10 and the second housing 2 and the second ceramic part 5, thereby improving the glass sealing performance of the product.

[0032] 5. An overflow cavity 11 is provided between the upper inner wall of the second housing 2 and the outer wall of the second ceramic part 5 to store the sealing glass 10 that overflows along the gap between the upper inner wall of the second housing 2 and the outer wall of the second ceramic part 5. This can ensure that the second ceramic part 5 can be pressed into place during glass sealing, and can also prevent the glass from overflowing to the end of the second housing 2 and causing excess contamination.

[0033] 6. A sealing ring 12 is provided between the lower end face of the third housing 3 and the contact surface of the second ceramic part 5. When the third housing 3 is pressed down, the sealing ring 12 is deformed by the pressing force to realize the third sealing defense line of the external sealing channel.

[0034] 7. A sealing gasket 13 is provided between the upper end of the second housing 2 and the contact surface of the third housing 3. It has two main functions: ① pressing the third housing 3 downward; ② achieving a fourth sealing line of the external sealing channel by mechanically closing the upper end of the second housing 2.

[0035] 8. The lower end face of the central electrode 7 protrusion is made to contact the upper end face of the second ceramic part 5 to fix the central electrode 7 in the vertically downward direction.

[0036] 9. By attaching the upper edge of the protrusion of the central electrode 7 to the sealing gasket 15 and the second ceramic part 5, the central electrode 7 is fixed in the vertical upward direction, and the first sealing line of the internal sealing channel is formed at the same time.

[0037] 10. By providing organic sealant 14 between the inner wall of the second ceramic part 5 and the lower end of the locking contact 6 and between the inner wall of the second ceramic part 5 and the upper part of the protrusion of the center electrode 7, a second sealing line of the internal sealing channel can be formed.

[0038] 11. By placing the rubber sleeve 8 between the locking contact 6 and the inner wall of the second ceramic part 5, the rubber sleeve 8 deforms when it is pressed down, thereby forming the third sealing line of the internal sealing channel.

[0039] 12. The lower end of the locking contact 6 is provided with an internal thread, and the upper end of the center electrode 7 is provided with an external thread. When the two threads are engaged and locked, the upper end of the locking contact 6 forms a vertically downward pressing force, which is used to press the rubber sleeve 8.

[0040] 13. The center electrode 7 is placed inside the first ceramic part 4 and the second ceramic part 5 in order to increase the insulation strength between the center electrode 7 and the second housing 2, and to avoid internal breakdown discharge during product operation.

[0041] The specific assembly sequence and assembly process are as follows:

[0042] 1. First, install the second ceramic part 4 into the first housing 1. Then, fill the cavity formed by the first ceramic part 4 and the first housing 1 with inorganic sealant 9, preferably filling 90% of the cavity. After the inorganic sealant 9 has cured, continue to fill the cavity with inorganic sealant 9. Before the inorganic sealant 9 has cured, mechanically close the end of the first housing. Wipe away the inorganic sealant 9 overflowing from the mechanically closed area and place the product vertically to allow the inorganic sealant 9 to cure completely.

[0043] 2. The above-mentioned components are passed through the lower end of the second housing 2 and connected by argon arc welding at the junction of the first housing 1 and the second housing 2;

[0044] 3. Insert the center electrode 7 into the ceramic part 14 from top to bottom, and assemble the sealing gasket 15 onto the upper edge of the protrusion of the center electrode 7;

[0045] 4. Add 8±0.5g of sealing glass 10 to the cavity formed by the second shell 2 and the first ceramic part 4, and then place the second ceramic part 5 as shown in the figure. Figure 1 The components are inserted from top to bottom as shown.

[0046] 5. Place the entire assembly into a 990℃ high-temperature furnace and heat for 35 minutes to melt the sealing glass 10. Apply downward pressure to the second ceramic part 5 to make the sealing gasket 15 adhere and press tightly against the inner wall of the second ceramic part 5.

[0047] 6. Fill the space between the inner wall of the second ceramic part 5 and the lower end of the locking contact 6 and between the inner wall and the upper part of the protrusion of the center electrode 7 with organic sealant 14 and allow it to cure.

[0048] 7. Place the rubber sleeve 8 on the locking contact 6 and rotate the locking contact 6 clockwise so that its lower internal thread engages with the upper external thread of the center electrode 7 to lock it in place. The upper end of the locking contact 6 forms a vertical downward pressing force, which is used to press the rubber sleeve 8.

[0049] 8. Press the sealing ring 12. Figure 1 Once assembled as shown, when the third housing 3 is pressed down, it deforms to form the third sealing line of the external sealing channel.

[0050] 9. Press the third housing 3 and sealing gasket 13 together. Figure 1 The assembly is complete as shown.

[0051] 10. Mechanically close the upper end of the second housing 2 to press the third housing 3, thus forming the fourth sealing line of the external sealing channel.

[0052] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aviation ignition nozzle, characterized in that, include: First housing (1), second housing (2), third housing (3), first ceramic component (4), second ceramic component (5), locking contact (6), center electrode (7), rubber sleeve (8), sealing glass (10), The first housing (1) is welded to the lower end of the second housing (2); the upper end of the second housing (2) is mechanically closed with the lower end of the third housing (3); the first ceramic piece (4) is disposed inside the first housing (1) and the second housing (2); the second ceramic piece (5) is located inside the second housing (2) and the third housing (3) and the lower end of the second ceramic piece (5) is fitted outside the upper end of the first ceramic piece (4); an annular boss is provided on the outer side of the center electrode (7), the center electrode (7) is disposed inside the first ceramic piece (4) and the second ceramic piece (5), and the lower end face of the boss of the center electrode (7) is in contact with the upper end face of the second ceramic piece (5); a rubber sleeve (8) is disposed between the locking contact (6) and the inner wall of the second ceramic piece (5); the internal thread at the lower end of the locking contact (6) is engaged with the external thread at the upper end of the center electrode (7) to press the rubber sleeve (8), and the second housing (2) and the second ceramic piece (5) are sealed by a sealing glass (10).

2. The aviation ignition nozzle according to claim 1, characterized in that, Organic sealant (14) is provided between the inner wall of the second ceramic part (5) and the lower end of the locking contact (6) and between the second ceramic part (5) and the upper part of the protrusion of the center electrode (7).

3. The aviation ignition nozzle according to claim 1, characterized in that, A sealing gasket (15) is provided between the upper edge of the protrusion of the central electrode (7) and the inner wall of the second ceramic part (5).

4. The aviation ignition nozzle according to claim 1, characterized in that, The first ceramic component (4) is sealed to the first housing (1) by inorganic sealant (9), and the upper end of the first housing (1) is mechanically closed.

5. The aviation ignition nozzle according to claim 1, characterized in that, The inner wall of the second housing (2) and the outer wall of the second ceramic piece (5) are provided with threads or sawtooth grooves.

6. The aviation ignition nozzle according to claim 1, characterized in that, An overflow cavity (11) and an annular gap of 0.1-0.5 mm are provided between the inner wall of the upper end of the second shell (2) and the outer wall of the second ceramic piece (5), so that the sealing glass (10) can overflow upward from the annular gap to the overflow cavity (11) after melting.

7. The aviation ignition nozzle according to claim 1, characterized in that, A sealing ring (12) is provided between the lower end face of the third housing (3) and the contact surface of the second ceramic part (5).

8. The aviation ignition nozzle according to claim 1, characterized in that, A sealing gasket (13) is provided between the upper end of the second housing (2) and the contact surface of the third housing (3).

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