Aircraft engine seal structure and method

Abstract

An aero-engine sealing structure and method, according to the sealing position, four sealing structure forms are adopted; the first sealing structure form is applied to the inside of the cabin body axial end plate, a sealing reinforcing plate is welded, and the sealing performance between the shell segment end surface flange and the cabin body axial end plate can be enhanced after being fastened by a screw; the second sealing structure form is applied to the fixed part between the shell segment and the cabin body radial side plate, the fixed part is double sealed by a sealing rubber strip and room temperature vulcanized silicone rubber, a stable anti-vibration integrated sealing area is formed, the sealing effect and the sealing life are increased; the third sealing structure form is applied to the fixed part between the shell segments, the fixed part is double sealed by a sealing rubber and room temperature vulcanized silicone rubber, and the sealing life is improved; the fourth sealing structure form is applied to the sealing between the cabin body radial side plate and the shell segment combination sealing flange through a sealing cover and sealing rubber, the sealing cover is used to realize the integrated sealing of different shell segments, and the machining difficulty of the cabin body is reduced.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, and in particular relates to an aero-engine sealing structure and method. Background Technology

[0002] Previously, the sealing connections between the casing and the cabin of aircraft engines were typically achieved using only rivets and sealant under conventional sealing structures. However, during aircraft engine operation, a large amount of vibration and heat are generated, which can easily cause damage and failure of the sealant under conventional sealing structures.

[0003] In addition, since the engine casing is mostly composed of multiple curved surfaces, the difficulty of traditional sealing connections is greatly increased. At the same time, dust, water and gas can easily enter the cabin, affecting the normal operation of other precision instruments inside the cabin, and thus affecting the reliability of the aero engine. Summary of the Invention

[0004] To address the problems existing in the prior art, this invention provides a sealing structure and method for an aero-engine, employing four sealing structure forms depending on the sealing location. In the first sealing structure application, a sealing reinforcement plate is welded to the inner side of the axial end plate of the cabin, effectively increasing the area of ​​the sealing contact surface. Furthermore, after the sealing reinforcement plate is tightened with screws, it further enhances the sealing performance between the shell section end flange and the axial end plate of the cabin. In the second sealing structure application, the shell section and the radial side plate of the cabin are fixed with screws, and the fixing point is double-sealed by a sealing strip and room temperature vulcanizing silicone rubber, forming a stable and shock-resistant structure. The integrated sealing area, further tightened by screws, significantly increases the sealing effect and lifespan of this structure. In the third sealing structure application, the shell sections are fixed with rivets, and the fixing points are double-sealed with sealant and room temperature vulcanizing silicone rubber, forming a high-strength sealing surface that effectively resists engine vibration and improves sealing life. In the fourth sealing structure application, a sealing cover and sealant are used to seal the radial side plates of the hull and the sealing flanges of the shell section assembly. The sealing cover enables integrated sealing of shell sections with different shapes, greatly reducing the difficulty of hull processing.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: an aero-engine sealing structure, comprising a cabin, a first shell section, and a second shell section; a first sealing structure is adopted between the first shell section and one side of the cabin axial end plate, and between the second shell section and the other side of the cabin axial end plate; a second sealing structure is adopted between the first and second shell sections and both sides of the cabin radial side plates; a third sealing structure is adopted between the first and second shell sections; and a fourth sealing structure is adopted between the sealing connection of the first and second shell sections and both sides of the cabin radial side plates.

[0006] In the application of the first sealing structure, the first shell section is provided with a first shell section end face flange, which is fixedly connected to the axial end plate of the cabin by end face screws. Sealing adhesive is applied to the sealing contact surface between the first shell section end face flange and the axial end plate of the cabin. A first sealing reinforcement plate is welded and fixed to the inner side of the axial end plate of the cabin. The first sealing reinforcement plate matches the shape of the first shell section end face flange. The end face screws pass through the first shell section end face flange and the axial end plate of the cabin in sequence and are fixedly connected to the first sealing reinforcement plate.

[0007] In the application of the first sealing structure, the second shell section is provided with a second shell section end face flange, which is fixedly connected to the axial end plate of the cabin by end face screws. Sealant is applied to the sealing contact surface between the second shell section end face flange and the axial end plate of the cabin. A second sealing reinforcement plate is welded and fixed to the inner side of the axial end plate of the cabin. The second sealing reinforcement plate matches the shape of the second shell section end face flange. The end face screws pass through the second shell section end face flange and the axial end plate of the cabin in sequence and are fixedly connected to the second sealing reinforcement plate.

[0008] In the second sealing structure application, the first shell section and the radial side plate of the cabin are fixedly connected by side plate screws. A first upper sealing strip is provided between the first shell section above the side plate screws and the radial side plate of the cabin, and a first lower sealing strip is provided between the first shell section below the side plate screws and the radial side plate of the cabin. Room temperature vulcanizing silicone rubber is filled in the gap between the first lower sealing strip and the first upper sealing strip.

[0009] In the application of the second sealing structure, the second shell section is fixedly connected to the radial side plate of the cabin by side plate screws. A second upper sealing strip is provided between the second shell section above the side plate screws and the radial side plate of the cabin, and a second lower sealing strip is provided between the second shell section below the side plate screws and the radial side plate of the cabin. Room temperature vulcanizing silicone rubber is filled in the gap between the second lower sealing strip and the second upper sealing strip.

[0010] In the application of the third sealing structure, the first shell section is provided with a first shell section sealing flange, and the second shell section is provided with a second shell section sealing flange. The second shell section sealing flange and the first shell section sealing flange are fixedly connected by rivets. Sealant is applied to the sealing contact surfaces of the second shell section sealing flange and the first shell section sealing flange. A first shell section sealing groove is provided on the sealing contact surface of the first shell section sealing flange, and a second shell section sealing groove is provided on the sealing contact surface of the second shell section sealing flange. The second shell section sealing groove and the first shell section sealing groove are directly opposite each other and are engaged together. The engaged second shell section sealing groove and the first shell section sealing groove are filled with room temperature vulcanizing silicone rubber.

[0011] The first and second shell section sealing grooves adopt a wavy orientation, which allows the first and second shell section sealing grooves to bypass the rivets.

[0012] In the application of the fourth sealing structure, a sealing cover is fixedly welded to the radial side plate of the cabin. The first shell section sealing flange and the second shell section sealing flange after sealing connection are located inside the sealing cover. The inner surface of the sealing cover contacts the outer surface of the first shell section sealing flange and the second shell section sealing flange and forms a sealing contact surface. Sealant is applied to the sealing contact surface.

[0013] A method for sealing an aircraft engine, employing the aforementioned aircraft engine sealing structure, includes the following steps:

[0014] Step 1: Assemble the first and second shell segments

[0015] First, apply sealant to the sealing contact surfaces of the first and second shell section sealing flanges. Then, assemble the first and second shell section sealing flanges together after applying the sealant. Next, use rivets to fix the first and second shell section sealing flanges together. Finally, inject room temperature vulcanizing silicone rubber into one end of the groove of the second and first shell section sealing grooves in the interlocking state until the silicone rubber leaves out from the other end of the groove. This indicates that the inside of the interlocking second and first shell section sealing grooves has been filled with silicone rubber. Then, wait for the silicone rubber to cure until the first and second shell sections are sealed together to form a shell section assembly.

[0016] Step 2: Assemble the cabin and shell sections.

[0017] The first upper and lower sealing strips are adhered to the predetermined positions of the first shell section, and the second upper and lower sealing strips are adhered to the predetermined positions of the second shell section. Then, sealant is applied to the sealing contact surfaces of the first shell section end flange, the second shell section end flange, and the axial end plate of the cabin. The shell section assembly is then assembled with the cabin. Finally, the first shell section end flange is fixedly connected to the axial end plate of the cabin, and the second shell section end flange is fixedly connected to the axial end plate of the cabin, using end face screws. The end face screws are screwed into the first and second sealing reinforcement plates. The first shell section is fixedly connected to the radial side plate of the cabin and the second shell section is fixedly connected to the radial side plate of the cabin using side plate screws. Finally, room temperature vulcanizing silicone rubber is injected from one end of the gap between the first lower sealing strip and the first upper sealing strip until the room temperature vulcanizing silicone rubber flows out from the other end of the gap. At the same time, room temperature vulcanizing silicone rubber is injected from one end of the gap between the second lower sealing strip and the second upper sealing strip until the room temperature vulcanizing silicone rubber flows out from the other end of the gap, indicating that the gap has been filled with room temperature vulcanizing silicone rubber. Then, wait for the room temperature vulcanizing silicone rubber to cure until the cabin and shell section assembly is sealed and connected.

[0018] The beneficial effects of this invention are:

[0019] The aero-engine sealing structure and method of the present invention employs four sealing structure forms according to different sealing positions. In the first sealing structure application, a sealing reinforcement plate is welded to the inner side of the axial end plate of the cabin, which effectively increases the area of ​​the sealing contact surface. Furthermore, after the sealing reinforcement plate is tightened with screws, it further enhances the sealing performance between the shell section end flange and the axial end plate of the cabin. In the second sealing structure application, the shell section and the radial side plate of the cabin are fixed with screws, and the fixing point is double-sealed by sealing strips and room temperature vulcanizing silicone rubber, forming a stable and shock-resistant integrated sealing area. The screws then apply pressure to the sealing area, significantly increasing the sealing effect and sealing life of this structure. In the third sealing structure application, the shell sections are fixed with rivets, and the fixing point is double-sealed by sealant and room temperature vulcanizing silicone rubber, forming a high-strength sealing surface that effectively resists engine vibration and improves sealing life. In the fourth sealing structure application, a sealing cover and sealant are used to achieve sealing between the radial side plate of the cabin and the sealing flange of the shell section assembly. The sealing cover enables integrated sealing of shell sections with different shapes, significantly reducing the processing difficulty of the cabin. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of a sealing structure for an aircraft engine according to the present invention;

[0021] Figure 2 This is a schematic diagram of a sealing structure for an aero-engine (the cabin and shell section assembly are in a separate state) according to the present invention.

[0022] Figure 3 This is a schematic diagram (axial section view) of a sealing structure for an aircraft engine according to the present invention;

[0023] Figure 4 This is a schematic diagram of the sealing structure of an aero-engine according to the present invention (radial cross-section within the first shell section);

[0024] Figure 5 for Figure 3 Enlarged view of the middle section (I);

[0025] Figure 6 for Figure 3 Enlarged view of Part II;

[0026] Figure 7 for Figure 4 Enlarged view of Part III;

[0027] Figure 8 This is a schematic diagram of the cabin structure of the present invention;

[0028] Figure 9 This is a schematic diagram of the structure of the second shell segment of the present invention;

[0029] In the figure, 1—hull, 11—hull axial end plate, 12—hull radial side plate, 13—first sealing reinforcement plate, 2—first shell section, 21—first shell section end face flange, 22—first shell section sealing flange, 23—first shell section sealing groove, 3—second shell section, 31—second shell section end face flange, 32—second shell section sealing flange, 33—second shell section sealing groove, 4—end face screw, 5—side plate screw, 6—first upper sealing strip, 7—first lower sealing strip, 8—rivet, 9—sealing cover. Detailed Implementation

[0030] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0031] like Figures 1-9 As shown, an aero-engine sealing structure includes a cabin 1, a first shell section 2, and a second shell section 3. A first sealing structure is used between the first shell section 2 and one side of the axial end plate 11 of the cabin 1, and between the second shell section 3 and the other side of the axial end plate 11 of the cabin 1. A second sealing structure is used between the first shell section 2 and the second shell section 3 and the radial side plates 12 of the cabin 1 on both sides. A third sealing structure is used between the first shell section 2 and the second shell section 3. A fourth sealing structure is used at the sealing connection between the first shell section 2 and the second shell section 3 and the radial side plates 12 of the cabin 1 on both sides.

[0032] In the application of the first sealing structure, the first shell section 2 is provided with a first shell section end face flange 21. The first shell section end face flange 21 is fixedly connected to the axial end plate 11 of the cabin 1 by end face screws 4. Sealing adhesive is applied to the sealing contact surface between the first shell section end face flange 21 and the axial end plate 11 of the cabin 1. A first sealing reinforcement plate 13 is welded and fixed to the inner side of the axial end plate 11 of the cabin 1. The first sealing reinforcement plate 13 matches the shape of the first shell section end face flange 21. The end face screws 4 pass through the first shell section end face flange 21 and the axial end plate 11 of the cabin 1 in sequence and are fixedly connected to the first sealing reinforcement plate 13.

[0033] In the application of the first sealing structure, the second shell section 3 is provided with a second shell section end face flange 31. The second shell section end face flange 31 is fixedly connected to the axial end plate 11 of the cabin 1 by end face screws 4. Sealing adhesive is applied to the sealing contact surface between the second shell section end face flange 31 and the axial end plate 11 of the cabin 1. A second sealing reinforcement plate is welded and fixed to the inner side of the axial end plate 11 of the cabin 1. The second sealing reinforcement plate matches the shape of the second shell section end face flange 31. The end face screws 4 pass through the second shell section end face flange 31 and the axial end plate 11 of the cabin 1 in sequence and are fixedly connected to the second sealing reinforcement plate.

[0034] In the second sealing structure application, the first shell section 2 and the radial side plate 12 of the cabin 1 are fixedly connected by side plate screws 5. A first upper sealing strip 6 is provided between the first shell section 2 above the side plate screws 5 and the radial side plate 12 of the cabin 1, and a first lower sealing strip 7 is provided between the first shell section 2 below the side plate screws 5 and the radial side plate 12 of the cabin 1. The gap between the first lower sealing strip 7 and the first upper sealing strip 6 is filled with room temperature vulcanizing silicone rubber.

[0035] In the application of the second sealing structure, the second shell section 3 is fixedly connected to the radial side plate 12 of the cabin 1 by side plate screws 5. A second upper sealing strip is provided between the second shell section 3 above the side plate screws 5 and the radial side plate 12 of the cabin 1, and a second lower sealing strip is provided between the second shell section 3 below the side plate screws 5 and the radial side plate 12 of the cabin 1. The gap between the second lower sealing strip and the second upper sealing strip is filled with room temperature vulcanizing silicone rubber.

[0036] In the application of the third sealing structure, the first shell section 2 is provided with a first shell section sealing flange 22, and the second shell section 3 is provided with a second shell section sealing flange 32. The second shell section sealing flange 32 and the first shell section sealing flange 22 are fixedly connected by rivets 8. Sealant is applied to the sealing contact surface of the second shell section sealing flange 32 and the first shell section sealing flange 22. A first shell section sealing groove 23 is provided on the sealing contact surface of the first shell section sealing flange 22, and a second shell section sealing groove 33 is provided on the sealing contact surface of the second shell section sealing flange 32. The second shell section sealing groove 33 and the first shell section sealing groove 23 are directly opposite each other and are fastened together. The fastened second shell section sealing groove 33 and the first shell section sealing groove 23 are filled with room temperature vulcanizing silicone rubber.

[0037] The first shell section sealing groove 23 and the second shell section sealing groove 33 adopt a wavy direction, which allows the first shell section sealing groove 23 and the second shell section sealing groove 33 to bypass the rivet 8.

[0038] In the application of the fourth sealing structure, a sealing cover 9 is fixedly welded to the radial side plate 12 of the cabin 1. The first shell section sealing flange 22 and the second shell section sealing flange 32 after sealing connection are located inside the sealing cover 9. The inner surface of the sealing cover 9 contacts the outer surface of the first shell section sealing flange 22 and the second shell section sealing flange 32 and forms a sealing contact surface. Sealant is applied to the sealing contact surface.

[0039] A method for sealing an aircraft engine, employing the aforementioned aircraft engine sealing structure, includes the following steps:

[0040] Step 1: Assemble the first shell segment 2 and the second shell segment 3

[0041] First, apply sealant to the sealing contact surfaces of the first shell section sealing flange 22 and the second shell section sealing flange 32. Then, assemble the first shell section sealing flange 22 and the second shell section sealing flange 32 together after applying the sealant. Next, use rivets 8 to fix the first shell section sealing flange 22 and the second shell section sealing flange 32. Finally, inject room temperature vulcanizing silicone rubber into one end of the groove opening of the second shell section sealing groove 33 and the first shell section sealing groove 23 in the snap-fit ​​state until the room temperature vulcanizing silicone rubber leaves out from the other end of the groove opening. This indicates that the interior of the second shell section sealing groove 33 and the first shell section sealing groove 23 in the snap-fit ​​state has been filled with room temperature vulcanizing silicone rubber. Then wait for the room temperature vulcanizing silicone rubber to cure until the first shell section 2 and the second shell section 3 are sealed together to form a shell section assembly.

[0042] Step 2: Assemble the cabin 1 and shell section assembly

[0043] The first upper sealing strip 6 and the first lower sealing strip 7 are attached to the preset positions of the first shell section 2, and the second upper sealing strip and the second lower sealing strip are attached to the preset positions of the second shell section 3. Then, sealant is applied to the sealing contact surfaces of the first shell section end flange 21, the second shell section end flange 31, and the axial end plate 11 of the cabin 1. The shell section assembly is then assembled with the cabin 1. Finally, the first shell section end flange 21 and the axial end plate 11 of the cabin 1, and the second shell section end flange 31 and the axial end plate 11 of the cabin 1 are fixedly connected together using end face screws 4. The end face screws 4 are screwed into the first sealing reinforcement plate 13 and the second sealing... The reinforcing plate is then used to fix the first shell section 2 to the radial side plate 12 of the cabin 1 and the second shell section 3 to the radial side plate 12 of the cabin 1 together using side plate screws 5. Finally, room temperature vulcanizing silicone rubber is injected from one end of the gap between the first lower sealing strip 7 and the first upper sealing strip 6 until the room temperature vulcanizing silicone rubber flows out from the other end of the gap. At the same time, room temperature vulcanizing silicone rubber is injected from one end of the gap between the second lower sealing strip and the second upper sealing strip until the room temperature vulcanizing silicone rubber flows out from the other end of the gap, indicating that the gap has been filled with room temperature vulcanizing silicone rubber. Then, the room temperature vulcanizing silicone rubber is allowed to cure until the cabin 1 and the shell section assembly are sealed together.

[0044] The solutions described in the embodiments are not intended to limit the scope of patent protection of this invention. All equivalent implementations or modifications that do not depart from the scope of this invention are included in the patent scope of this case.

Claims

1. A sealing structure for an aircraft engine, characterized in that: It includes a cabin, a first shell section, and a second shell section; a first sealing structure is used between the first shell section and one side of the cabin axial end plate, and between the second shell section and the other side of the cabin axial end plate; a second sealing structure is used between the first and second shell sections and both sides of the cabin radial side plates; a third sealing structure is used between the first and second shell sections; and a fourth sealing structure is used between the sealing connection of the first and second shell sections and both sides of the cabin radial side plates. In the application of the first sealing structure, the first shell section is provided with a first shell section end face flange, which is fixedly connected to the axial end plate of the cabin by end face screws. Sealing adhesive is applied to the sealing contact surface between the first shell section end face flange and the axial end plate of the cabin. A first sealing reinforcement plate is welded and fixed to the inner side of the axial end plate of the cabin. The first sealing reinforcement plate matches the shape of the first shell section end face flange. The end face screws pass through the first shell section end face flange and the axial end plate of the cabin in sequence and are fixedly connected to the first sealing reinforcement plate. In the application of the first sealing structure, the second shell section is provided with a second shell section end face flange, which is fixedly connected to the axial end plate of the cabin by end face screws. Sealing adhesive is applied to the sealing contact surface between the second shell section end face flange and the axial end plate of the cabin. A second sealing reinforcement plate is welded and fixed to the inner side of the axial end plate of the cabin. The shape of the second sealing reinforcement plate matches that of the second shell section end face flange. The end face screws pass through the second shell section end face flange and the axial end plate of the cabin in sequence and are fixedly connected to the second sealing reinforcement plate. In the second sealing structure application, the first shell section and the radial side plate of the cabin are fixedly connected by side plate screws. A first upper sealing strip is provided between the first shell section above the side plate screws and the radial side plate of the cabin, and a first lower sealing strip is provided between the first shell section below the side plate screws and the radial side plate of the cabin. Room temperature vulcanizing silicone rubber is filled in the gap between the first lower sealing strip and the first upper sealing strip. In the application of the second sealing structure, the second shell section and the radial side plate of the cabin are fixedly connected by side plate screws. A second upper sealing strip is provided between the second shell section above the side plate screws and the radial side plate of the cabin, and a second lower sealing strip is provided between the second shell section below the side plate screws and the radial side plate of the cabin. Room temperature vulcanizing silicone rubber is filled in the gap between the second lower sealing strip and the second upper sealing strip. In the application of the third sealing structure, the first shell section is provided with a first shell section sealing flange, and the second shell section is provided with a second shell section sealing flange. The second shell section sealing flange and the first shell section sealing flange are fixedly connected by rivets. Sealant is applied to the sealing contact surfaces of the second shell section sealing flange and the first shell section sealing flange. A first shell section sealing groove is provided on the sealing contact surface of the first shell section sealing flange, and a second shell section sealing groove is provided on the sealing contact surface of the second shell section sealing flange. The second shell section sealing groove and the first shell section sealing groove are directly opposite each other and are fastened together. The fastened second shell section sealing groove and the first shell section sealing groove are filled with room temperature vulcanizing silicone rubber. The first shell section sealing groove and the second shell section sealing groove adopt a wavy direction, which allows the first shell section sealing groove and the second shell section sealing groove to bypass the rivet. In the application of the fourth sealing structure, a sealing cover is fixedly welded to the radial side plate of the cabin. The first shell section sealing flange and the second shell section sealing flange after sealing connection are located inside the sealing cover. The inner surface of the sealing cover contacts the outer surface of the first shell section sealing flange and the second shell section sealing flange and forms a sealing contact surface. Sealant is applied to the sealing contact surface.

2. A method for sealing an aircraft engine, employing the aircraft engine sealing structure described in claim 1, characterized in that... The steps include the following: Step 1: Assemble the first and second shell segments First, apply sealant to the sealing contact surfaces of the first and second shell section sealing flanges. Then, assemble the first and second shell section sealing flanges together after applying the sealant. Next, use rivets to fix the first and second shell section sealing flanges together. Finally, inject room temperature vulcanizing silicone rubber into one end of the groove of the second and first shell section sealing grooves in the interlocking state until the silicone rubber leaves out from the other end of the groove. This indicates that the inside of the interlocking second and first shell section sealing grooves has been filled with silicone rubber. Then, wait for the silicone rubber to cure until the first and second shell sections are sealed together to form a shell section assembly. Step 2: Assemble the cabin and shell sections. The first upper and lower sealing strips are adhered to the predetermined positions of the first shell section, and the second upper and lower sealing strips are adhered to the predetermined positions of the second shell section. Then, sealant is applied to the sealing contact surfaces of the first shell section end flange, the second shell section end flange, and the axial end plate of the cabin. The shell section assembly is then assembled with the cabin. Finally, the first shell section end flange is fixedly connected to the axial end plate of the cabin, and the second shell section end flange is fixedly connected to the axial end plate of the cabin, using end face screws. The end face screws are screwed into the first and second sealing reinforcement plates. The first shell section is fixedly connected to the radial side plate of the cabin and the second shell section is fixedly connected to the radial side plate of the cabin using side plate screws. Finally, room temperature vulcanizing silicone rubber is injected from one end of the gap between the first lower sealing strip and the first upper sealing strip until the room temperature vulcanizing silicone rubber flows out from the other end of the gap. At the same time, room temperature vulcanizing silicone rubber is injected from one end of the gap between the second lower sealing strip and the second upper sealing strip until the room temperature vulcanizing silicone rubber flows out from the other end of the gap, indicating that the gap has been filled with room temperature vulcanizing silicone rubber. Then, wait for the room temperature vulcanizing silicone rubber to cure until the cabin and shell section assembly is sealed and connected.

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