Composite pressure vessel with equatorial threaded boss for high temperature gas and method of manufacturing same

Abstract

The application provides a high-temperature gas composite pressure vessel with an equatorial boss and a manufacturing method thereof, and the composite pressure vessel comprises a heat insulation layer, a metal lining and a composite layer; the steps of the method mainly comprise: metal lining forming; metal lining weld seam grinding; heat insulation layer spraying; heat insulation layer curing; metal lining outer surface glue supplementing; annular composite layer winding; equatorial boss fiber cloth reinforcing winding; lining composite layer spiral winding; equatorial S-shaped fiber winding; composite layer surface treatment; and fiber curing. The application solves the problems that the existing high-temperature gas pressure vessel can only adopt a heavy full-metal structure scheme to realize equatorial boss connection and cannot realize light weight, and solves the matching problem of high-temperature resin and a titanium alloy lining, and provides a solution for the manufacturing method of the high-temperature gas composite pressure vessel with an equatorial boss.

Description

Technical Field

[0001] This invention relates to the field of high-temperature composite material pressure vessel manufacturing technology, specifically to a high-temperature gas-fired composite material pressure vessel with an equatorial threaded boss and its manufacturing method. Background Technology

[0002] High-temperature pressure vessels for high-temperature gas systems are mainly used for storing liquid and gaseous media and bearing a certain pressure to achieve functions such as power propulsion and pressure supply.

[0003] Due to the high-temperature environment, pressure vessels cannot be directly wound with conventional room-temperature composite materials; only all-metal pressure vessels can be used. However, the equatorial boss structure further restricts the winding process.

[0004] Currently, there is no suitable method for manufacturing composite pressure vessels with equatorial bosses using spiral winding technology, either domestically or internationally, for high-temperature applications. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the present invention aims to provide a composite material pressure vessel with an equatorial threaded boss for high-temperature gas combustion and its manufacturing method.

[0006] A method for manufacturing a high-temperature gas-fired composite pressure vessel with an equatorial boss, according to the present invention, includes:

[0007] Step S1: Metal liner forming;

[0008] Step S2: Grinding the weld seams of the metal lining;

[0009] Step S3: Spray an insulation layer onto the inner wall of the metal liner;

[0010] Step S4: Curing the insulation layer;

[0011] Step S5: Apply adhesive to the outer surface of the metal liner;

[0012] Step S6: Circumferentially wrap a composite material layer around the equatorial boss of the metal liner;

[0013] Step S7: Reinforcing wrapping of fiber cloth around the equatorial boss;

[0014] Step S8: Spiral winding of the inner lining composite material layer; Repeat steps S7 to S8 until the preset conditions are met;

[0015] Step S9: Equatorial boss S-shaped fiber winding;

[0016] Step S10: Surface treatment of the composite material layer;

[0017] Step S11: Fiber curing.

[0018] Preferably, in step S1, the metal liner is formed by welding multiple shells. During welding, segmented welding should be used to avoid misalignment of the thin-walled shells; at the same time, each arc starting and ending point should avoid the area above and below the equatorial convex platform.

[0019] The weld seam of the metal lining is ground with sandpaper, and then the ground surface is cleaned. The height of the ground weld seam should not exceed the preset value.

[0020] Preferably, step S3 involves spraying the inner wall of the metal liner to evenly cover the inner surface with heat-insulating coating, with the thickness meeting the preset requirements.

[0021] Preferably, step S5 involves filling the non-smooth transition area of ​​the lining and the weld depression area with fibers and adhesive to prevent fiber entanglement.

[0022] Preferably, step S6 involves: wet-winding a composite material layer around the upper and lower circumferential regions of the equatorial protrusion of the metal liner;

[0023] Step S8 involves spiral wet winding of the inner lining composite material layer.

[0024] Preferably, step S7 involves: impregnating a cross-fiber cloth of a determined size with colloid and then laying and bonding the fiber winding blind area of ​​each equatorial protrusion of the metal lining.

[0025] Preferably, step S9 involves: the fibers are wet-wound sequentially from the lower root of the previous equatorial protrusion to the upper root of the next equatorial protrusion.

[0026] Preferably, step S10 involves: treating the intersecting gaps between fibers in the fiber composite material layer to minimize the exposed area of ​​the lining, while simultaneously squeezing and removing adhesive from the fibers piled up at the root of the flange lugs to effectively improve the thickness of the fiber pile.

[0027] Preferably, the pressure vessel is filled with gas, and the pressure is always maintained at 0.5-2 MPa. The fiber curing temperature is raised to 400-450°C and held for 5-10 hours.

[0028] The high-temperature gas-fired composite pressure vessel with an equatorial boss provided by the present invention is prepared by the above-described manufacturing method of the high-temperature gas-fired composite pressure vessel with an equatorial boss.

[0029] Compared with the prior art, the present invention has the following beneficial effects: The present invention solves the problem of large structural weight of the all-metal scheme of the pressure vessel with equatorial flange for high temperature gas, and proposes a solution for the manufacturing method of composite material pressure vessel with equatorial flange for high temperature gas. Attached Figure Description

[0030] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0031] Figure 1 A schematic diagram of a fiber-wound spherical pressure vessel with an equatorial boss for high-temperature combustion gases.

[0032] Figure 2 A schematic diagram of a fiber-wound spherical pressure vessel with an equatorial boss for high-temperature combustion gases.

[0033] Figure 3 A schematic diagram of a fiber-wound ellipsoidal pressure vessel with an equatorial boss for high-temperature combustion gases.

[0034] Figure 4 This is a schematic diagram of the circumferential composite material layer winding.

[0035] Figure 5 This is a schematic diagram of fiber reinforcement for the equatorial protrusion.

[0036] Figure 6 This is a schematic diagram of the spiral winding of the inner lining composite material layer.

[0037] Figure 7 This is a schematic diagram of S-shaped fiber winding around the equatorial protrusion. Detailed Implementation

[0038] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0039] To address the issue of high structural mass in pressure vessels with equatorial flanges used for high-temperature gas applications, which are limited to all-metal pressure vessels, a method for manufacturing composite material pressure vessels with equatorial bosses suitable for high-temperature gas environments is proposed.

[0040] Example 1

[0041] According to the present invention, a method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss is provided, wherein the composite material pressure vessel comprises: a metal liner, a heat insulation layer, and a composite material layer.

[0042] The steps of this method are as follows Figures 1 to 7 As shown, it includes:

[0043] Step 1: Metal liner forming;

[0044] Step 2: Grinding the weld seams of the metal lining;

[0045] Step 3: Apply the heat insulation layer;

[0046] Step 4: Curing of the insulation layer;

[0047] Step 5: Apply adhesive to the outer surface of the metal lining;

[0048] Step 6: Circumferential composite material layer winding;

[0049] Step 7: Reinforcing wrapping of fiber cloth around the equatorial protrusion;

[0050] Step 8: Spiral winding of the inner lining composite material layer;

[0051] Step 9: S-shaped fiber winding around the equatorial protrusion;

[0052] Step 10: Surface treatment of the composite material layer;

[0053] Step 11: Fiber curing.

[0054] Specifically, the metal liner in step 1 is formed by welding two or three shell parts. Welding should be done in sections to avoid misalignment of the thin-walled shell. At the same time, the starting and ending points of each arc should avoid the area above and below the equatorial convex platform.

[0055] Specifically, the metal lining weld grinding in step 2 refers to: grinding the metal lining weld with sandpaper, and then cleaning the ground surface. The height of the ground weld should not exceed 0.4mm.

[0056] Specifically, the heat insulation layer spraying in step 3 refers to spraying the inner wall of the metal lining to evenly cover the inner surface with heat insulation coating, with a thickness of 0.2 to 1.5 mm.

[0057] Specifically, the curing of the heat insulation layer in step 4 refers to curing the heat insulation layer by heating it in a heat treatment furnace at 450-500°C for 4-5 hours, thereby firmly bonding it to the inner surface of the metal lining.

[0058] Specifically, the adhesive filling on the outer surface of the metal lining in step 5 refers to filling the non-smooth transition areas and weld depression areas of the lining with fibers and adhesive to prevent fiber entanglement.

[0059] The adhesive filling is performed in two stages. After the first application and curing, the surface is sanded and the surface quality is checked. The filled area is required to have a smooth transition. Any areas that do not meet the requirements are filled with adhesive a second time. After the adhesive filling is completed, it is cured at room temperature for 8 to 10 hours.

[0060] Specifically, wet winding is used when fiber winding is performed in steps 6, 8 and 9.

[0061] Specifically, in step 6, the circumferential composite material layer is wound around the upper and lower circumferential regions of the equatorial bulge of the metal liner.

[0062] Specifically, the equatorial protrusion fiber cloth reinforcement in step 7 refers to: after impregnating the cross-fiber cloth of a certain size with colloid, laying it on the metal lining near the blind area of ​​each equatorial protrusion fiber winding.

[0063] Specifically, steps 7 and 8 should be performed alternately.

[0064] Specifically, the fiber winding in step 9 refers to the following: the fiber is wound in an S-shape along the upper and lower sides of the equatorial protrusion of the metal lining, that is, the fiber is wound sequentially from the lower root of the previous equatorial protrusion to the upper root of the next equatorial protrusion.

[0065] Specifically, in step 10, the intersecting gaps between fibers in the fiber composite material layer are treated to minimize the exposed area of ​​the lining. At the same time, the fibers piled up at the root of the flange lugs are squeezed and the adhesive is removed to effectively improve the thickness of the fiber pile.

[0066] Specifically, in step 11, the pressure vessel is filled with gas, and the pressure is always maintained at 0.5 to 2 MPa. The fiber curing temperature is raised to 400 to 450°C and kept at that temperature for 5 to 10 hours.

[0067] According to the present invention, a composite material pressure vessel is manufactured using the manufacturing method of the high-temperature gas-fired composite material pressure vessel with an equatorial boss.

[0068] Example 2

[0069] Example 2 is a preferred example of Example 1.

[0070] The present invention will be further described below with reference to the accompanying drawings and examples.

[0071] In this embodiment, the present invention provides a method for manufacturing an 8.6L composite material pressure vessel with an equatorial boss for high-temperature fuel gas, wherein the composite material pressure vessel comprises: a titanium alloy liner and a T800 carbon fiber composite material layer; the method includes the following steps:

[0072] Step 1: The titanium alloy liner is formed by electron beam circumferential welding through the upper and lower shells to the connecting ring containing the load-bearing flange. The arc start and end points are located between the two equatorial bosses. The welding voltage is 50kV, the beam current is 9A, the focusing is 395mA, and the speed is 1000mm / min. Radiographic testing is performed after welding.

[0073] Step 2: Protect the areas of the lining that do not require grinding with tape. Grind the weld seams of the metal lining with 80-120 grit sandpaper, and then clean the ground surface with acetone. The height of the ground weld seam should not exceed 0.4mm.

[0074] Step 3: Spray the heat insulation coating evenly onto the inner wall of the metal lining, with a thickness of 0.2-1.5 mm;

[0075] Step 4: Place the metal lining in an oven to cure the heat insulation layer at 450-500℃ for 4-5 hours;

[0076] Step 5: Mix the white carbon and polyetheramine curing agent in a certain proportion to form a gel-like liquid. Fill the non-smooth transition area and weld depression area on the inner lining surface. The filling is done in two stages. After the first filling is cured, the surface is ground and the surface quality is inspected. The second filling is done on the unqualified areas. After the filling is completed, let it be placed at room temperature to cure for 8 to 10 hours.

[0077] Step 6: As Figure 4 As shown, circumferential fiber winding is performed in the areas above and below the equatorial convex platform of the metal liner;

[0078] Step 7: As Figure 5 As shown, the first layer of fiber cloth is used to reinforce the fiber wrapping blind area above and below each equatorial boss. Specifically, a hole with an area equivalent to the root area of ​​the flange lug is cut in the center of the cross fiber cloth. Then, the fiber cloth is passed through the equatorial boss and bonded to the outer surface of the inner lining in a taut state using phthalic acid resin / polyetheramine curing agent gel liquid.

[0079] Step 8: As Figure 6 As shown, the first layer of spiral winding is carried out using a wet winding process. When the fiber is wound to each equatorial protrusion, manual intervention is performed to make the fiber bypass the flange lugs and accumulate at the root on both sides. The winding angle is 8 to 12°.

[0080] Step 9: Repeat step 5 to reinforce the fiber entanglement blind area above and below the equatorial bulge with a second layer of fiber cloth;

[0081] Step 10: Repeat step 6 to perform the second layer of spiral winding, with a winding angle of 15-20°;

[0082] Step 11: Repeat step 5 to reinforce the fiber entanglement blind area above and below the equatorial bulge with a third layer of fiber cloth;

[0083] Step 12: Repeat step 6 to make the remaining three spiral windings, with the third winding angle being 25-30°, the fourth winding angle being 30-50°, and the fifth winding angle being 50-70°;

[0084] Step 13: As Figure 7As shown, on the outer surface of the fifth spiral winding layer, the flange lugs are circumferentially wound in an S-shape, that is, the fibers are wound from the lower root of the previous flange lug to the upper root of the next flange lug.

[0085] Step 14: Treat the intersecting gaps of each fiber in the fiber composite layer to minimize the exposed area of ​​the lining. The exposed area of ​​the lining should not exceed 5mm×5mm. At the same time, squeeze and remove the glue from the accumulated fibers at the root of the flange lug to improve the thickness of the fiber accumulation.

[0086] Step 15: Place the pressure vessel after winding into a curing oven for curing at 400-450℃ for 5-10 hours.

[0087] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for manufacturing a composite material pressure vessel with an equatorial boss for high-temperature gas combustion, characterized in that, include: Step S1: Metal liner forming; Step S2: Grinding the weld seams of the metal lining; Step S3: Spray an insulation layer onto the inner wall of the metal liner; Step S4: Curing the insulation layer; Step S5: Apply adhesive to the outer surface of the metal liner; Step S6: Circumferentially wrap a composite material layer around the equatorial boss of the metal liner; Step S7: Reinforcing wrapping of fiber cloth around the equatorial boss; Step S8: Spiral winding of the inner lining composite material layer; Repeat steps S7 to S8 until the preset conditions are met; Step S9: Equatorial boss S-shaped fiber winding; Step S10: Surface treatment of the composite material layer; Step S11: Fiber curing; The pressure vessel is filled with gas, and the pressure is maintained at 0.5-2 MPa. The fiber curing temperature is raised to 400-450℃ and held for 5-10 hours.

2. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, In step S1, the metal liner is formed by welding multiple shells. During welding, segmented welding should be used to avoid misalignment of the thin-walled shells. At the same time, each arc starting and ending point should avoid the area above and below the equatorial convex platform. The weld seam of the metal lining is ground with sandpaper, and then the ground surface is cleaned. The height of the ground weld seam should not exceed the preset value.

3. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, Step S3 involves spraying the inner wall of the metal lining to evenly cover the inner surface with heat-insulating coating, with the thickness meeting the preset requirements.

4. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, Step S5 involves filling the non-smooth transition areas of the inner lining and the weld depression areas with fibers and adhesive to prevent fiber entanglement.

5. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, Step S6 involves: wet-winding a composite material layer around the upper and lower circumferential regions of the equatorial convex area of ​​the metal liner; Step S8 involves spiral wet winding of the inner lining composite material layer.

6. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, Step S7 involves: impregnating a cross-fiber cloth of a determined size with colloid, then laying and bonding the metal lining to the blind areas of each equatorial protrusion fiber winding.

7. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, Step S9 involves the following: the fiber is wet-wound sequentially from the lower root of the previous equatorial protrusion to the upper root of the next equatorial protrusion.

8. The method for manufacturing a high-temperature gas-fired composite material pressure vessel with an equatorial boss according to claim 1, characterized in that, Step S10 involves treating the intersecting gaps between fibers in the fiber composite material layer to minimize the exposed area of ​​the lining, while simultaneously squeezing and removing adhesive from the fibers piled up at the root of the flange lugs to effectively improve the thickness of the fiber pile.

9. A composite material pressure vessel with an equatorial boss for high-temperature gas combustion, characterized in that, It is prepared using the manufacturing method of the high-temperature gas-fired composite material pressure vessel with an equatorial boss as described in any one of claims 1 to 8.

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