Double-sealing flange assembly suitable for high-pressure propellant pushing of liquid aircraft

Abstract

The embodiment of the utility model provides a double sealing flange assembly suitable for pushing a high-pressure propellant of a liquid aircraft, the double sealing flange assembly further comprises a first sealing installation structure and a first sealing piece, the first sealing installation structure is provided with an upper flange end face (11) and a lower flange end face (21), and the first sealing piece is installed in the first sealing installation structure. When the upper channel and the lower channel are filled with high-pressure propellants, the first sealing piece deforms under the pressure effect of the high-pressure propellants, and self-tightening sealing between the first sealing piece and the upper flange (1) and between the first sealing piece and the lower flange (2) can be achieved. A second sealing installation structure and a second sealing piece are further included, the second sealing installation structure is provided with an upper flange end face (11) and a lower flange end face (21), and the second sealing piece can be installed in the second sealing installation structure in an attached mode. The flange structure and the sealing structure are simple, and the sealing efficiency is high.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of carrier rockets, in particular to a double-channel sealing flange assembly suitable for high-pressure propellant pushing of liquid aircraft. BACKGROUND

[0002] Most of the mainstream carrier rockets in service in China adopt low-temperature propellants such as liquid oxygen kerosene, liquid oxygen methane, liquid hydrogen liquid oxygen, etc. The inner and outer flange faces of the carrier rocket are for two different propellants, and the temperature difference of the propellants is large, and the temperature range is wide. Once the sealing surface of the flange leaks, it will directly lead to system failure and launch failure, and the sealing reliability requirement is extremely high.

[0003] In the process of implementing the utility model, the applicant found that there are at least the following problems in the prior art:

[0004] The traditional single-channel sealing method has low reliability and cannot meet the sealing requirements of the flange interface of the liquid oxygen kerosene, liquid oxygen methane, liquid hydrogen liquid oxygen, etc. low-temperature propellants of the mainstream carrier rockets in service. UTILITY MODEL CONTENTS

[0005] The utility model embodiment provides a double-channel sealing flange assembly suitable for high-pressure propellant pushing of liquid aircraft, which can solve the technical problem of the prior art that the traditional single-channel sealing method has low reliability and cannot meet the sealing requirements of the flange interface of the liquid oxygen kerosene, liquid oxygen methane, liquid hydrogen liquid oxygen, etc. low-temperature propellants of the mainstream carrier rockets in service.

[0006] To achieve the above purpose, the utility model embodiment provides a double-channel sealing flange assembly suitable for high-pressure propellant pushing of liquid aircraft, the double-channel sealing flange assembly comprises an upper flange arranged on an upper channel and a lower flange arranged on a lower channel, an upper flange end face of the upper flange and a lower flange end face of the lower flange are in communication to form a top-down flow channel of high-pressure propellant, and the flow channel is used for pushing the high-pressure propellant in the upper channel into the lower channel.

[0007] The double-channel sealing flange assembly further comprises a first sealing installation structure and a first sealing element, the first sealing installation structure is arranged on the upper flange end face and the lower flange end face, and the first sealing element is installed in the first sealing installation structure.

[0008] The double-channel sealing flange assembly further comprises a second sealing installation structure and a second sealing element, the second sealing installation structure is arranged on the upper flange end face and the lower flange end face, and the second sealing element can be installed in the second sealing installation structure.

[0009] The first sealing mounting structure and the second sealing mounting structure are arranged in sequence along a direction perpendicular to and away from an axis of the flow passage.

[0010] The upper flange end surface of the upper flange and the lower flange end surface of the lower flange can be connected to realize communication between the upper passage and the lower passage to form a flow passage for pushing the high-pressure propellant in the upper passage into the lower passage; in the double-seal flange assembly formed by the upper flange and the lower flange, the first sealing member arranged in the inner ring serves as a main seal and can be self-tightened in the first sealing mounting structure, and the second sealing member arranged in the outer ring can be fitted in the second sealing mounting structure and serves as an auxiliary seal, so that the flange structure and the sealing structure are simple, the flange size is relatively small under the same working condition, the manufacturing cost is low, and if the first sealing member arranged in the inner ring fails, the second sealing member arranged in the outer ring can also realize sealing, the sealing efficiency is high, and the sealing reliability can be effectively improved compared with the traditional single-seal. BRIEF DESCRIPTION OF DRAWINGS

[0011] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0012] Figure 1 is a sectional view of the double-seal flange assembly for high-pressure propellant pushing of a liquid aircraft according to an embodiment of the present application;

[0013] Figure 2 is a sectional view of the upper flange 1 according to an embodiment of the present application;

[0014] Figure 3 is a sectional view of the lower flange 2 according to an embodiment of the present application;

[0015] Figure 4 is a sectional view of the pan seal ring 3 according to an embodiment of the present application.

[0016] The signs are represented as:

[0017] 1. Upper flange; 2. Lower flange; 3. Universal seal ring; 4. Graphite ring; 5. Bolt; 6. Flat washer; 7. Spring washer; 8. Nut; 11. Upper flange end face; 21. Lower flange end face; 31. Spring energy storage ring; 32. Jacket; 300. Universal seal ring mounting groove; 400. Graphite ring mounting structure; 500. Fastening assembly; 310. Inner ring wall; 320. Upper top surface; 330. Outer ring wall; 340. Lower bottom surface; 410. Sealing tenon; 420. Sealing mortise. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0019] like Figure 1 As shown, in combination with an embodiment of the present utility model, a double-pass sealing flange assembly suitable for pushing high-pressure propellant of liquid aircraft is provided, the double-pass sealing flange assembly is used for pushing high-pressure propellant in launch vehicles, the double-pass sealing flange assembly includes an upper flange 1 provided on the upper channel and a lower flange 2 provided on the lower channel, the upper flange 1 and the lower flange 2 are both vertically arranged, the upper flange end face 11 of the upper flange 1 and the lower flange end face 21 of the lower flange 2 can be connected to realize connecting the upper channel and the lower channel to form a circulation channel for high-pressure propellant from top to bottom, that is, a leakage channel, the leakage channel is used to push the high-pressure propellant in the upper channel into the lower channel; wherein, the high pressure of the high-pressure propellant refers to ≯20MPa (not more than 20MPa), for a double-pass sealing flange or channel with a diameter of 600mm, 20MPa is a very high pressure, and the flange with this characteristic belongs to a large-diameter high-pressure sealing flange or channel.

[0020] The double-channel sealing flange assembly further includes a first sealing mounting structure and a first sealing member, wherein the first sealing mounting structure is arranged on the upper flange end face 11 and the lower flange end face 21, and the first sealing member is mounted in the first sealing mounting structure. When the upper channel and the lower channel are filled with high-pressure propellant, the first sealing member deforms under the pressure of the high-pressure propellant to achieve a self-tightening seal with the upper flange 1 and the lower flange 2.

[0021] The double-pass sealing flange assembly further includes a second sealing mounting structure and a second sealing member, wherein the second sealing mounting structure is provided with the upper flange end face 11 and the lower flange end face 21, and the second sealing member can be fittedly mounted in the second sealing mounting structure;

[0022] The first sealing mounting structure and the second sealing mounting structure are sequentially arranged along a direction perpendicular to and away from the axis of the flow passage, that is, the first sealing mounting structure is arranged at an inner ring, and the second sealing mounting structure is arranged at an outer ring, and the distance between the inner ring and the axis of the leakage passage is less than the distance between the outer ring and the axis of the leakage passage.

[0023] In the double-channel sealing flange assembly formed by the upper flange 1 and the lower flange 2, the first sealing member arranged at the inner ring serves as the main sealing, and can be self-tightened in the first sealing mounting structure; the second sealing member arranged at the outer ring can be fitted and arranged in the second sealing mounting structure, and serves as the auxiliary sealing. The flange structure is simple, and the sealing structure is also simple. Therefore, the flange size under the same working condition is relatively small, and the manufacturing cost is low. If the first sealing member arranged at the inner ring fails, the second sealing member arranged at the outer ring can still realize sealing, and the sealing efficiency is high. Compared with the traditional single-channel sealing, the sealing reliability can be effectively improved.

[0024] Preferably, as shown in Figure 4 The first sealing member is a universal packing ring 3, which includes a spring energy storage ring 31 and a clamping sleeve 32. The opening direction of the clamping sleeve 32 is consistent with the pushing direction of the high-pressure propellant. When the upper channel and the lower channel are filled with high-pressure propellant, the pressure of the high-pressure propellant is downward, and the clamping sleeve 32 is pressed downward. The opening of the clamping sleeve 32 is downward, and the pressure of the high-pressure propellant forces the opening of the clamping sleeve 32 downward to expand, so as to realize the self-tightening of the universal packing ring 3, which is superior to the sealing combination of the traditional O-ring and graphite ring.

[0025] Preferably, as shown in Figure 2 And Figure 3As shown, the first sealing mounting structure is externally provided with a pan gasket mounting groove 300, which comprises an inner ring wall 310 and an upper top surface 320 belonging to the upper flange end surface 11, and an outer ring wall 330 and a lower bottom surface 340 belonging to the lower flange end surface 21, the inner ring wall 310 is vertically arranged and coaxial with the upper flange 1, the upper top surface 320 is horizontally arranged and connected to the inner ring wall 310, the outer ring wall 330 is vertically arranged and coaxial with the lower flange 2, and the lower bottom surface 340 is horizontally arranged and connected to the outer ring wall 330; the inner ring wall 310 and the outer ring wall 330 are oppositely arranged inside and outside the axis of the leakage passage, and the upper top surface 320 and the lower bottom surface 340 are oppositely arranged vertically; the space formed by the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340 is used for mounting the pan gasket 3; that is, the inner ring wall 310 and the upper top surface 320 are in inverted L shape, the outer ring wall 330 and the lower bottom surface 340 are in positive L shape, and the space formed by the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340 is in a frame shape similar to a Chinese character mouth;

[0026] When the upper passage and the lower passage are filled with high-pressure propellant, under the pressure of the high-pressure propellant, the opening of the jacket 32 is expanded, and the spring energy storage ring 31 is compressed, so that the jacket 32 and the spring energy storage ring 31 can form a self-tight sealing between the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340, and the greater the medium pressure, the tighter the inner ring wall 310, the outer ring wall 330, the upper top surface 320 and the lower bottom surface 340 are pressed, so the greater the self-tight force, the better the sealing effect.

[0027] Preferably, the diameter tolerance of the outer ring wall 330 is 0-+0.08mm; and the diameter tolerance of the inner ring wall 310 is -0.08-0mm. That is, the diameter tolerance of the outer ring wall 330 is a positive tolerance, and the diameter tolerance of the inner ring wall 310 is a negative tolerance of -0.08-0. Through the two tolerances, the compression rate of the pan gasket 3 can be guaranteed to be 20%-30%, that is, the sealing effect can be guaranteed without additional tightening torque.

[0028] Preferably, the spring energy storage ring 31 can be applied to a sealing environment temperature in an atmosphere of -200℃-300℃, and the material of the spring energy storage ring 31 comprises one of the following: cobalt-based alloy steel wire, cobalt-based alloy steel strip, nickel-based alloy steel wire, nickel-based alloy steel strip, 301 austenitic stainless steel wire or 301 austenitic stainless steel strip;

[0029] The jacket 32 can be adapted to the sealed ambient temperature in the temperature range of -200℃ to 300℃, and the material used by the jacket 32 is one of the following: modified polytetrafluoroethylene, ultra-high molecular weight polytetrafluoroethylene, reinforced polytetrafluoroethylene, graphite and glass fiber.

[0030] That is, the panzer 3 can be adapted to the sealed ambient temperature in the temperature range of -200℃ to 300℃, so that the entire double-channel sealing flange assembly of the embodiment can be adapted to the temperature range of -200℃ to 300℃, that is, to the end face sealing working condition of large diameter pipeline, wide temperature range (-200℃ to 300℃), and the sealing ring and flange structure can adapt to sealing under low temperature shrinkage and high temperature expansion, that is, it can be applied to different high pressure propellants with large temperature difference and wide temperature range, such as liquid oxygen kerosene, liquid oxygen methane, liquid hydrogen liquid oxygen. And better than the traditional O-ring and graphite ring sealing combination, because the traditional O-ring and graphite ring sealing combination can only adapt to the sealing of normal temperature propellant in the temperature range of -60℃ to 50℃. Among them, large diameter refers to the diameter ≯600mm (not greater than 600mm), and at the same time, the wall thickness >1mm. For a double-channel sealing flange or channel with a diameter of 600mm, 20MPa is a very high pressure, and the flange with this characteristic belongs to a large-diameter high-pressure sealing flange or channel.

[0031] Preferably, the configuration of the spring energy ring 31 includes one of the following: V-shaped cantilever spring, H-shaped spiral spring, S-shaped coil spring, G-shaped grid spring and L-shaped symmetric spring, which can be selected according to the pressure of high pressure propellant and the gap size between the panzer mounting groove 300 and the graphite ring mounting structure 400.

[0032] Preferably, the second sealing mounting structure is a graphite ring mounting structure 400, the second sealing member is a graphite ring 4, and the graphite ring mounting structure 400 is a mortise and tenon structure, which includes a downward protruding sealing tenon 410 belonging to the upper flange end face 11 and a downward recessed sealing mortise 420 belonging to the upper flange end face 21. The sealing tenon 410 can be vertically embedded into the sealing mortise 420 to form a mortise and tenon connection form with the sealing mortise 420. The mortise and tenon structure is simple in form and convenient to match, and can be installed with the graphite ring 4.

[0033] Preferably, the fastening assembly 500 is further included, which comprises a bolt 5, a flat washer 6, a spring washer 7 and a nut 8, the bolt 5 penetrates the upper flange 1 and the lower flange 2, the head of the bolt 5 is located above the upper flange 1, the spring washer 7 and the flat washer 6 are located on the screw rod of the bolt 5 between the head of the bolt 5 and the upper flange 1, and the nut 8 is located on the screw rod of the bolt 5 below the lower flange 2; the fastening assembly 500 bears a preset tightening torque. Because the universal gasket 3 can be self-tightened and installed, the graphite gasket 4 is installed in the graphite gasket installation structure 400 of the mortise and tenon structure, and when the upper flange 1 and the lower flange 2 are connected together by the fastening assembly 500 after the assembly of the upper flange 1 and the lower flange 2 is completed, the tightening torque of the fastening assembly 500 only needs to connect the upper flange 1 and the lower flange 2 together and force the sealing tenon 410 to press the graphite gasket 4 to compress the graphite gasket 4, so the fastening assembly 500 bears a very small preset tightening torque, which is smaller than the same under the same working condition. Therefore, under the same working condition, the size of the upper flange 1 and the lower flange 2 will be smaller, and the pipe wall of the upper flange 1 and the lower flange 2 will be thinner, so the thin-wall flange can be used, and therefore the double-seal flange assembly of the embodiment of the utility model is suitable for thin-wall flanges. And it is better than the traditional sealing combination of O-ring and graphite gasket, because the tightening torque required by the traditional sealing combination of O-ring and graphite gasket needs to reach 1.5-1.8 times or more of the single-seal, which inevitably leads to a heavy sealing flange structure, high bolt strength requirement, sharp increase in manufacturing cost, low structure efficiency and the like.

[0034] Preferably, the graphite gasket 4 is compressed and installed in the graphite gasket installation structure 400, and the compression rate of the graphite gasket 4 compressed and installed in the graphite gasket installation structure 400 is 20%-30%, which can guarantee the auxiliary sealing effect of the graphite gasket 4.

[0035] By controlling the size of the graphite gasket installation structure 400 and the tightening torque 21-30 N·m of the fastening assembly 500, the compression rate of the graphite gasket 4 can be guaranteed to be 20%-30%, that is, the sealing effect can be guaranteed, wherein the inner diameter of the sealing mortise 420 has a negative tolerance of -0.15 to -0.1 mm, the outer diameter of the sealing mortise 4200 has a positive tolerance of +0.1 to +0.15 mm, the inner diameter of the sealing tenon 410 has a positive tolerance of +0.1 to +0.15 mm, and the outer diameter of the sealing tenon 410 has a negative tolerance of -0.15 to -0.1 mm.

[0036] The gap between the upper flange end surface 11 between the graphite gasket installation structure 400 and the outer wall of the upper flange 1 and the lower flange end surface 21 between the graphite gasket installation structure 400 and the outer wall of the lower flange 2 can be measured by a plug gauge to determine how much the compression rate of the graphite gasket 4 reaches, so as to ensure that the compression rate of the graphite gasket 4 is 20%-30%.

[0037] Preferably, the upper flange end face 11 and the lower flange end face 21 between the pan gasket mounting groove 300 and the graphite gasket mounting structure 400 are provided with a clearance fit, so that the pan gasket 3 can be tightly sealed in the pan gasket mounting groove 300, and the graphite gasket 4 can be tightly sealed in the graphite gasket mounting structure 400.

[0038] The upper flange end face 11 between the pan gasket mounting groove 300 and the inner wall of the upper flange 1, and the lower flange end face 21 between the pan gasket mounting groove 300 and the inner wall of the lower flange 2 are provided with a clearance fit, so that the pan gasket 3 can be tightly sealed in the pan gasket mounting groove 300.

[0039] It should be understood that all the features together in the foregoing detailed description of the embodiments are combined in a single embodiment to simplify the disclosure. Therefore, the appended claims are hereby expressly incorporated into the detailed description, wherein each claim is separately a preferred embodiment of the utility model.

[0040] The above disclosed embodiments are described to enable any person skilled in the art to practice or use the present utility model. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein can be applied to other embodiments without departing from the spirit and scope of the disclosure. Thus, the present disclosure is not intended to be limited to the embodiments described herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0041] The above description includes examples of one or more embodiments. Of course, not all possible combinations of components or methods described above will be described as the description of the above embodiments, but those of ordinary skill in the art should recognize that various embodiments can be further combined and arranged. Therefore, the embodiments described herein are intended to cover all such changes, modifications and variations falling within the scope of the appended claims. In addition, as the term "comprising" is used in the specification or claims, the coverage is similar to the term "including", as explained in the interpretation of "including" as a transitional phrase in the claims. In addition, the use of any one term "or" in the specification or claims is intended to mean "non-exclusive or".

[0042] The above specific embodiments explain the purpose, technical scheme and beneficial effects of the present application in further detail, and it should be understood that the above description is only a specific embodiment of the present application and is not used to limit the protection scope of the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A dual seal flange assembly suitable for use with liquid aircraft high pressure propellant push-pull, characterized in that, The double-channel sealing flange assembly comprises an upper flange (1) arranged on the upper channel and a lower flange (2) arranged on the lower channel, an upper flange end face (11) of the upper flange (1) and a lower flange end face (21) of the lower flange (2) are in communication with each other to form a high-pressure propellant downward flow channel, and the high-pressure propellant in the upper channel is pushed into the lower channel through the flow channel; The double-channel sealing flange assembly further comprises a first sealing installation structure and a first sealing element, the first sealing installation structure is arranged on the upper flange end face (11) and the lower flange end face (21), and the first sealing element is installed in the first sealing installation structure; The double-channel sealing flange assembly further comprises a second sealing installation structure and a second sealing element, the second sealing installation structure is arranged on the upper flange end face (11) and the lower flange end face (21), and the second sealing element is installed in the second sealing installation structure in a close-fitting manner; The first sealing installation structure and the second sealing installation structure are arranged in sequence along a direction perpendicular to and away from the axis of the flow channel.

2. The dual seal flange assembly suitable for use with liquid aircraft high pressure propellant push-pull of claim 1, wherein, The first sealing element is a generic seal ring (3), and the generic seal ring (3) comprises a spring energy storage ring (31) and a clamping sleeve (32), and the opening direction of the clamping sleeve (32) is consistent with the pushing direction of the high-pressure propellant.

3. The dual seal flange assembly suitable for use with liquid aircraft high pressure propellant push-pull of claim 2, wherein, The first sealing installation structure is a generic seal ring installation groove (300), and the generic seal ring installation groove (300) comprises an inner ring wall (310) and an upper top face (320) belonging to the upper flange end face (11), and an outer ring wall (330) and a lower bottom face (340) belonging to the lower flange end face (21); The upper top face (320) and the lower bottom face (340) are arranged in an upper-lower opposite manner; and the space formed by the inner ring wall (310), the outer ring wall (330), the upper top face (320) and the lower bottom face (340) is used for installing the generic seal ring (3); When the upper channel and the lower channel are filled with high-pressure propellant, under the pressure of the high-pressure propellant, the opening of the clamping sleeve (32) is expanded, the spring energy storage ring (31) is compressed, and the clamping sleeve (32) and the spring energy storage ring (31) can form a self-tight sealing between the inner ring wall (310), the outer ring wall (330), the upper top face (320) and the lower bottom face (340).

4. The double-channel sealing flange assembly suitable for high-pressure propellant pushing of a liquid aircraft according to claim 3, wherein The diameter tolerance of the outer ring wall (330) is 0-+0.08 mm; The diameter tolerance of the inner ring wall (310) is -0.08-0 mm.

5. The double-channel sealing flange assembly suitable for high-pressure propellant pushing of a liquid aircraft according to claim 2, wherein The spring energy ring (31) can be applied to a sealed ambient temperature of -200℃ to 300℃, and the material of the spring energy ring (31) includes one of the following: cobalt-based alloy steel wire, cobalt-based alloy steel strip, nickel-based alloy steel wire, nickel-based alloy steel strip, 301 austenitic stainless steel wire or 301 austenitic stainless steel strip; The jacket (32) can be applied to a sealed ambient temperature of -200℃ to 300℃, and the material of the jacket (32) is one of the following: modified polytetrafluoroethylene, ultra-high molecular weight polytetrafluoroethylene, reinforced polytetrafluoroethylene, graphite and glass fiber.

6. The double-channel sealed flange assembly suitable for liquid aircraft high-pressure propellant pushing according to claim 2, wherein, The configuration of the spring energy ring (31) includes one of the following: V-shaped cantilever spring, H-shaped spiral spring, S-shaped coil spring, G-shaped grid spring and L-shaped symmetric spring.

7. The double-channel sealed flange assembly suitable for liquid aircraft high-pressure propellant pushing according to claim 1, wherein, The second sealing mounting structure is a graphite ring mounting structure (400), the second sealing member is a graphite ring (4), the graphite ring mounting structure (400) is a mortise and tenon structure, the mortise and tenon structure includes a downward protruding sealing tenon (410) belonging to the upper flange end face (11) and a downward recessed sealing mortise (420) belonging to the lower flange end face (21), the sealing tenon (410) can be vertically embedded into the sealing mortise (420) to form a mortise and tenon connection form with the sealing mortise (420).

8. The dual seal flange assembly suitable for use with liquid aircraft high pressure propellant push-pull of claim 7, wherein, Further comprising a fastening assembly (500) penetrating through the upper flange (1) and the lower flange (2), the fastening assembly (500) bears a preset tightening torque.

9. The dual seal flange assembly suitable for use with liquid aircraft high pressure propellant push-pull of claim 1, wherein, The second sealing member is compressed and mounted in the second sealing mounting structure, and the compression rate is 20% to 30%.

10. The dual seal flange assembly suitable for use with liquid aircraft high pressure propellant push-pull of claim 1, wherein, The upper flange end face (11) and the lower flange end face (21) between the first sealing mounting structure and the second sealing mounting structure adopt a clearance fit; The upper flange end face (11) between the first sealing mounting structure and the inner wall of the upper flange (1), and the lower flange end face (21) between the first sealing mounting structure and the inner wall of the lower flange (2) adopt a clearance fit.

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