Air-tight tool and sealing device for exhaust pipe of liquid rocket engine

Abstract

The utility model provides a liquid rocket engine exhaust pipe airtight tool and a sealing device. The airtight tool comprises a supporting cover (1), a sliding block (2) arranged below the supporting cover (1) and a sealing seat (4) arranged below the sliding block (2). The sliding block (2) is in bolted connection with the supporting cover (1); the sealing seat (4) is connected with the supporting cover (1) through a shaft rod (3); the outer end of the sliding block (2) is in contact with the inner wall of the exhaust pipe of the rocket engine; the side face of the sealing seat (4) makes contact with the inner wall of the rocket engine exhaust pipe. A groove is formed in the outer side of the sealing seat (4), and a sealing ring is arranged in the groove. And the safety in the use process is ensured. The airtight tool for the exhaust pipe is convenient to disassemble, if the shape of the exhaust pipe is changed in the iteration process of an engine, the use requirement can be met only by adjusting part of parts in the tool, and the production efficiency of the engine is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of airtight tooling devices, in particular to an airtight tooling device and a sealing device for an exhaust pipe of a liquid rocket engine. Background Art

[0002] The turbine exhaust pipe of a liquid rocket engine is a key component of a pumped-type open-cycle engine. During the engine assembly test process, hydraulic and airtightness tests must be performed. During these tests, airtight fixtures are required to ensure the exhaust pipe's tightness. Due to the unique structural shape of the exhaust pipe, sealing the exhaust pipe becomes a scientific challenge, and different rocket engine models require different airtight fixtures for the exhaust pipe. Existing rocket engine exhaust pipe airtight fixtures are of the plug-in type, with a flange at the exhaust pipe outlet. Their large size and weight make installation time-consuming and labor-intensive, resulting in a lengthy preparation process for airtightness testing. Furthermore, due to significant limitations imposed by the engine's structure, installation is sometimes impossible due to limited space. These issues significantly hinder the rapid, standardized, and low-cost development of liquid rocket engines, impacting the overall engine production schedule.

[0003] In summary, the existing technology has the following problems: the existing rocket engine exhaust pipe airtight tooling is installed outside the rocket engine exhaust pipe, which is time-consuming and labor-intensive to install, resulting in a long airtight test preparation process and low efficiency. Utility Model Content

[0004] The utility model provides an airtight tooling and a sealing device for a liquid rocket engine exhaust pipe, and aims to solve the problem of low installation efficiency of the airtight tooling for the rocket engine exhaust pipe.

[0005] To achieve the above-mentioned object, on the one hand, the utility model provides an airtight tooling for a liquid rocket engine exhaust pipe, comprising: a support cover, a first locking mechanism, a second locking mechanism, a slider, and a sealing seat provided below the slider;

[0006] The slider is movably mounted on the support cover, and the first locking mechanism can lock the slider and the support cover;

[0007] The sealing seat is connected to the support cover via a second locking mechanism; the outer end of the slider is used to contact the inner wall of the liquid rocket engine exhaust pipe; the side surface of the sealing seat is used to seal and contact the inner wall of the rocket engine exhaust pipe;

[0008] The support cover and the sealing seat can move relative to each other along the second locking mechanism and can achieve position locking.

[0009] Specifically, the second locking mechanism includes: a shaft and a nut. The shaft passes through the sealing seat and the support cover. The nuts are provided at both ends of the shaft to fix the sealing seat and the support cover.

[0010] Specifically, the first locking mechanism includes: a slide groove and a first bolt, wherein the support cover is provided with a slide groove, and the slider can move along the slide groove; the slide groove is provided with a first bolt, and the first bolt passes through the slide groove and is fixed to the slider.

[0011] Specifically, the slide grooves are through holes, are in the shape of long strips and are evenly distributed on the support cover.

[0012] Specifically, a groove is provided on the outer side of the sealing seat, and a first sealing ring is provided in the groove.

[0013] Specifically, the support cover is provided with a bolt hole, and the upper end of the slider is provided with a limiting hole corresponding to the bolt hole;

[0014] The first locking mechanism includes a second bolt installed in the bolt hole, and the second bolt can be partially inserted into the limiting hole.

[0015] Specifically, the number of the sliders and the number of the sliding grooves are both N, where N≥1.

[0016] Specifically, the shaft is provided with an annular groove, and a second sealing ring sealedly connected to the sealing seat is provided in the annular groove.

[0017] Specifically, the support cover is in the shape of a triangle, a circle or a cross.

[0018] On the other hand, the present invention provides a liquid rocket engine exhaust pipe sealing structure, comprising a liquid rocket engine exhaust pipe and the aforementioned liquid rocket engine exhaust pipe airtight tooling, wherein the airtight tooling is installed in the contraction-expansion section of the liquid rocket engine exhaust pipe;

[0019] The pipe wall of the contraction-expansion section of the exhaust pipe is convex inward; the sliding block and the sealing seat are respectively in contact with the inner part of the contraction-expansion section, and the contraction-expansion section is clamped under the drive of the second locking mechanism.

[0020] This utility model achieves fixed fixation by adjusting the travel of the slider in the chute. Its structure is ingenious and reliable, ensuring safety during use. The exhaust pipe airtight fixture is easy to disassemble. If the exhaust pipe shape changes during engine iterations, only some parts of the fixture need to be adjusted to meet the requirements. This improves engine production efficiency and reduces costs, which is of great significance to the commercialization of rocket engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the structure of an airtight tooling for a liquid rocket engine exhaust pipe according to an embodiment of the present utility model;

[0022] Figure 2 This is a schematic cross-sectional structure diagram of an airtight tooling for a liquid rocket engine exhaust pipe according to an embodiment of the present utility model.

[0023] Description of Figure Numbers:

[0024] 1. Support cover; 2. Slider; 3. Shaft; 4. Sealing seat; 5. Second bolt; 6. First bolt; 7. Upper nut; 8. Lower nut; 9. Flat washer; 10. Exhaust pipe; 101. Contraction and expansion section; 11. Slide; 41. Groove. DETAILED DESCRIPTION

[0025] 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.

[0026] The present invention provides a liquid rocket engine exhaust pipe airtight tooling, such as Figure 1 As shown, including:

[0027] A support cover 1, a first locking mechanism, a second locking mechanism, a slider 2, and a sealing seat 4 disposed below the slider 2;

[0028] The slider 2 is movably mounted on the support cover 1, and the first locking mechanism can lock the slider 2 with the support cover 1; the sealing seat 4 is arranged below the slider 2; the slider 2 is bolted to the support cover 1; the support cover 1 is triangular, circular or cross-shaped; the number of sliders 2 is N, and N ≥ 1. Preferably, N is 3, N is 5, such as Figure 1 As shown, a plurality of slide blocks 2 are distributed along the circumferential direction.

[0029] The sealing seat 4 is connected to the support cover 1 through the shaft 3, and the shaft 3 passes through the sealing seat 4. In one embodiment, an annular groove is provided on the shaft 3, and the annular groove is provided at the position where the shaft 3 contacts the sealing seat 4. A second sealing ring is provided in the annular groove and is sealed with the sealing seat 4. The shaft 3 and the sealing seat 4 are sealed by the second sealing ring. Preferably, the number of annular grooves is 1 or 2. The support cover 1 and the sealing seat 4 can move relative to each other along the shaft 3, and the second locking mechanism can drive the sealing seat 4 and the support cover 1 to be relatively close, such as Figure 2As shown, the slider 2 moves toward the sealing seat 4 together with the support cover 1. When the slider 2 and the sealing seat 4 respectively contact the contraction and expansion section of the exhaust pipe 10, the contraction and expansion section is clamped. At the same time, the sealing seat 4 is sealed and matched with the contraction and expansion section.

[0030] The outer end of the slider 2 contacts the inner wall of the liquid rocket engine exhaust pipe; the wall of the contraction and expansion section 101 of the exhaust pipe 10 is convex inward, the outer end of the slider 2 contacts the wall of the contraction and expansion section 101 of the exhaust pipe 10, and the side of the sealing seat 4 is in sealing contact with the inner wall of the rocket engine exhaust pipe; the outer wall of the sealing seat 4 is annular, and a groove 41 is provided on the outer side of the sealing seat 4, and a first sealing ring is provided in the groove 41, and the first sealing ring is used to form a seal with the inner wall of the rocket engine exhaust pipe. A slide groove 11 is provided on the support cover 1, and the slider 2 can move along the slide groove 11 to realize the movement of the slider 2 relative to the support cover. The state of the airtight tooling after installation is completed is as follows. Figure 2 As shown, the outer contour of the slider 2 is greater than the minimum of the contraction-expansion section. During installation, the slider 2 needs to be loaded into the opening of the exhaust pipe 10, and the slider 2 is moved inwardly so that the slider can be installed in place during installation.

[0031] The second locking mechanism includes: a shaft 3 and a nut.

[0032] like Figure 2 As shown, the outer wall of the slider 2 contacts the inner wall of the contraction-expansion section 101 of the exhaust pipe 10. Preferably, the outer wall of the slider 2 is directed in the direction of the sealing seat 4 (ie Figure 2 The sealing seat 4 and the slider 2 cooperate to clamp the contraction-expansion section together, thereby ensuring the sealing effect between the sealing seat 4 and the inner wall of the contraction-expansion section.

[0033] A bolt hole is provided on the support cover 1, and a limiting hole corresponding to the bolt hole is provided on the upper end of the slider 2; the first locking mechanism includes: a slide groove 11 and a first bolt 6, wherein the support cover 1 is provided with a slide groove 11, and the slider 2 can move along the slide groove 11; a first bolt 6 is provided in the slide groove 11, and the first bolt 6 passes through the slide groove 11 and is fixed to the slider 2.

[0034] The first locking mechanism also includes a second bolt 5 mounted in the bolt hole, which can be partially inserted into the stopper hole. The bolt hole is located near the edge of the support cover 1. A slide slot 11 extends through the support cover 1. A first bolt 6 is disposed in the slide slot 11 and is secured to the slider 2 through the slide slot 11. The number of slide slots 11 is N, where N ≥ 1; preferably, N is 3 or 5.

[0035] During installation, if Figure 2As shown, first pass the first bolt 6 through the slide groove 11 and fix it to the slider 2, while allowing the first bolt 6 to slide in the slide groove 11, move the slider 2 to contact the inner wall of the rocket engine exhaust pipe, and the upper end of the slider 2 is provided with a limiting hole corresponding to the bolt hole. Move the slider 2 so that the bolt hole overlaps with the limiting hole, insert the second bolt 5 into the bolt hole, and partially insert the second bolt 5 into the limiting hole, thereby limiting and locking the slider 2. Tighten the lower nut 8 at the lower end of the shaft 3 to increase the sealing force and compression. Set a flat gasket 9 between the lower nut 8 and the sealing seat 4, so that the force area can be increased and the pressure can be reduced. Tighten the upper nut 7 at the upper end of the shaft 3 to press and fix the support cover 1 and the slider 2.

[0036] This utility model achieves fixed fixation by adjusting the travel of the slider in the chute. Its structure is ingenious and reliable, ensuring safety during use. The exhaust pipe airtight fixture is easy to disassemble. If the exhaust pipe shape changes during engine iterations, only some parts of the fixture need to be adjusted to meet the requirements. This improves engine production efficiency and reduces costs, which is of great significance to the commercialization of rocket engines.

[0037] The slider's travel in the slot is adjusted to meet the required fixation requirements. The ingenious and reliable structure ensures safety during use. The nut installed on the shaft controls the sealing force and compression of the silicone seal ring, improving the product's sealing performance.

[0038] The present invention provides a liquid rocket engine exhaust pipe airtight tooling, such as Figure 2 As shown, the airtight tooling is installed in the contraction and expansion section of the exhaust pipe 10. Figure 1 and Figure 2 As shown, it includes a support cover 1, a slider 2 and a sealing seat 4. The slider 2 is connected to the support cover 1 through a first bolt 6. A first sealing ring is installed in the groove 41 of the sealing seat 4.

[0039] The embodiment of the present invention also provides a liquid rocket engine exhaust pipe sealing device, which is installed in the contraction and expansion section of the liquid rocket engine exhaust pipe and includes the aforementioned liquid rocket engine exhaust pipe airtight tooling. The pipe wall of the contraction and expansion section of the exhaust pipe 10 is convex inward, and the exhaust pipe 10 is sealed and connected to the liquid rocket engine exhaust pipe airtight tooling. First, the position of the liquid rocket engine exhaust pipe 10 is fixed, and the slider 2 is moved to the housing limit position through the slide groove of the support cover 1. The second bolt 5 is installed. After confirming that the position of the support cover 1 is stable, the sealing seat 4 is passed through the shaft 3. The sealing seat 4 is tightly fitted inside the exhaust pipe 10 by tightening the lower nut 8, and the throat of the exhaust pipe 10 can be sealed. The tooling is installed as a whole inside the exhaust pipe, and the tooling body is fastened and installed with bolts. The installation structure is stable and easy to disassemble, and the sealing performance is reliable.

[0040] like Figure 1and Figure 2 As shown, the fixing device at the upper end of the airtight tooling includes a support cap 1 and a slider 2. The support cap 1 can be processed into various shapes, such as circular or cross-shaped. The number of sliders 2 can be increased according to usage, and the angle between the straight section and the oblique side of the slider 2 can be adjusted according to the inner surface of the exhaust pipe 10. The diameter of the shaft 3 can be increased or decreased according to the operating pressure.

[0041] like Figure 1 As shown, the lower portion of the shaft 3 is machined with a groove 41, which seals against the sealing seat 4 via a sealing ring within the groove 41. An upper nut 7 is mounted on the shaft 3 to retain the support cover 1. The sealing seat 4 has been lightened to facilitate installation. The fixing mechanism of this airtight fixture uses screws, and the sealing structure is a silicone sealing ring. All components are completely removable for easy maintenance or replacement.

[0042] The utility model has the following beneficial effects:

[0043] This utility model achieves fixed fixation by adjusting the travel of the slider in the chute. Its structure is ingenious and reliable, ensuring safety during use. The exhaust pipe airtight fixture is easy to disassemble. If the exhaust pipe shape changes during engine iterations, only some parts of the fixture need to be adjusted to meet the requirements. This improves engine production efficiency and reduces costs, which is of great significance to the commercialization of rocket engines.

[0044] The slider's travel in the slot is adjusted to meet the required fixation requirements. The ingenious and reliable structure ensures safety during use. The nut installed on the shaft controls the sealing force and compression of the silicone seal ring, improving the product's sealing performance.

[0045] The above description is merely an illustrative embodiment of the present invention and is not intended to limit the scope of the present invention. The various components of the present invention may be combined with each other without conflict, and any equivalent changes and modifications made by a person skilled in the art without departing from the concept and principles of the present invention shall fall within the scope of protection of the present invention.

Claims

1. A liquid rocket engine exhaust pipe airtight tooling, characterized in that: include: A support cover (1), a first locking mechanism, a second locking mechanism, a slider (2), and a sealing seat (4) arranged below the slider (2); The slider (2) is movably mounted on the support cover (1), and the first locking mechanism can lock the slider (2) and the support cover (1); The sealing seat (4) is connected to the support cover (1) via a second locking mechanism; the outer end of the slider (2) is used to contact the inner wall of the liquid rocket engine exhaust pipe; the side surface of the sealing seat (4) is used to seal and contact the inner wall of the rocket engine exhaust pipe; The support cover (1) and the sealing seat (4) can move relative to each other along the second locking mechanism and can achieve position locking.

2. The liquid rocket engine exhaust pipe airtight tooling according to claim 1, characterized in that: The second locking mechanism comprises: a shaft (3) and a nut, the shaft (3) passing through the sealing seat (4) and the support cover (1), and the nuts are arranged at both ends of the shaft (3) for fixing the sealing seat (4) and the support cover (1).

3. The liquid rocket engine exhaust pipe airtight tooling according to claim 1, characterized in that: The first locking mechanism comprises: a slide groove (11) and a first bolt (6), wherein the support cover (1) is provided with a slide groove (11), and the slider (2) can move along the slide groove (11); the slide groove (11) is provided with a first bolt (6), and the first bolt (6) passes through the slide groove (11) and is fixed to the slider (2).

4. The liquid rocket engine exhaust pipe airtight tooling according to claim 3, characterized in that: The sliding grooves (11) are through holes, and the sliding grooves (11) are in the shape of long strips and are evenly distributed on the support cover (1).

5. The liquid rocket engine exhaust pipe airtight tooling according to claim 1, characterized in that: A groove (41) is provided on the outside of the sealing seat (4), and a first sealing ring is provided in the groove (41).

6. The liquid rocket engine exhaust pipe airtight tooling according to claim 3, characterized in that: The support cover (1) is provided with a bolt hole, and the upper end of the slider (2) is provided with a limiting hole corresponding to the bolt hole; The first locking mechanism includes a second bolt installed in the bolt hole, and the second bolt can be partially inserted into the limiting hole.

7. The liquid rocket engine exhaust pipe airtight tooling according to claim 3, characterized in that: The number of the sliders (2) and the number of the chute (11) are both N, where N≥1.

8. The liquid rocket engine exhaust pipe airtight tooling according to claim 2, characterized in that: The shaft (3) is provided with an annular groove, and a second sealing ring is provided in the annular groove and is sealedly connected to the sealing seat (4).

9. The liquid rocket engine exhaust pipe airtight tooling according to claim 1, characterized in that: The support cover (1) is triangular, circular or cross-shaped.

10. A liquid rocket engine exhaust pipe sealing structure, characterized in that: It comprises a liquid rocket engine exhaust pipe (10) and a liquid rocket engine exhaust pipe airtight tooling according to any one of claims 1 to 9, wherein the airtight tooling is installed in the contraction-expansion section of the liquid rocket engine exhaust pipe (10); The wall of the contraction-expansion section of the exhaust pipe (10) is convex inward; the slider (2) and the sealing seat (4) are respectively in contact with the inside of the contraction-expansion section, and the contraction-expansion section is clamped under the driving of the second locking mechanism.

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