Plugging device for liquid rocket engine ignition chamber flow resistance characteristic test

Abstract

The invention relates to a plugging device for a liquid rocket engine ignition chamber flow resistance characteristic test. The plugging device comprises a tray, a non-metal expansion sealing ring, a metal extrusion structure and a locking nut. The non-metal expansion sealing ring is mounted in the product pipeline, and a boss is designed at the bottom; a bottom boss of the non-metal expansion sealing ring is mounted in an annular groove of the tray; the upper end of the metal extrusion structure is located in the product pipeline, and the lower end of the metal extrusion structure penetrates through an inner hole of the non-metal expansion sealing ring and a tray via hole and then is fixedly connected with the locking nut. The tightening torque is applied to the locking nut, the metal extrusion structure moves downwards, the non-metal expansion sealing ring is extruded, circumferential extrusion expansion of the non-metal expansion sealing ring is achieved, and plugging is achieved. According to the invention, the problem of plugging the light pipe attached with the supporting structure is solved, the sealing ring is fixedly arranged on the inner wall of the pipeline through extrusion expansion, the plugging of the flow channel is realized, and the flow resistance characteristic test of the specific flow channel is further realized.

Description

Technical Field

[0001] This invention belongs to the field of mechanical structure device design and relates to a sealing device for testing the flow resistance characteristics of the ignition chamber of a liquid rocket engine. Background Technology

[0002] The general structure of the liquid rocket engine ignition chamber consists of a medium inlet channel and two medium outlet channels. The medium outlet channels are an axial flow channel and a sandwich flow channel, respectively. The outlet of the axial flow channel is a bare tube without any attached support structure.

[0003] The liquid rocket engine ignition chamber has two outflow channels, requiring the sealing of each channel to conduct flow resistance characteristic tests on the unsealed channel. Traditional sealing devices rely on specific attachment and support structures of the product for fixation and sealing. However, in situations where the ignition chamber lacks suitable leverage points, traditional sealing devices are ineffective. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a sealing device for testing the flow resistance characteristics of the ignition chamber of a liquid rocket engine, so as to realize the sealing of the axial flow channel and the measurement of the flow resistance characteristics of the interlayer flow channel.

[0005] The solution of the present invention is: A sealing device for testing the flow resistance characteristics of the ignition chamber of a liquid rocket engine includes a tray, a non-metallic expansion sealing ring, a metal extrusion structure, and a locking nut. A non-metallic expansion sealing ring is installed inside the product pipeline, and a boss is designed at the bottom of the non-metallic expansion sealing ring; an annular groove is provided on the tray, and the boss at the bottom of the non-metallic expansion sealing ring is installed in the annular groove; the metal extrusion structure is provided with external threads, and the outer diameter of the metal extrusion structure is equal to the inner diameter of the lower surface of the non-metallic expansion sealing ring; a through hole matching the metal extrusion structure is provided on the tray; the upper end of the metal extrusion structure is located inside the product pipeline, and the lower end passes through the inner hole of the non-metallic expansion sealing ring and the through hole of the tray and is fixed to the locking nut. When a tightening torque is applied to the locking nut, the metal extrusion structure moves downward, compressing the non-metallic expansion sealing ring to achieve circumferential expansion and sealing.

[0006] Preferably, the inner wall of the non-metallic expansion sealing ring is a conical surface.

[0007] Preferably, the main body of the metal extrusion structure is a cylindrical segment with a ball head at the top. The ball head and the cylindrical segment are designed as a single unit, and the cylindrical segment is provided with external threads.

[0008] Preferably, the inner conical surface of the non-metallic expansion sealing ring 1 forms a seal with the spherical surface of the metal extrusion structure 4.

[0009] Preferably, the sealing device is used to seal the outlet of the axial flow channel.

[0010] Preferably, the bottom boss of the non-metallic expansion sealing ring is installed in the annular groove with a clearance fit.

[0011] The method for conducting flow resistance characteristic tests using the aforementioned sealing device for testing the flow resistance characteristics of a liquid rocket engine ignition chamber includes: The two media outflow channels in the ignition chamber of the liquid rocket engine are not blocked, and the total flow resistance characteristics of the two media outflow channels are measured. The sealing device is installed at the outlet of the axial flow channel; The flow resistance characteristics of the sandwiched flow channel were obtained by conducting flow resistance characteristic tests. The flow resistance characteristics of the axial flow channel are obtained by subtracting the flow resistance characteristics of the interlayer flow channel from the overall flow resistance characteristics.

[0012] The advantages of this invention compared to the prior art are: The device of this invention can solve the problem of sealing the attached support structure of the light tube. By squeezing and expanding, the sealing ring is installed and fixed to the inner wall of the pipe, thereby sealing the flow channel and realizing the flow resistance characteristic test of a specific flow channel. Attached Figure Description

[0013] Figure 1 A schematic diagram of the ignition chamber structure of a liquid rocket engine; Figure 2 This is a schematic diagram of the sealing device. Detailed Implementation

[0014] The invention will now be further described with reference to the accompanying drawings.

[0015] This invention designs a novel extrusion-type sealing device to complete the flow resistance characteristic test of a specific flow channel in the ignition chamber of a liquid rocket engine. Figure 1 This is a schematic diagram of the ignition chamber structure of a liquid rocket engine.

[0016] The sealing device of the present invention includes a tray 2, a non-metallic expansion sealing ring 1, a metal extrusion structure 4, and a locking nut 3, the structure of which is as follows: Figure 2 As shown.

[0017] The non-metallic expansion sealing ring 1 has a boss at its bottom, which assembles with a groove on the tray 2 to achieve circumferential fixation of the non-metallic expansion sealing ring and prevent slippage during extrusion. The non-metallic expansion sealing ring 1 is placed inside the product pipeline, with the bottom boss acting as a bottom extension structure to protect the bottom surface of the product. The metal extrusion structure 4 has external threads, and its outer diameter is equal to the inner diameter of the lower surface of the non-metallic expansion sealing ring. The tray has a through hole matching the metal extrusion structure. The upper end of the metal extrusion structure is located inside the product pipeline, and its lower end passes through the inner hole of the non-metallic expansion sealing ring and the through hole on the tray before being fixed to a locking nut. The inner wall of the non-metallic expansion sealing ring is conical. The main body of the metal extrusion structure is a cylindrical section with a ball head at the top. The ball head and cylindrical section are designed as a single unit, and the cylindrical section has external threads. The inner conical surface of the non-metallic expansion sealing ring 1 and the ball head surface of the metal extrusion structure 4 form a seal.

[0018] The sealing device is used to seal the outlet of the axial flow channel.

[0019] The locking nut 3 and the external thread of the metal extrusion structure 4 cooperate with each other to apply a tightening torque. The tray limits the non-metallic expansion sealing ring, and the metal extrusion structure moves downward at the same time. By extruding the conical surface of the non-metallic expansion sealing ring, the circumferential extrusion expansion of the non-metallic expansion sealing ring is completed, thus sealing the product flow channel.

[0020] The tray is made of stainless steel, and the inner wall of the sealing ring is conical with a cone angle of 37°.

[0021] The implementation of this invention is as follows: (1) Product 5 is assembled with tray 2 through non-metallic expansion sealing ring 1 to protect the bottom surface of the product; (2) Locking nut 3 and the external thread of metal extrusion structure 4 cooperate with each other, and tray 2 prevents the sealing device from falling off the pipeline. After applying tightening torque, metal extrusion structure 4 achieves axial downward displacement, realizing mutual extrusion of non-metallic expansion sealing ring 1 and metal extrusion mechanism 4; (3) Non-metallic expansion sealing ring 1 is extruded with the inner wall of the pipeline to form a seal, and at the same time, the inner conical surface of non-metallic expansion sealing ring 1 and the ball head surface of metal extrusion structure 4 form a seal to achieve the sealing of the axial flow channel and complete the measurement of the flow resistance characteristics of different flow channels of the product.

[0022] A method for conducting flow resistance characteristic tests using a plugging device includes the following steps: The two media outflow channels in the ignition chamber of the liquid rocket engine are not blocked, and the total flow resistance characteristics of the two media outflow channels are measured. The sealing device is installed at the outlet of the axial flow channel; The flow resistance characteristics of the sandwiched flow channel were obtained by conducting flow resistance characteristic tests. The flow resistance characteristics of the axial flow channel are obtained by subtracting the flow resistance characteristics of the interlayer flow channel from the overall flow resistance characteristics.

[0023] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A blanking device for liquid rocket engine chamber flow resistance characteristic tests, characterized in that: It includes a tray (2), a non-metallic expansion sealing ring (1), a metal extrusion structure (4), and a locking nut (3). The non-metallic expansion sealing ring (1) is installed inside the product pipeline, and the bottom of the non-metallic expansion sealing ring is designed with a boss; the tray (2) is provided with an annular groove, and the bottom boss of the non-metallic expansion sealing ring is installed in the annular groove; the metal extrusion structure (4) is provided with an external thread, and the outer diameter of the metal extrusion structure is equal to the inner diameter of the lower surface of the non-metallic expansion sealing ring. The tray is provided with a through hole that matches the metal extrusion structure. The upper end of the metal extrusion structure is located inside the product pipeline, and the lower end passes through the inner hole of the non-metallic expansion sealing ring and the through hole of the tray and is fixed to the locking nut. When a tightening torque is applied to the locking nut, the metal extrusion structure moves downward, compressing the non-metallic expansion sealing ring to achieve circumferential expansion and sealing.

2. A closure device for use in flow resistance characteristic tests of a liquid rocket engine ignition chamber according to claim 1, characterized in that: The inner wall of the non-metallic expansion sealing ring is a conical surface.

3. A closure device for use in flow resistance characteristic testing of a liquid rocket engine ignition chamber according to claim 1, characterized in that: The main body of the metal extrusion structure is a cylindrical section with a ball head at the top. The ball head and the cylindrical section are designed as a single unit, and the cylindrical section is provided with external threads.

4. A sealing device for testing the flow resistance characteristics of an ignition chamber in a liquid rocket engine according to claim 2, characterized in that: The inner conical surface of the non-metallic expansion sealing ring 1 forms a seal with the spherical surface of the metal extrusion structure 4.

5. A sealing device for testing the flow resistance characteristics of an ignition chamber in a liquid rocket engine according to claim 1, characterized in that: The sealing device is used to seal the outlet of the axial flow channel.

6. The sealing device for testing the flow resistance characteristics of the ignition chamber of a liquid rocket engine according to claim 1, characterized in that: The bottom boss of the non-metallic expansion sealing ring is installed in the annular groove with a clearance fit.

7. A method for conducting flow resistance characteristic tests using a sealing device for testing the flow resistance characteristics of an ignition chamber of a liquid rocket engine as described in any one of claims 1-6, characterized in that, include: The two media outflow channels in the ignition chamber of the liquid rocket engine are not blocked, and the total flow resistance characteristics of the two media outflow channels are measured. The sealing device is installed at the outlet of the axial flow channel; The flow resistance characteristics of the sandwiched flow channel were obtained by conducting flow resistance characteristic tests. The flow resistance characteristics of the axial flow channel are obtained by subtracting the flow resistance characteristics of the interlayer flow channel from the overall flow resistance characteristics.

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