A liquid rocket engine throat air tightness detection device

Abstract

This application provides a liquid rocket engine throat airtightness detection device, comprising: a tooling main rod, an inner plate, an outer plate, a fastening nut, and a sealing ring; the inner plate is disposed inside the engine throat; the tooling main rod passes through the inner plate; the tooling main rod has an air inlet and an airflow channel; the airflow channel communicates with the air inlet; the air inlet communicates with the engine throat cavity; the outer plate is disposed parallel to the inner plate and is sleeved on the tooling main rod, with the outer peripheral wall of the outer plate sealingly fitted to the inner wall of the engine nozzle expansion section; the fastening nut is threadedly connected to the tooling main rod, and the fastening nut is located on the side of the outer plate away from the inner plate; the sealing ring is disposed at the connection between the outer plate and the tooling main rod; when the fastening nut is rotated, the outer plate moves along the axial direction of the tooling main rod. This device has a stable structure, high sealing reliability, and can identify and eliminate potential leakage risks in the engine throat in advance, improving the sealing assurance capability during engine testing and flight.

Description

Technical Field

[0001] This application relates to the field of rocket engine technology, and in particular to a throat airtightness detection device for a liquid rocket engine. Background Technology

[0002] Liquid rocket engines operate under extreme high temperatures, high pressures, and strong vibrations, making their sealing reliability crucial to engine safety, service life, and mission success rates. Due to the engine's complex overall structure and numerous connection interfaces, even a minor leak can lead to catastrophic consequences such as seal erosion, propellant leakage, or even deflagration under the influence of high-temperature combustion gases. Therefore, after engine assembly and process testing, conducting specialized airtightness tests, especially on the throat region which experiences the heaviest heat load, is a critical step in ensuring engine flight reliability. However, current sealing testing devices for the throat of liquid rocket engines still face numerous technical limitations.

[0003] For example, the existing patent publication number CN219734630U proposes a nozzle sealing plug, which can enable rapid airtightness checks on the engine. However, its structural design lacks an effective external force fixing device, making it prone to problems such as incomplete sealing and inaccurate test results. In addition, some engine models develop carbon deposits in the throat area after testing, making it difficult for rubber-based sealing structures to effectively adhere to the sealing surface, severely limiting the applicability and versatility of this device.

[0004] Another patent, CN120287230A, proposes a liquid rocket engine airtight clamp. It improves the stability of the device by setting auxiliary structures such as support plates and springs, but still has significant problems: First, the airtightness test pipeline is long and has many transition points, which can easily lead to poor sealing at the transition points, resulting in the risk of false detection or missed detection; Second, the device has a complex structure and many parts, which can easily cause parts to fall off and remain inside the engine during installation or disassembly, potentially causing serious accidents such as structural damage or even explosion during ignition.

[0005] Therefore, the urgent technical problem to be solved is that the existing liquid rocket engine throat airtightness detection device has low sealing reliability, cannot identify and eliminate potential leakage risks in the engine throat in advance, and has low sealing guarantee capability during engine testing and flight. Utility Model Content

[0006] The purpose of this application is to provide a liquid rocket engine throat airtightness detection device. The device has a stable structure, high sealing reliability, can identify and eliminate potential leakage risks in the engine throat in advance, and improve the sealing guarantee capability during engine testing and flight.

[0007] To achieve the above objectives, this application provides a liquid rocket engine throat airtightness detection device, comprising: a tooling main rod, an inner plate, an outer plate, a fastening nut, and a sealing ring; the inner plate is disposed on the inner side of the engine throat; the tooling main rod passes through the inner plate; the tooling main rod has an air inlet and an airflow channel; the airflow channel communicates with the air inlet; the air inlet communicates with the engine throat cavity; the outer plate is disposed parallel to the inner plate, and the outer plate is sleeved on the tooling main rod, the outer peripheral wall of the outer plate being sealed and fitted against the inner wall of the engine nozzle expansion section; the fastening nut is threadedly connected to the tooling main rod, and the fastening nut is located on the side of the outer plate away from the inner plate; the sealing ring is disposed at the connection between the outer plate and the tooling main rod; when the fastening nut is rotated, the outer plate moves along the axial direction of the tooling main rod.

[0008] As described above, the liquid rocket engine throat airtightness detection device includes a tooling main rod comprising a main rod, a limiting protrusion, and an airtightness detection head, wherein the limiting protrusion and the airtightness detection head are located at both ends of the main rod; the limiting protrusion is limited to the inner plate on the side away from the outer plate; a rubber pad is provided between the limiting protrusion and the inner plate; the outer periphery of the main rod has an installation thread, which is threadedly connected to the fastening nut.

[0009] As described above, in the liquid rocket engine throat air tightness detection device, the air inlet and the airflow channel are disposed on the main rod; the air inlet is disposed perpendicular to the axis of the main rod; the airflow channel is disposed along the axis of the main rod; the air tightness detection head has an air tightness detection hole inside; the air tightness detection hole is connected to the end of the airflow channel away from the air inlet.

[0010] In the liquid rocket engine throat airtightness detection device described above, the inner plate is in the shape of a truncated circular plate.

[0011] As described above, in the liquid rocket engine throat airtightness detection device, the outer plate is circular; a rubber sealing gasket is provided on the outer peripheral edge of the outer plate; the rubber sealing gasket is disposed between the outer plate and the inner wall of the engine throat.

[0012] The liquid rocket engine throat airtightness detection device as described above, wherein the inner plate has an inner plate through hole; the outer plate has a sealing through hole; and the tooling main rod passes through the inner plate through hole and the sealing through hole.

[0013] As described above, in the liquid rocket engine throat airtightness detection device, the outer plate has an outer plate boss; the interior of the outer plate boss is a sealed through hole; the tooling main rod passes through the sealed through hole of the outer plate boss and is sealed to the inner wall of the through hole by a sealing ring.

[0014] In the liquid rocket engine throat airtightness detection device described above, the sealing ring comprises two rings; the two sealing rings are spaced apart along the axial direction of the main rod of the tooling.

[0015] In the liquid rocket engine throat air tightness detection device described above, the outer wall of the tooling main rod is provided with a sealing groove; the sealing groove is located below the air inlet; and a sealing ring is installed in the sealing groove.

[0016] In the liquid rocket engine throat airtightness detection device described above, the cross-section of the outer plate is trapezoidal.

[0017] The beneficial effects achieved by this application are as follows:

[0018] (1) The outer plate of this application is screwed in by tightening the fastening nut, and the rubber sealing gasket set on the outer periphery edge of the outer plate is compressed and deformed, so as to fully fit and seal the detection device with the inner wall of the engine nozzle.

[0019] (2) The dynamic seal between the sealing through hole in the center of the outer plate and the sealing ring between the tooling main rod isolates the engine throat from the outside atmosphere into two spaces, which is more conducive to the airtightness inspection of the engine throat.

[0020] (3) The air tightness detection device can be installed by screwing in the fastening nut, which is convenient.

[0021] (4) This application simplifies the components, and the device includes a tooling main rod, an inner plate, an outer plate, a fastening nut, and a sealing ring. This simplifies the number of components and facilitates rapid disassembly and testing. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0023] Figure 1 This is a perspective view of a liquid rocket engine throat airtightness detection device according to an embodiment of this application.

[0024] Figure 2 This is a cross-sectional view of a liquid rocket engine throat airtightness detection device according to an embodiment of this application.

[0025] Figure 3 This is a schematic diagram of an airtightness detection device for the throat of a liquid rocket engine according to an embodiment of this application.

[0026] Reference numerals: 1-Main rod of tooling; 2-Inner plate; 3-Outer plate; 4-Fasting nut; 5-Sealing ring; 6-Main valve of engine throat; 7-Engine throat cavity; 8-Engine throat; 9-Engine nozzle expansion section; 11-Main rod; 12-Limiting protrusion; 13-Air tightness detection head; 111-Rubber gasket; 112-Air inlet; 113-Air tightness detection hole; 114-Airflow channel; 115-Sealing groove; 116-Mounting thread; 211-Through hole of inner plate; 311-Rubber sealing gasket; 312-Sealing through hole; 313-Outer plate boss; 611-Main valve inlet. Detailed Implementation

[0027] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0028] like Figure 1-3 As shown, this application provides a liquid rocket engine throat airtightness testing device. This testing device is installed at the throat of the rocket engine and includes: a tooling main rod 1, an inner plate 2, an outer plate 3, a fastening nut 4, and a sealing ring 5. The inner plate 2 is disposed inside the engine throat 8. The tooling main rod 1 passes through the inner plate 2. The tooling main rod 1 has an air inlet 112 and an airflow channel 114. The airflow channel 114 communicates with the air inlet 112. The air inlet 112 communicates with the engine throat cavity 7. The outer plate 3 is arranged parallel to the inner plate 2 and is sleeved on the tooling main rod 1. The outer peripheral wall of the outer plate 3 is sealed and fitted to the inner wall of the engine expansion section nozzle. The space enclosed by the outer plate 3, the inner plate 2, and the inner wall of the engine throat 8 communicates with the engine throat cavity 7. The fastening nut 4 is threadedly connected to the tooling main rod 1, and the fastening nut 4 is located on the side of the outer plate 3 away from the inner plate 2. The sealing ring 5 is installed at the connection between the outer plate 3 and the main tooling rod 1 to achieve a sealed connection between the outer plate 3 and the main tooling rod 1. When the fastening nut 4 is rotated, the outer plate 3 moves along the axial direction of the main tooling rod 1. Rotating the fastening nut 4 can change the distance between the outer plate 3 and the inner plate 2, so that the outer plate 3 fits tightly against the inner wall of the engine nozzle expansion section 9.

[0029] In a specific embodiment of this utility model, after the rocket engine is assembled, a small amount of gas leaks out from the main valve 6 at the engine throat after it is closed. This gas enters the space between the inner plate 2 and the outer plate 3 through the engine throat cavity 7, and then flows into the airflow channel 114 through the air inlet 112. The function of this device is to collect the gas leaking from the main valve 6 at the engine throat to check whether the leakage rate (a physical quantity measuring the degree of leakage) of the engine throat meets the requirements. The required leakage rate varies depending on the type of engine.

[0030] like Figure 3 As shown, the engine throat 8 has an engine throat main valve 6 on the side away from the engine nozzle expansion section 9. The engine throat main valve 6 has a main valve inlet 611 and is connected to the engine throat cavity 7. Gas is introduced into the engine throat main valve 6 from the main valve inlet 611. The gas enters the engine throat cavity 7 through the engine throat main valve 6, and the gas in the engine throat cavity 7 enters the space between the inner plate 2 and the outer plate 3.

[0031] This invention can change the distance between the outer plate 3 and the inner plate 2 by adjusting the relative position of the fastening nut 4 and the tooling main rod 1. It can be adapted to be installed in the throat of liquid rocket engines of various models and operating conditions, thus making it suitable for airtightness testing of the throat of liquid rocket engines of various models and operating conditions. While ensuring the accuracy of airtightness testing, it also improves operational safety and system versatility.

[0032] like Figure 1 and 2 As shown, the tooling main rod 1 includes a main rod 11, a limiting protrusion 12, and an airtightness detection head 13. The main rod 11, the limiting protrusion 12, and the airtightness detection head 13 are integrally formed. The limiting protrusion 12 and the airtightness detection head 13 are located at both ends of the main rod 11. The limiting protrusion 12 protrudes from the main rod 11. The limiting protrusion 12 is limited on the side of the inner plate 2 away from the outer plate 3. A rubber pad 111 is provided between the limiting protrusion 12 and the inner plate 2. The rubber pad 111 facilitates installation and buffering. The outer periphery of the main rod 11 has an installation thread 116, which is threadedly connected to the fastening nut 4.

[0033] like Figure 1 As shown, the air inlet 112 is located on the main rod 11 and between the inner plate 2 and the outer plate 3. The air inlet 112 is connected to the space between the inner plate 2 and the outer plate 3, so that the gas between the inner plate 2 and the outer plate 3 can enter the air inlet 112.

[0034] like Figure 1 and 2As shown, an air inlet 112 and an airflow channel 114 are provided on the main rod 11. The air inlet 112 is perpendicular to the axis of the main rod 11 and extends through the main rod 11 along a direction perpendicular to the axis. The airflow channel 114 is arranged along the axis of the main rod 11, with one end connected to the air inlet 112 and the other end extending to the airtightness detection head 13. The airflow channel 114 is connected to the airtightness detection hole 113 of the airtightness detection head 13. The airtightness detection head 13 has an airtightness detection hole 113 inside. The airtightness detection hole 113 is connected to the end of the airflow channel 114 away from the air inlet 112. The airtightness detection head 13 is used to insert into a beaker containing an alcohol solution for airtightness testing. The airtightness detection channels (air inlet 112 and airflow channel 114) are integrated with the tooling main rod 1, avoiding the risk of gas leakage caused by channel transitions, shortening the ventilation path length, and increasing the accuracy of airtightness testing.

[0035] like Figure 2 As shown, the air inlet 112 is connected to the space between the inner plate 2 and the outer plate 3. Gas from the space between the inner plate 2 and the outer plate 3 can enter the air inlet 112, and then enter the airflow channel 114 from the air inlet 112. The gas in the airflow channel 114 enters the airtightness detection hole 113.

[0036] like Figure 1 As shown, the inner plate 2 is in the shape of a truncated circular plate. The inner plate 2 is formed by longitudinally cutting off a circular plate from both sides. The two transverse sides of the inner plate 2 are arc surfaces, which fit against the inner wall of the rocket engine nozzle, while the two longitudinal sides are flat surfaces, which do not contact the inner wall of the rocket engine nozzle, and form a gap between the flat surface and the inner wall of the rocket engine nozzle that allows gas to pass through.

[0037] like Figure 1 and 2 As shown, the outer plate 3 is circular; a rubber sealing gasket 311 is provided on the outer periphery of the outer plate 3; the rubber sealing gasket 311 is provided between the outer plate 3 and the inner wall of the engine nozzle expansion section 9, so as to facilitate the outer plate 3 to fit and seal with the inner wall of the engine nozzle expansion section 9.

[0038] like Figure 2 As shown, the inner plate 2 has an inner plate through hole 211; the outer plate 3 has a sealing through hole 312; the tooling main rod 1 passes through the inner plate through hole 211 and the sealing through hole 312, so that the tooling main rod 1 passes through the inner plate 2 and the outer plate 3. The engine throat 8 has a minimum diameter section. The inner plate 2 is limited to one side of the minimum diameter section of the engine throat 8, and the outer plate 3 is limited to the other side of the minimum diameter section of the engine throat 8. The device is installed stably and reliably.

[0039] like Figure 1As shown, the outer plate 3 has an outer plate boss 313, which is concentric with the outer plate 3; the interior of the outer plate boss 313 is a sealing through hole 312; the tooling main rod 1 passes through the sealing through hole 312 of the outer plate boss 313 and is sealed to the inner wall of the sealing through hole 312 by a sealing ring 5.

[0040] like Figure 2 As shown, the sealing ring 5 includes two rings; the two sealing rings 5 ​​are spaced apart along the axial direction of the main rod 1 of the tooling. By setting two sealing rings 5 ​​between the main rod 1 of the tooling and the outer plate 3, the sealing performance of the connection between the main rod 1 of the tooling and the outer plate 3 is improved.

[0041] like Figure 2 As shown, a sealing groove 115 is provided on the outer wall of the main rod 1 of the tooling; the sealing groove 115 is located below the air inlet 112; a sealing ring 5 is installed in the sealing groove 115. Preferably, there are two sealing grooves 115, and a sealing ring 5 is installed in each sealing groove 115. Preferably, the sealing ring 5 is a sealing O-ring.

[0042] like Figure 2 As shown, the outer plate 3 has a trapezoidal cross-section. The trapezoidal cross-section outer plate 3 of this utility model is paired with an inner plate 2 that has a truncated circular plate shape. The engine throat 8 is sealed by the dynamic seal between the rubber sealing gasket 311 attached to the circumference of the outer plate 3 and the sealing ring 5 between the sealing through hole 312 and the tooling main rod 1, thereby increasing the reliability of the airtightness test of the liquid rocket engine.

[0043] The installation steps for the detection device of this utility model are as follows:

[0044] Step S1: Pass the main tooling rod and the inner plate through the engine throat at the same time, assemble them inside the engine throat, pass the main tooling rod through the inner plate through hole of the inner plate, and leave the inner plate inside the engine throat.

[0045] Step S2: Place the two sealing rings into the sealing groove of the main rod of the tooling.

[0046] Preferably, a thin layer of sealing grease can be applied to the sealing ring.

[0047] Step S3: Pass the other end of the tooling main rod through the sealing through hole of the outer plate, with the outer plate boss facing the engine throat, and move along the axial direction of the tooling main rod. The sealing ring can slide freely in the sealing through hole without jamming.

[0048] Step S4: Screw the fastening nut along the mounting thread until the rubber sealing gasket on the outer plate is tightly fitted to the inner wall of the engine nozzle expansion section.

[0049] The airtightness testing steps of the testing device of this utility model are as follows:

[0050] like Figure 1-3As shown, the method for airtightness testing of the rocket engine throat is as follows: After the rocket engine is assembled, the airtightness testing hole 113 of the tooling main rod 1 is inserted into a beaker containing an alcohol solution. Actual operating pressure is introduced into the main valve 6 of the engine throat from the main valve inlet 611. The main valve 6 of the engine throat is in a closed state during the airtightness test, but a small amount of test gas will leak through the engine throat cavity 7. The gas will enter the space between the inner plate 2 and the outer plate 3, and flow into the airflow channel 114 through the air inlet 112. Then it will be discharged into the alcohol solution through the airtightness testing hole 113. According to the existing QJ3253-2005 bubble leak detection test method (QJ3253-2005 is applicable to the test of using gas as a medium and judging the leakage by observing whether bubbles are generated and the number of bubbles in the tested part), the leakage rate index of the main valve 6 of the engine throat is defined. The "number of bubbles generated per unit time" is used as a quantitative index and compared with the standard value to judge the overall airtightness of the rocket engine throat. For example, if no bubbles are generated at the tested area within the specified test pressure and time, or if the number of bubbles is less than or equal to the standard value (e.g., 1 bubble / 30 seconds), the overall airtightness of the engine throat is deemed to meet the requirements. If the number of bubbles per unit time exceeds the standard value (e.g., 2 or more bubbles are generated within 30 seconds), the overall airtightness of the engine throat is deemed to fail to meet the requirements. The specific value of the standard is not limited here; the aforementioned standard value (e.g., 1 bubble / 30 seconds) can be set as needed.

[0051] As a specific embodiment of this utility model, during the airtightness test of the rocket engine throat, air bubbles will be discharged from the alcohol. One leak detection method is to count the number of air bubbles within 3 minutes. If the count of air bubbles within 3 minutes meets the preset requirement (the leakage rate of the main valve of the engine throat is ≤50 air bubbles / min), then the airtightness test of the rocket engine throat is qualified; otherwise, the airtightness test of the rocket engine throat is unqualified. Another airtightness test method is to use a graduated cylinder filled with alcohol and collect the liquid discharged from the airtightness test hole 113 inserted into the alcohol using the water displacement method. The alcohol in the graduated cylinder will be discharged into a container. After collecting for a certain period of time (e.g., t seconds), the volume V (unit: mm^3) of alcohol reduction in the graduated cylinder is read. This volume is the volume of leaked gas during this period to check the amount of leaked gas and measure the leakage rate of the engine throat (e.g., the engine throat leakage rate requirement is not greater than 20 ml / min). Here, the leakage rate is equal to the volume of leaked gas per unit time.

[0052] The beneficial effects achieved by this application are as follows:

[0053] (1) The outer plate of this application is screwed in by tightening the fastening nut, and the rubber sealing gasket set on the outer periphery edge of the outer plate is compressed and deformed, so as to fully fit and seal the detection device with the inner wall of the engine nozzle.

[0054] (2) The dynamic seal between the sealing through hole in the center of the outer plate and the sealing ring between the tooling main rod isolates the engine throat from the outside atmosphere into two spaces, which is more conducive to the airtightness inspection of the engine throat.

[0055] (3) The air tightness detection device can be installed by screwing in the fastening nut, which is convenient.

[0056] (4) This application simplifies the components, and the device includes a tooling main rod, an inner plate, an outer plate, a fastening nut, and a sealing ring. This simplifies the number of components and facilitates rapid disassembly and testing.

[0057] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0058] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to implement and use the present invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the present invention can be implemented without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the present invention with unnecessary detail. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0059] The above description is merely an embodiment of this utility model and is not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this utility model should be included within the scope of the claims of this utility model.

Claims

1. A liquid rocket engine throat airtightness detection device, characterized in that, include: Tooling main rod, inner plate, outer plate, fastening nuts and sealing rings; The inner plate is disposed inside the engine throat. The tooling main rod passes through the inner plate; The tooling main rod has an air inlet and an airflow channel; the airflow channel is connected to the air inlet; the air inlet is connected to the engine throat cavity; The outer plate is arranged parallel to the inner plate, and the outer plate is sleeved on the main rod of the tooling. The outer peripheral wall of the outer plate is sealed and fitted to the inner wall of the engine nozzle expansion section. The fastening nut is threaded onto the main rod of the tooling, and the fastening nut is located on the side of the outer plate away from the inner plate; The sealing ring is disposed at the connection between the outer plate and the main rod of the tooling; When the fastening nut is rotated, the outer plate moves along the axial direction of the main tooling rod.

2. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The tooling main rod includes a main rod, a limiting protrusion, and an airtightness detection head. The limiting protrusion and the airtightness detection head are located at both ends of the main rod; The limiting protrusion is positioned on the side of the inner plate away from the outer plate; A rubber pad is provided between the limiting protrusion and the inner plate; The outer circumference of the main rod has mounting threads, which are threadedly connected to the fastening nut.

3. The liquid rocket engine throat airtightness detection device according to claim 2, characterized in that, The air inlet and the airflow channel are provided on the main rod; The air inlet is positioned perpendicular to the axis of the main rod; The airflow channel is arranged along the axial direction of the main rod; The airtightness detection head has an airtightness detection hole inside; The airtightness detection hole is connected to the end of the airflow channel away from the air inlet.

4. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The inner plate is in the shape of a truncated circular plate.

5. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The outer plate is circular. A rubber sealing gasket is provided on the outer periphery edge of the outer plate; The rubber sealing gasket is disposed between the outer plate and the inner wall of the engine throat.

6. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The inner plate has an inner plate through hole; The outer panel has a sealing through hole; The tooling main rod passes through the inner plate through hole and the sealing through hole.

7. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The outer panel has an outer panel boss; The interior of the outer plate boss is a sealed through hole; The main tooling rod passes through the sealing through hole of the outer plate boss and is sealed to the inner wall of the through hole by a sealing ring.

8. The liquid rocket engine throat airtightness detection device according to claim 7, characterized in that, The sealing rings comprise two; The two sealing rings are spaced apart along the axial direction of the main rod of the tooling.

9. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The outer wall of the main rod of the tooling is provided with a sealing groove; The sealing groove is located below the air inlet; A sealing ring is installed inside the sealing groove.

10. The liquid rocket engine throat airtightness detection device according to claim 1, characterized in that, The outer panel has a trapezoidal cross-section.

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