Rocket engine gas measuring device

Abstract

The invention relates to the field of spectrum external field testing, and discloses a rocket engine fuel gas measuring device which comprises a support and a hollow probe assembly installed on the support. In order to solve the problems of high-temperature and high-pressure impact and thermal ablation of the tail flame of the rocket, the support and the probe assembly are both designed to be of a wedge-shaped structure, internal circulating water paths are arranged on the support and the probe assembly for forced cooling, the probe assembly is of a U-shaped structure, and an optical measurement light path is arranged in the probe assembly. According to the optical measurement light path, gas parameters are measured through a light refraction principle by using a lighting tube, a prism and a collimating lens connector which are inserted into a probe, so that a measurement component is far away from a high-temperature area. According to the invention, the wedge-shaped structure, active water cooling and high-temperature-resistant materials are combined, so that the effects of good cooling performance, stable structure and ablation resistance are realized, and the measurement precision in a harsh environment can be ensured.

Description

Technical Field

[0001] This invention relates to the field of spectral field testing, and more particularly to a rocket engine gas measurement device. Background Technology

[0002] Currently, in the development of aerospace propulsion systems, the design verification of liquid oxygen-kerosene rocket engines is crucial. To validate the infrared radiation model of the engine's exhaust plume and provide a reliable basis for inversion analysis, extensive spectral field characteristic tests must be conducted. This often needs to be performed in a vacuum chamber environment or on a ground test stand. Obtaining the actual gas parameters in the core region of the exhaust plume is the data foundation for optimizing engine performance and evaluating material durability.

[0003] To address the aforementioned testing requirements, existing measurement operations typically employ contact or near-field detection methods. The measuring device is fixed at a specific location on the test platform, generally downstream of the nozzle exit. The device houses optical elements or sensors. During engine ignition, this device directly or indirectly contacts the exhaust plume flow field. The optical path system captures the radiation signals from the combustion gases. Subsequently, the signals are transmitted to back-end processing equipment. In this way, technicians attempt to capture the patterns of change in combustion gas composition and temperature.

[0004] However, existing technologies face challenges in practical applications, resulting in low equipment survivability. During the operation of liquid oxygen / kerosene engines, the harsh environment and the impact of the exhaust flame on the platform create radially diffusing wall jets, causing temperatures to surge instantaneously to over 1000°C. Conventional metal materials struggle to withstand this, and reignition further expands the high-temperature zone. Existing measurement probes often lack targeted high-temperature stagnation point designs, leading to severe material corrosion and structural damage. Furthermore, the dynamic impact cannot be ignored; many devices are designed without considering aerodynamic effects. When an obstacle is placed vertically in a high-speed flow field, the pressure peak in the stagnation zone increases dramatically, the shock wave structure deforms due to reignition, and pressure fluctuations are severe. The platform structure is prone to fatigue cracks, and mechanical strength is insufficient. In addition, traditional devices have limited internal optical path protection measures. Under the coupling effect of high temperature and chemical reactions, precision components lack effective isolation and temperature control, measurements are often interrupted due to equipment damage, and data acquisition is incomplete.

[0005] Therefore, to address the above shortcomings, there is a need to provide a rocket engine gas measurement device. Summary of the Invention

[0006] To address the shortcomings of existing technologies, this invention provides a rocket engine gas measurement device that solves the problem that existing measurement devices are unable to withstand the high-temperature thermal shock, high-pressure dynamic shock, and chemical ablation of rocket engine exhaust flames, thus failing to operate stably and accurately in harsh environments.

[0007] To achieve the above objectives, the present invention is implemented through the following technical solution: a rocket engine gas measuring device, comprising a support and a hollow probe assembly mounted on the support, wherein both the probe assembly and the support are wedge-shaped structures, both the probe assembly and the support are provided with internal circulating water channels, and the hollow probe assembly is also provided with an optical measuring optical path inside; The probe assembly includes probe A and probe B arranged symmetrically and a square water channel. Probe A and probe B are respectively connected to the two ends of the square water channel and sealed and welded thereto, forming a U-shaped structure. The outer wall of the U-shaped structure forms part of the internal circulating water channel of the probe assembly.

[0008] Preferably, the optical measurement path is disposed inside light-collecting tube A and light-collecting tube B, and light-collecting tube A and light-collecting tube B are inserted into the inside of probe A and probe B. The optical measurement path also includes a prism and a collimating lens connector. The prism is bonded to the light-collecting tube A and is used to refract the laser. The collimating lens connector is threadedly connected to the light-collecting tube B.

[0009] Preferably, the device further includes a probe copper-impregnated anchor point installed at the front end of the probe assembly and a support copper-impregnated anchor point installed on the windward side of the support.

[0010] Preferably, both the probe copper-impregnated anchor point and the support copper-impregnated anchor point are made of WUCU7 material. The probe copper-impregnated anchor point is installed using a mortise and tenon structure, and the support copper-impregnated anchor point is connected using a dovetail groove structure.

[0011] Preferably, the device further includes glass and a fastening nut, the glass being screwed onto the front of the probes A and B by the fastening nut to seal the optical measurement path.

[0012] Preferably, the internal circulating water path of the probe assembly further includes square groove-shaped heat dissipation channels disposed on the outer walls of probe A and probe B, and the probe assembly is also fixedly connected to an external probe connector.

[0013] Preferably, the internal circulating water channel of the support is located in the lower layer of the outer wall surface of the support.

[0014] Preferably, the wedge-shaped structure of the support has a groove in the middle and two square openings at the upper end for mounting the probe assembly, and the bottom of the support is a flange plate.

[0015] Preferably, the device further includes a connecting plate, through which the probe assembly is assembled in the opening of the support.

[0016] Preferably, the device further includes a rear cover plate, which is a laminated phenolic material part and is bolted to the support.

[0017] The rocket engine gas measuring device according to the present invention has the following beneficial effects: 1. The structure of this invention is impact-resistant and high-temperature resistant. By designing both the probe and the support as wedge-shaped structures, this shape can effectively resist and guide the high-pressure dynamic impact of the tail flame. At the same time, a closed circulating water channel is designed on the windward side of both the probe and the support. Forced cooling by an external water pump can reduce high-temperature thermal shock and ensure the structural stability and survivability of the device in extreme environments.

[0018] 2. The key components of this invention exhibit strong resistance to ablation. WUCU7 material is used at the probe and support copper infiltration points, where the impact of the tail flame is most severe and the temperature is highest. This material possesses excellent high-temperature resistance and ablation resistance, effectively resisting chemical corrosion and high-temperature melting from the tail flame, ensuring the integrity of the critical windward surface of the device, and extending its service life.

[0019] 3. The measurement system of the present invention is reliable and easy to maintain. By adopting a structure in which the light-collecting tube and the probe are plugged in, and the collimating lens for laser emission and reception is placed externally, this design simplifies the overall structure. By placing the precision optical components outside the high-temperature core area and allowing the light to enter the measurement area only through prism refraction, the survivability and reliability of the measurement system are improved. On the other hand, the plug-in structure also facilitates the replacement and installation of internal optical components. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the gas measuring device of the present invention; Figure 2 This is a half-sectional schematic diagram of the gas measuring device of the present invention; Figure 3 This is a schematic diagram of the support structure of the present invention; Figure 4 This is a schematic diagram of the unwelded probe A of the present invention; Figure 5 This is a schematic diagram of the probe A after welding according to the present invention; Figure 6 This is a schematic diagram of the unwelded probe B of the present invention; Figure 7 This is a schematic diagram of the probe B after welding according to the present invention; Figure 8 This is a schematic diagram of the square waterway of the present invention; Figure 9 This is a schematic diagram of the light-collecting tube A of the present invention; Figure 10 This is a schematic diagram of the light-collecting tube B of the present invention; Figure 11 This is a schematic diagram of the connecting plate of the present invention; Figure 12This is a schematic diagram of the copper penetration point of the probe in this invention; Figure 13 This is a schematic diagram of the fastener nut of the present invention; Figure 14 This is a schematic diagram of the probe outer tube connector of the present invention; Figure 15 This is a schematic diagram of the collimating lens connector of the present invention; Figure 16 This is a schematic diagram of the copper-impregnated support point of the present invention; Figure 17 This is a schematic diagram of the U-shaped structure after welding according to the present invention.

[0021] In the diagram: 1. Rear cover plate; 2. Light-collecting tube A; 3. Prism; 4. Probe A; 5. Light-collecting tube B; 6. Collimating lens connector; 7. Probe B; 8. Probe external pipe connector; 9. Glass; 10. Probe copper-impregnated anchor point; 11. Fastening nut; 12. Square water channel; 13. Connecting plate; 14. Support; 15. Support copper-impregnated anchor point. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] See attached document Figure 1 and attached Figure 2 A specific embodiment of the present invention provides a gas measurement device for a rocket engine, including a rear cover plate 1, a light-collecting tube A2, a prism 3, a probe A4, a light-collecting tube B5, a collimating lens connector 6, a probe B7, a probe outer tube connector 8, a glass 9, a probe copper-impregnated anchor point 10, a fastening nut 11, a square water channel 12, a connecting plate 13, a support 14, and a support copper-impregnated anchor point 15.

[0024] See attached document Figure 1 and attached Figure 2 The entire device, including the hollow probe assembly and the support 14, features a wedge-shaped structure to effectively reduce the high-temperature thermal shock and high-pressure dynamic impact from the rocket exhaust. The internal structure of the device includes how the hollow probe assembly is installed in the groove of the support 14, and how the optical measurement light routes, such as the light-collecting tubes A2 and B5, are set in the blind holes inside the probes A4 and B7.

[0025] See attached document Figure 3The support 14 serves as the mounting base and is wedge-shaped with a groove in the middle. The upper end of the support 14 has two square openings for mounting the hollow probe assembly. The bottom of the support 14 has a flange plate for bolting to the test bench. An internal circulating water channel is provided on the lower layer of the outer wall of the support 14.

[0026] See attached document Figure 4 and attached Figure 5 The probe A4 is designed with square grooved cooling channels on all four sides, and has a blind hole in the middle of its rear end. This blind hole serves as the probe mounting hole and the threaded hole for installation. Before assembly, the metal cover plate must be welded to the probe A4 to form a closed cooling channel.

[0027] See attached document Figure 6 and attached Figure 7 The structure and preparation method of probe B7 are similar to those of probe A4, and the two are arranged symmetrically.

[0028] See attached document Figure 8 The square water channel 12 is used to connect the two ends of probe A4 and probe B7 and to seal and weld them together. Its internal pipes connect the heat dissipation water channels of probe A4 and probe B7, forming a U-shaped structure together.

[0029] See attached document Figure 9 and attached Figure 10 The light-collecting tubes A2 and B5 are inserted into the blind holes inside the probes A4 and B7, together forming the optical measurement path.

[0030] See attached document Figure 11 The connecting plate 13 is used to weld the U-shaped probe assembly and to assemble the probe assembly into the square opening of the support 14 through the connecting plate 13.

[0031] See attached document Figure 12 The probe copper-impregnated anchor point 10 is made of WUCU7 material and is installed at the front end of probe A4 and probe B7 through a tenon and mortise structure to resist direct ablation by high-temperature gas.

[0032] See attached document Figure 13 The screw nut 11 is screwed onto the front of probes A4 and B7 by threads to press the glass 9 in order to seal the optical measurement path.

[0033] See attached document Figure 14 The probe external pipe connector 8 is fixedly connected to the probe assembly, such as probe B7, and serves as the external water supply interface for the internal circulating water circuit of the probe assembly.

[0034] See attached document Figure 15 The collimating lens connector 6 and the light-collecting tube B5 are connected by threads for connecting external laser receiving and analysis equipment.

[0035] See attached document Figure 16 The support copper anchor point 15 is made of WUCU7 material and is inserted into the windward side of the support 14 through a dovetail groove structure to protect the support 14 from ablation.

[0036] See attached document Figure 17 The assembly process of the present invention includes: welding the welded probes A4 and B7 to the square waterway 12, and then welding them to the connecting plate 13 to form a closed U-shaped probe assembly.

[0037] The specific assembly and workflow of this invention are as follows: First, as Figure 17 As shown, probes A4 and B7, which have already been welded to the metal cover plate, are welded to the square waterway 12, and then welded to the connecting plate 13 to form a closed U-shaped structure, namely the U-shaped probe assembly. Secondly, as... Figure 2 As shown, the light-collecting tube A2 is assembled with the prism 3 bonded thereto, and the light-collecting tube B5 is assembled with the threaded collimating lens connector 6. Then, as... Figure 2 As shown, assemble probe A4, glass 9, and fastening nut 11; assemble the copper-plated support anchor point 15 with the support 14; assemble the copper-plated probe anchor point 10 with probe A4 and probe B7. Then, assemble the assembled U-shaped probe assembly into the opening of the support 14 via the connecting plate 13. Finally, as shown... Figure 2 As shown, the rear cover plate 1 is assembled with the support 14. The rear cover plate 1 is a laminated phenolic material part and is bolted to the support 14.

[0038] Before starting the rocket engine, the two closed-loop water circuits—the probe assembly water circuit and the support water circuit—are connected to the water pump for water injection. Simultaneously, the measuring equipment is turned on and put into normal operation. After the rocket engine is started, the circulating water in the device exchanges heat with the high temperature on the outer surface, bringing the internal temperature to a measurable level, thus ensuring the smooth conduct of the experiment.

[0039] This invention effectively reduces the high-temperature thermal shock and high-pressure dynamic impact of rocket exhaust on the measuring device through the design of a wedge-shaped structure and a square cooling water tank. Simultaneously, the plug-in structure of the light-collecting tube and probe greatly simplifies the overall structure, facilitates machining, and makes the replacement and installation of parts in the light-collecting device easier. Furthermore, the use of WUCU7 material effectively reduces the ablation of the measuring device by the exhaust. The solution proposed in this invention offers excellent cooling performance, structural stability, and high measurement accuracy.

[0040] Working principle: By combining an impact-resistant wedge-shaped aerodynamic structure, a dual-path independent forced water cooling system, and ablation-resistant special materials, a built-in optical measurement path is provided with survivability in harsh environments, enabling it to measure rocket engine exhaust gases. The workflow, structural coordination, and measurement principle are as follows: Firstly, in the overall construction and installation of the measuring device, support 14 serves as the mounting base. The bottom of support 14 is a flange plate for rigid connection with the test platform. Support 14 itself is designed as a hollow wedge-shaped structure with two square openings at its upper end. A U-shaped probe assembly is assembled into the square openings of support 14 via connecting plate 13. The U-shaped probe assembly itself is formed by sealing and welding symmetrically arranged probes A4 and B7, and square channels 12 connecting their ends. Probes A4 and B7 are also wedge-shaped structures. On the windward side of support 14 and the front end of the probe assembly, i.e., the stagnation point most severely impacted by high-temperature combustion gases, copper-impregnated support stagnation point 15 and copper-impregnated probe stagnation point 10 are respectively installed. Both are made of WUCU7 high-temperature resistant ablation material, together forming the first line of defense of this invention.

[0041] Secondly, in terms of thermal protection and impact resistance, this invention utilizes a dual design of aerodynamic shape and active cooling. On one hand, the wedge-shaped structure of the probe assembly and support 14 effectively guides the high-temperature, high-pressure wall jet, reducing positive dynamic impact and pressure peaks. On the other hand, the device is equipped with two independent internal circulating water circuits. The first circuit is the probe assembly water circuit, which consists of square groove-shaped heat dissipation channels on the outer walls of probes A4 and B7 connected to the internal pipes of square water channel 12, and is supplied with water by an external water pump through the probe external pipe connector 8; the second circuit is the support water circuit, which is located on the lower layer of the outer wall of support 14. Before the rocket engine operates, the water pump starts, and circulating water flows simultaneously in both circuits, forcibly cooling the probe assembly and support 14, and removing the heat transferred by the exhaust flame through heat exchange, ensuring the structural integrity of the device.

[0042] Finally, in the measurement of gas parameters, this invention utilizes an optical measurement path located inside the hollow probe assembly. This optical path is mechanically protected by probes A4 and B7, cooled by an internal circulating water system, and sealed by the front-end glass 9. Light-collecting tubes A2 and B5 are respectively inserted into the blind holes inside probes A4 and B7. The front end of the optical measurement path is sealed by glass 9 installed at the front of probes A4 and B7, and glass 9 is tightened and fixed by fastening nuts 11. During measurement, the laser is emitted from one side of light-collecting tube A2, refracted by a prism 3 bonded to light-collecting tube A2, passes through the gas space between probes A4 and B7, and is finally received by one side of light-collecting tube B5 and transmitted to the collimating lens connector 6 threadedly connected to light-collecting tube B5. By analyzing the changes in the laser light passing through the gas, parameters such as gas composition and temperature are measured. Simultaneously, a rear cover plate 1 is bolted to the support 14, providing protection for the rear of the device.

[0043] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A rocket engine gas measurement device, comprising a support (14) and a hollow probe assembly mounted on the support (14), characterized in that, Both the probe assembly and the support (14) are wedge-shaped structures. Both the probe assembly and the support (14) are provided with internal circulating water channels. The hollow probe assembly is also provided with an optical measurement optical path inside. The probe assembly includes probes A (4) and B (7) arranged symmetrically and a square waterway (12). Probes A (4) and B (7) are respectively connected to the two ends of the square waterway (12) and sealed and welded thereto, forming a U-shaped structure. The outer wall of the U-shaped structure forms part of the internal circulating waterway of the probe assembly.

2. The rocket engine gas measuring device according to claim 1, characterized in that, The optical measurement path is set inside the light collection tube A (2) and the light collection tube B (5). The light collection tube A (2) and the light collection tube B (5) are inserted into the probe A (4) and the probe B (7). The optical measurement path also includes a prism (3) and a collimating lens connector (6). The prism (3) is bonded to the light collection tube A (2) for refracting the laser. The collimating lens connector (6) is threadedly connected to the light collection tube B (5).

3. The rocket engine gas measuring device according to claim 1, characterized in that, The device also includes a probe copper-impregnated anchor point (10) installed at the front end of the probe assembly and a support copper-impregnated anchor point (15) installed on the windward side of the support (14).

4. The rocket engine gas measuring device according to claim 3, characterized in that, Both the probe copper-impregnated anchor point (10) and the support copper-impregnated anchor point (15) are made of WUCU7 material. The probe copper-impregnated anchor point (10) is installed by mortise and tenon structure, and the support copper-impregnated anchor point (15) is inserted by dovetail groove structure.

5. A rocket engine gas measuring device according to claim 1, characterized in that, The device also includes glass (9) and a fastening nut (11), the glass (9) being screwed onto the front of the probe A (4) and the probe B (7) by the fastening nut (11) to seal the optical measurement path.

6. The rocket engine gas measuring device according to claim 1, characterized in that, The internal circulating water path of the probe assembly also includes square groove-shaped heat dissipation channels provided on the outer walls of probe A (4) and probe B (7), and the probe assembly is also fixedly connected to a probe external pipe connector (8).

7. A rocket engine gas measuring device according to claim 1, characterized in that, The internal circulating water channel of the support (14) is located on the lower layer of the outer wall surface of the support (14).

8. A rocket engine gas measuring device according to claim 1, characterized in that, The support (14) has a wedge-shaped structure with a groove in the middle and two square openings at the top for mounting the probe assembly. The bottom of the support (14) is a flange plate.

9. A rocket engine gas measuring device according to claim 1, characterized in that, The device also includes a connecting plate (13), through which the probe assembly is assembled in the opening of the support (14).

10. A rocket engine gas measuring device according to claim 1, characterized in that, The device also includes a rear cover plate (1), which is a laminated phenolic material part and is bolted to the support (14).

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