CN-115855760-B - Rocket engine condensed phase combustion product dynamic deposition test device and system

CN115855760BCN 115855760 BCN115855760 BCN 115855760BCN-115855760-B

Abstract

The invention provides a rocket engine condensed phase combustion product dynamic deposition test device and a rocket engine condensed phase combustion product dynamic deposition test system, wherein the rocket engine condensed phase combustion product dynamic deposition test device comprises a main shell, a propellant burner connecting flange and a temperature measuring component mounting flange are respectively fixedly arranged at the top end and the bottom end of the main shell, and a deposition runner is arranged in the space in the main shell and the temperature measuring component mounting flange; the main shell is provided with a left observation window and a right observation window, and the left observation window and the right observation window are respectively provided with an observation plate and a heat protection plate. The rocket engine condensed phase combustion product dynamic deposition test device can observe deposition evolution processes of solid propellant combustion products under various charging states, and can achieve the purpose of measuring deposition heat flow and heat increment in real time.

Inventors

Guan Diewen
YAN NING
BIAN CHENG
YANG YANJING
HU SHAOQING
WANG LE
HUI KUN

Assignees

西安近代化学研究所

Dates

Publication Date: 20260505
Application Date: 20221130

Claims (10)

1. The dynamic deposition test device for the condensed-phase combustion products of the rocket engine is characterized by comprising a main shell (1), wherein a propellant burner connecting flange (2) is integrally arranged at the top end of the main shell (1), a temperature measuring component mounting flange (3) is fixedly connected to the bottom end of the main shell (1), and a deposition runner (4) is arranged in the space between the main shell (1) and the temperature measuring component mounting flange (3); The top of the temperature measuring component mounting flange (3) stretches into the main shell (1), a heat insulation sleeve (5) is fixedly arranged in the top of the temperature measuring component mounting flange (3), a heat measuring body (6) is sleeved in the heat insulation sleeve (5), the heat insulation sleeve (5) and the heat measuring body (6) are both positioned at the bottom of the deposition runner (4), a plurality of thermocouple mounting holes (7) are formed in the heat measuring body (6), thermocouples (8) are arranged in the thermocouple mounting holes (7), the bottom of the temperature measuring component mounting flange (3) is fixedly connected with the temperature measuring instrument connecting flange (9), a temperature measuring wire fixing plug (10) and a temperature measuring wire joint (11) are sequentially and fixedly arranged in the temperature measuring instrument connecting flange (9) from top to bottom, a temperature measuring wire (12) is arranged in the temperature measuring wire fixing plug (10), one end of the temperature measuring wire (12) is connected with the thermocouples (8), and the other end of the temperature measuring wire (12) penetrates through the temperature measuring wire joint (11) and stretches out of the bottom end of the temperature measuring instrument connecting flange (9); The novel thermal insulation device is characterized in that a left observation window (13) is formed in the left side of the main shell (1), a right observation window (14) is formed in the right side of the main shell (1), the left observation window (13) and the right observation window (14) are oppositely arranged, the left observation window (13) and the right observation window (14) are communicated with the deposition runner (4), an observation plate (15) is arranged at each of the left observation window (13) and the right observation window (14), the observation plate (15) is arranged on the main shell (1), a thermal protection plate (16) is fixedly connected to the inner side of the observation plate (15), and the thermal protection plate (16) is arranged in the main shell (1) above the thermal insulation sleeve (5).
2. Rocket engine condensed phase combustion product dynamic deposition test device according to claim 1, characterized in that the front side of the main housing (1) is integrally provided with a mounting flange (17).
3. A rocket engine condensed phase combustion product dynamic deposition testing device according to claim 1, wherein the plurality of thermocouple mounting holes (7) are arranged in two sides of the heat measuring body (6), and the plurality of thermocouple mounting holes (7) positioned on the same side are arranged at equal intervals.
4. Rocket engine condensed phase combustion product dynamic deposition test device according to claim 1, characterized in that a plurality of observation plate mounting holes (18) are formed in the main casing (1) around the left observation window (13) and the right observation window (14), a plurality of observation plate fixing holes (19) are formed in the observation plate (15), and the plurality of observation plate mounting holes (18) and the plurality of observation plate fixing holes (19) are arranged in a one-to-one correspondence.
5. A rocket engine condensed phase combustion product dynamic deposition test device according to claim 1, wherein the deposition runner (4) is of a square structure, the side length of the cross section of the deposition runner is 80mm, and the height of the deposition runner is 165mm.
6. A rocket engine condensed phase combustion product dynamic deposition testing device according to claim 1, wherein the left observation window (13) and the right observation window (14) have the same size, and the length of the left observation window is 80mm and the width of the left observation window is 50mm.
7. A rocket motor condensed phase combustion product dynamic deposition test device according to claim 1, wherein said heat measuring body (6) is made of graphite.
8. A rocket engine condensed phase combustion product dynamic deposition testing device according to claim 1, wherein said observation plate (15) is made of aluminum, and said heat-proof protection plate (16) is made of graphite.
9. A rocket engine condensed phase combustion product dynamic deposition test device according to claim 1, wherein said temperature measuring wire fixing plug (10) is made of polytetrafluoroethylene.
10. The rocket engine condensed phase combustion product dynamic deposition test system is characterized by comprising the rocket engine condensed phase combustion product dynamic deposition test device according to any one of claims 1 to 9, wherein the rocket engine condensed phase combustion product dynamic deposition test device is fixedly arranged on a support (20), a propellant burner (21) is fixedly arranged on the support (20), the bottom end of the propellant burner (21) is fixedly connected with a propellant burner connecting flange (2), a lifting table (22) is arranged beside the support (20), an X-ray emitter (23) is movably arranged on the lifting table (22), the X-ray emitter (23) is close to a left observation window (13), a light source of the X-ray emitter (23) faces the left observation window (13), a temperature measuring instrument (24) is arranged beside the lifting table (22), and the temperature measuring instrument (24) is connected with a temperature measuring line (12).

Description

Rocket engine condensed phase combustion product dynamic deposition test device and system Technical Field The invention belongs to the technical field of solid rocket engines, relates to the deposition characteristics of rocket engine condensed phase combustion products, and in particular relates to a rocket engine condensed phase combustion product dynamic deposition test device and system. Background The composite propellant containing the metal fuel has high energy and can effectively inhibit high/medium frequency oscillation combustion, so the composite propellant is widely used as a main power energy source of a solid rocket engine at present. However, the composite propellant containing the metal fuel can generate a large amount of metal compound condensed phase particles in the combustion process, a high-temperature and high-pressure two-phase flow environment is formed in the combustion chamber and the spray pipe, the inside of the engine body of the aircraft can generate high overload in the high-speed flight process, the high-temperature two-phase flow can gather to the heat insulation layer of the engine, and serious ablation can be generated on the wall surface and the heat insulation layer of the engine, so that the overall performance and the service life of the engine are influenced. In addition, because modern large solid rocket engine jet pipes generally adopt a submerged structure, a large part of the jet pipes penetrate into a combustion chamber or a shell, the length of the engine can be effectively shortened, the dead weight of an aircraft is reduced, the requirement on the overall design of the engine is met, and on the other hand, movable jet pipes capable of providing thrust vector control for the aircraft are mostly submerged. The submerging of the lance complicates the flow at the tail of the combustion chamber and the flow conditions change greatly as the combustion surface moves and mass is added. When the composite propellant containing the metal fuel is combusted, the generated large solid particles cannot enter the nozzle and can be deposited in the cavity of the back wall of the submerged nozzle, so-called slag deposition layer is formed. The energy of the propellant is lost due to the incapability of discharging slag, the negative weight of the engine is increased, the heat transfer process of the inner wall surface of the engine is enhanced due to the deposition of slag, and in addition, the strength of the wall surface of the engine is reduced due to the deposition of slag, and accidents such as burning-through of the engine shell, failure of the engine and the like are caused. In order to avoid adverse effects of slag deposition on the engine, experiments were designed to investigate the deposition characteristics of the condensed phase combustion products of the propellant. The Chinese patent with the publication number of CN105448177B discloses a double-spray pipe simulation device for researching the ablation phenomenon of a heat insulation layer in a rocket engine, which can simulate the ablation phenomenon of the heat insulation layer of a large solid rocket engine under the condition of particle phase deposition in a cavity of the back wall of a spray pipe, and can obtain the quality ablation rate of the heat insulation layer, observe microscopic morphology of a charring layer and the like through means such as a thickness gauge, an electron microscope and the like in the later stage. However, in the prior art, because no visual structure is designed in practical application, it is difficult to test deposition and evolution processes of condensed phase products generated by combustion of the propellant under high temperature and high pressure conditions in real time, and it is difficult to dynamically and real-time measure heat transfer data of the deposited products under different evolution states. Disclosure of Invention Aiming at the defects existing in the prior art, the invention aims to provide a rocket engine condensed phase combustion product dynamic deposition test device and system, which solve the technical problems that the deposition phenomenon of solid propellant combustion products is difficult to observe in real time and heat transfer data is acquired in real time in the prior art. In order to solve the technical problems, the invention adopts the following technical scheme: The utility model provides a rocket engine condensed phase combustion product dynamic deposition test device, includes the main casing, the top integration of main casing is provided with propellant burner flange, the bottom fixedly connected with temperature measurement subassembly mounting flange of main casing, the space in main casing and the temperature measurement subassembly mounting flange be the deposition runner. The top of the temperature measuring component mounting flange stretches into the main shell, an insulating sleeve is fixedly arranged in the top of the temp