A multi-modal vacuum evacuation ejector relay system and method

Abstract

This invention discloses a multimodal vacuum ejector relay system and method, which solves the technical problem that existing technologies cannot meet the test requirements when facing complex working conditions such as high vacuum, long test time and large flow rate. By setting up a gas collection chamber, a vacuum spherical tank and a mechanical vacuum pump, the mechanical vacuum pump is started to evacuate the vacuum spherical tank, gas collection chamber, diffuser and vacuum test chamber, and complete the establishment of a simulated test environment, so as to achieve the effect of ultra-low pressure vacuum start-up and long-term vacuum maintenance.

Description

Technical Field

[0001] This invention relates to ejection systems, and more specifically to a multimodal vacuum ejection relay system and method. Background Technology

[0002] High-altitude and space environment simulation tests for rocket engines require creating a high-altitude environment in ground test equipment, allowing the engine to operate in this environment to obtain its performance, reliability, and service life, ensuring the requirements of flight missions.

[0003] During testing, the engine ignites and rapidly generates a large amount of combustion gas. This gas accumulates in the test chamber, disrupting the low-pressure / vacuum environment and causing the pressure inside the chamber to rise. This makes it impossible to reproduce high-altitude conditions, leading to distorted engine performance test data. Furthermore, the high-temperature combustion gas can burn the test chamber walls, sensors, and other test equipment. Therefore, it is necessary to quickly extract and eliminate the harmful effects of the combustion gas on the test environment and equipment. Currently, there are three main methods for extracting high-temperature combustion gas: mechanical vacuum pump ejection systems, air ejection pump ejection systems, and steam jet pump ejection systems.

[0004] The mechanical vacuum pump ejector system mainly includes components such as a main pump, a back pump, pipelines, valves, cooling and control systems. Before the test begins, the ejector gas in the test chamber is directly extracted by the main pump to meet the high vacuum requirements of the test chamber. Its suction vacuum degree is approximately inversely proportional to the suction flow rate, which leads to a sharp decrease in pumping efficiency under extreme high vacuum conditions, making it only suitable for engine tests with extremely small flow rates.

[0005] Air ejector pump systems and steam jet pump ejector systems operate on similar principles, consisting of a power source (air or steam), nozzles, an intake chamber, a mixing chamber, a diffuser, isolation valves, and an exhaust pipe. Utilizing the power source, a supersonic jet is generated through a Laval nozzle to draw in the ejected gas, thus creating a certain degree of vacuum. While it has a large pumping capacity, a relatively low vacuum level, and a limited pump compression ratio, it is only suitable for high-flow-rate, low-vacuum engine testing.

[0006] When faced with complex operating conditions such as high vacuum, long duration, and high flow rate, none of the above three ejection systems can meet the experimental requirements. Summary of the Invention

[0007] To address the technical problem that existing ejector systems cannot meet experimental requirements under complex conditions such as high vacuum, long test time, and large flow rate, this invention provides a multi-modal vacuum ejector relay system and method.

[0008] To achieve the above objectives, the present invention adopts the following technical solution:

[0009] A multimodal vacuum ejector relay system for exhausting vacuum test chambers; its special feature is that it includes a gas collection chamber, a vacuum spherical tank, a mechanical vacuum pump, a steam jet pump, a steam generator, and a diffuser.

[0010] The gas collection chamber is equipped with an air inlet, an exhaust outlet, a mechanical pump connection port, and a spherical tank connection port;

[0011] The air inlet of the gas collecting chamber is connected to the exhaust port of the diffuser through the first valve, and the air inlet of the diffuser is connected to the exhaust port of the vacuum test chamber.

[0012] The exhaust port of the gas collecting chamber is connected to a set of steam jet pumps via a second valve. The inlet of the steam jet pumps is connected to the gas collecting chamber, the exhaust port of the steam jet pumps is connected to the atmosphere, and the steam inlet of the steam jet pumps is connected to the steam generator. The steam generator supplies steam to the steam jet pumps so that the pressure before the second valve reaches the rated ejector pressure. ;

[0013] The spherical tank connection port of the gas collection chamber is connected to the vacuum spherical tank through a third valve;

[0014] The mechanical pump connection port of the gas collection chamber is connected to the mechanical vacuum pump through the fourth valve, and is used to evacuate the gas collection chamber, vacuum sphere, diffuser and vacuum test chamber by means of the mechanical vacuum pump.

[0015] This invention also provides a multimodal vacuum ejection relay method, based on the aforementioned multimodal vacuum ejection relay system; its special feature is that it includes the following steps:

[0016] Step 1: Obtain the test pressure value of the rocket engine under test based on its parameter information. The rated ejector pressure of the steam jet pump is q is the equivalent flow rate of the ejected gas inside the vacuum test chamber.

[0017] Step 2: Open the third valve, the fourth valve, and the first valve to connect the gas collecting chamber, the vacuum spherical tank, the diffuser, and the vacuum test chamber into a single integrated chamber. Use a mechanical vacuum pump to evacuate the integrated chamber until the pressure reaches the test pressure value. Then, shut off the fourth valve and the mechanical vacuum pump;

[0018] Step 3: Start the steam generator to charge steam into the steam jet pump, so that the pressure before the second valve reaches the rated ejector pressure value. ;

[0019] Step 4: The test rocket engine is ignited. The ejected gas generated during the test is pressurized by the diffuser and then enters the gas collection chamber and vacuum spherical tank.

[0020] Step 5: At time t after the start of the test, send a control command to the second valve via an external control device to open the second valve, thereby increasing the pressure in the gas collecting chamber to [value missing]. At that time, the second valve is fully opened, and the ejected gas is discharged into the atmosphere after passing through the steam jet pump, completing the multi-mode vacuum ejection relay.

[0021] Furthermore, in step 1, the formula for calculating the equivalent flow rate q of the ejected gas is as follows:

[0022] ;

[0023] in, The gas flow rate for the high-temperature combustion gases produced after the rocket engine ignites;

[0024] After the rocket engine is ignited, the sprayed cooling water generates water vapor flow.

[0025] An air temperature correction factor to equate the temperature of high-temperature gas combustion gas to 20 degrees Celsius air.

[0026] This is the correction factor for the average molecular weight of high-temperature gas;

[0027] This is a correction factor for water vapor temperature.

[0028] This is the correction factor for the molecular weight of water vapor;

[0029] In step 5, the formula for calculating time t is as follows:

[0030] ;

[0031] ;

[0032] in, The pressure in the gas collecting chamber is from Rise to Time required;

[0033] V is the total volume of the gas collection chamber and the vacuum spherical tank;

[0034] M is the mass number of molecules of the entrained gas:

[0035] R is the gas constant;

[0036] T is the temperature of the ejected gas;

[0037] The time required for the second valve to fully open.

[0038] The present invention also provides a multimodal vacuum ejector relay system for exhausting vacuum test chambers; its special feature is that it includes a gas collection chamber, a vacuum spherical tank, a mechanical vacuum pump, a steam jet pump, a steam generator and diffuser, a gas collection chamber connecting pipe, a power gas source and at least one set of air jet pumps;

[0039] The gas collection chamber is equipped with an air inlet, an exhaust outlet, a mechanical pump connection port, and a spherical tank connection port;

[0040] The air inlet of the gas collecting chamber is connected to the exhaust port of the diffuser through the first valve, and the air inlet of the diffuser is connected to the exhaust port of the vacuum test chamber.

[0041] The exhaust port of the gas collecting chamber is connected to a set of steam jet pumps via a second valve. The inlet of the steam jet pumps is connected to the gas collecting chamber, the exhaust port of the steam jet pumps is connected to the atmosphere, and the steam inlet of the steam jet pumps is connected to the steam generator. The steam generator supplies steam to the steam jet pumps so that the pressure before the second valve reaches the rated ejector pressure. ;

[0042] The spherical tank connection port of the gas collection chamber is connected to the vacuum spherical tank through a third valve;

[0043] The mechanical pump connection port of the gas collection chamber is connected to the mechanical vacuum pump through the fourth valve, and is used to evacuate the gas collection chamber, vacuum sphere, diffuser and vacuum test chamber by means of the mechanical vacuum pump;

[0044] One end of the gas collection chamber connecting pipe is connected to the gas collection chamber through a fifth valve, and the other end is closed. Multiple air jet pump mounting holes are provided on it.

[0045] Each air jet pump group includes a primary air jet pump and a secondary air jet pump arranged in series. Both of them include a compressed air inlet, an ejected gas inlet, and an exhaust port.

[0046] The inlet of the primary air jet pump is connected to the gas collection chamber connecting pipe through the first air jet pump mounting hole, and the exhaust port of the primary air jet pump is connected to the gas collection chamber connecting pipe through the second air jet pump mounting hole.

[0047] The inlet of the secondary air jet pump is connected to the gas collection chamber connecting pipe through the seventh valve, and its exhaust port is open to the atmosphere;

[0048] The fifth valve is installed on the gas collection chamber connecting pipe and is located between the first air jet pump mounting hole and the second air jet pump mounting hole;

[0049] The power air source is connected to the compressed air inlet of the first-stage air jet pump via a sixth valve, and is used to supply compressed air to the first-stage air jet pump so that the inlet pressure of the ejected gas in the first-stage air jet pump reaches the rated ejection pressure value. The power air source is connected to the compressed air inlet of the secondary air injection pump via the eighth valve, and is used to supply compressed air to the secondary air injection pump so that the pressure before the seventh valve reaches the rated ejector pressure. .

[0050] Furthermore, the air jet pump consists of two sets, which are connected in parallel on the air collection chamber connecting pipe.

[0051] This invention also provides an ejection relay method based on the above-mentioned multimodal vacuum ejection relay system, characterized by the following steps:

[0052] Step S1: Based on the test duration T of the rocket engine to be tested, if... If so, proceed to step S2; if If so, proceed to step S7;

[0053] Step S2: Obtain the test pressure value of the rocket engine under test based on the parameter information of the rocket engine under test. The rated ejector pressure of the steam jet pump is q is the equivalent flow rate of the ejected gas inside the vacuum test chamber.

[0054] Step S3: Open the third valve, the fourth valve, and the first valve to connect the gas collecting chamber, the vacuum spherical tank, the diffuser, and the vacuum test chamber into a single integrated chamber. Use a mechanical vacuum pump to evacuate the integrated chamber until its pressure reaches the test pressure value. Then, shut off the fourth valve and the mechanical vacuum pump;

[0055] Step S4: Start the steam generator to charge steam into the steam jet pump, so that the pressure before the second valve reaches the rated ejector pressure value. ;

[0056] Step S5: The rocket engine to be tested is ignited. The ejected gas generated during the test is pressurized by the diffuser and then enters the gas collection chamber and the vacuum spherical tank.

[0057] Step S6: At time t after the start of the test, the external control device sends a control command to the second valve to open it, thereby increasing the pressure in the gas collecting chamber to [value missing]. At that time, the second valve is fully opened, and the ejected gas is discharged into the atmosphere after passing through the steam jet pump;

[0058] Step S7: Obtain the test pressure value of the rocket engine under test based on the parameter information of the rocket engine under test. Rated ejector pressure of the air jet pump q is the equivalent flow rate of the ejected gas inside the vacuum test chamber.

[0059] Step S8: Based on the test pressure value of the rocket engine to be tested. Judgment, if If the pressure is atmospheric pressure P, then the first, fifth, and seventh valves are opened, directly discharging the gas discharged from the diffuser into the atmosphere through the gas collection chamber, the gas collection chamber connecting pipe, the primary air jet pump, and the secondary air jet pump. At this time, the primary and secondary air jet pumps do not perform air ejection. If... If the pressure is less than atmospheric pressure P, then proceed to step S4;

[0060] Step S9: Open the third valve, the fourth valve, and the first valve to connect the gas collecting chamber, the vacuum spherical tank, the diffuser, and the vacuum test chamber into a single integrated chamber. Use a mechanical vacuum pump to evacuate the integrated chamber until the pressure reaches a certain value. Then, shut off the fourth valve and the mechanical vacuum pump;

[0061] Step S10: Start the power air source and open the eighth valve to fill the secondary air injection pump with compressed air, so that the pressure before the seventh valve reaches the rated ejector pressure value. ;

[0062] Step S11: The rocket engine to be tested is ignited. The ejected gas generated during the test is pressurized by the diffuser and then enters the gas collection chamber and the vacuum spherical tank.

[0063] Step S12: After the test begins, the external control device is used to control the test. At any given time, a control command is sent to the seventh valve to open it, thereby increasing the pressure in the gas collecting chamber to [a certain value]. At this time, the seventh valve is fully open, and the ejected gas is discharged into the atmosphere through the first-stage air jet pump and the second-stage air jet pump in sequence. At this time, the first-stage air jet pump does not perform air ejection action.

[0064] Step S13: Open the sixth valve and fill the first-stage air jet pump with compressed air through the power air source. Start the first-stage air jet pump. The first-stage air jet pump and the second-stage air jet pump connected in series will jointly discharge the ejected gas into the atmosphere, completing the multi-mode vacuum ejection relay.

[0065] Furthermore, in steps S2 and S7, the formula for calculating the equivalent flow rate q of the ejected gas is as follows:

[0066] ;

[0067] in, The gas flow rate for the high-temperature combustion gases produced after the rocket engine ignites;

[0068] After the rocket engine is ignited, the sprayed cooling water generates water vapor flow.

[0069] An air temperature correction factor to equate the temperature of high-temperature gas combustion gas to 20 degrees Celsius air.

[0070] This is the correction factor for the average molecular weight of high-temperature gas;

[0071] This is a correction factor for water vapor temperature.

[0072] This is the correction factor for the molecular weight of water vapor;

[0073] In step S6, the formula for calculating time t is as follows:

[0074] ;

[0075] ;

[0076] in, The pressure in the gas collecting chamber is from Rise to Time required;

[0077] V is the total volume of the gas collection chamber and the vacuum spherical tank;

[0078] M is the mass number of molecules of the entrained gas:

[0079] R is the gas constant;

[0080] T is the temperature of the ejected gas;

[0081] The time required for the second valve to fully open.

[0082] In step S13, The formula for calculating time is as follows:

[0083] ;

[0084] ;

[0085] in, The pressure in the gas collecting chamber is from Rise to Time required;

[0086] V is the total volume of the gas collection chamber and the vacuum spherical tank;

[0087] M is the mass number of molecules of the entrained gas:

[0088] R is the gas constant;

[0089] T is the temperature of the ejected gas;

[0090] The time required for the seventh valve to fully open.

[0091] Furthermore, the air inlet and outlet of the air collection chamber each have at least two;

[0092] Each air inlet of the gas collecting chamber is connected to the exhaust port of a diffuser, and each air inlet of the diffuser is connected to the exhaust port of a vacuum test chamber.

[0093] Each exhaust port of the gas collection chamber is connected to a set of steam jet pumps, and each set of steam jet pumps includes a first-stage steam jet pump and a second-stage steam jet pump connected in series.

[0094] The inlet of the first-stage steam jet pump is connected to an exhaust port of the gas collecting chamber via a second valve, and the exhaust port of the second-stage steam jet pump is open to the atmosphere.

[0095] The steam generator has a first exhaust port and a second exhaust port; its first exhaust port is connected to the steam inlet of the first-stage steam jet pump, and its second exhaust port is connected to the steam inlet of the second-stage steam jet pump. By supplying steam to the first-stage and second-stage steam jet pumps, the pressure before the second valve reaches the rated ejector pressure. .

[0096] Furthermore, the gas collection chamber has three air inlets, and at most one of the three air inlets is in working condition;

[0097] The gas collection chamber has three sets of exhaust ports, and all three sets of exhaust ports work simultaneously.

[0098] Furthermore, there are two vacuum spherical tanks, each connected to a gas collection chamber;

[0099] The mechanical vacuum pump is a Roots pump unit.

[0100] The beneficial effects of this invention are:

[0101] 1. The present invention provides a multi-modal vacuum ejector relay system, which sets up a gas collection chamber, a vacuum spherical tank and a mechanical vacuum pump. The mechanical vacuum pump is started to evacuate the vacuum spherical tank, the gas collection chamber, the diffuser and the vacuum test chamber, thereby establishing a simulated test environment and achieving the effects of ultra-low pressure vacuum start-up and long-term vacuum maintenance.

[0102] 2. The present invention provides a multi-modal vacuum ejection relay system, which, by setting at least two air inlets and at least two exhaust outlets in the gas collection chamber, can simultaneously connect to vacuum test chambers of different specifications, meet the test requirements of more specifications of engines to be tested, and the parallel connection of at least two exhaust outlets to two sets of steam jet pumps can improve the air ejection capability.

[0103] 3. This invention provides a multi-modal vacuum ejector relay system. By setting up two air ejector systems—a steam jet pump and an air jet pump—it establishes an exhaust system suitable for multiple ejection groups. Utilizing a diffuser-based pressure rise judgment algorithm, it opens corresponding valves at specified times to initiate vacuum relay, achieving ultra-low pressure vacuum start-up and long-term vacuum maintenance. Furthermore, it determines whether to activate the steam jet pump or the air jet pump based on the ejected gas pressure rise ratio and the test duration T, making the ejection more targeted and saving resources.

[0104] 4. The present invention provides a multi-mode vacuum ejection relay method, which, through the cooperation of a steam jet pump, a gas collection chamber and a mechanical vacuum pump, can achieve ejection relay for high flow rate, high vacuum degree and long-term vacuum test, and meet the higher requirements of rocket engine test.

[0105] 5. The present invention provides a multi-mode vacuum ejection relay method, which, through the cooperation of an air jet pump, a gas collection chamber and a mechanical vacuum pump, can achieve both atmospheric pressure and vacuum ejection relay, thus meeting the needs of rocket engine testing under more operating conditions. Attached Figure Description

[0106] Figure 1 This is a schematic diagram of the steam jet pump ejector relay structure of an embodiment of the multimodal vacuum ejector relay system of the present invention;

[0107] Figure 2 This is a schematic diagram of the air jet pump ejector relay structure in an embodiment of a multimodal vacuum ejector relay system of the present invention.

[0108] The attached figures are labeled as follows:

[0109] 1. Gas collection chamber; 2. Diffuser; 3. Vacuum test chamber; 4. Steam jet pump; 401. First-stage steam jet pump; 402. Second-stage steam jet pump; 5. Mechanical vacuum pump; 6. Vacuum spherical tank; 7. First valve; 8. Second valve; 9. Steam generator; 10. Third valve; 11. Fourth valve; 12. Air jet pump; 121. First-stage air jet pump; 122. Second-stage air jet pump; 13. Gas collection chamber connecting pipe; 14. Fifth valve; 15. Power air source; 16. Sixth valve; 17. Seventh valve; 18. Eighth valve. Detailed Implementation

[0110] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings and embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and 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.

[0111] Example 1

[0112] like Figure 1-2 As shown, this embodiment of the invention provides a multi-modal vacuum ejector relay system for exhausting the vacuum test chamber 3; it includes a gas collection chamber 1, a vacuum spherical tank 6, a mechanical vacuum pump 5, a steam jet pump 4, a steam generator 9, a gas collection chamber connecting pipe 13, a power air source 15, an air jet pump 12, and a diffuser 2;

[0113] This embodiment uses two 5000 m³ vacuum spherical tanks 6; three diffusers 2, each diffuser 2 connected to a vacuum test chamber 3 for rocket engine testing; three steam jet pumps 4, each steam jet pump 4 including a first-stage steam jet pump 401 and a second-stage steam jet pump 402 connected in series; two air jet pumps 12, the two air jet pumps 12 are connected in parallel on the gas collection chamber connecting pipe 13, each air jet pump 12 including a first-stage air jet pump 121 and a second-stage air jet pump 122 connected in series; the mechanical vacuum pump 5 is a Roots pump unit.

[0114] The gas collection chamber 1 is equipped with three air inlets, three exhaust outlets, a mechanical pump connection port, a spherical tank connection port, and an air ejector connection port for connecting the gas collection chamber connecting pipe 13; among them, the three sets of exhaust outlets of the gas collection chamber 1 work simultaneously.

[0115] The air inlet of the gas collecting chamber 1 is connected to the exhaust port of the diffuser 2 through the first valve 7, and the air inlet of the diffuser 2 is connected to the exhaust port of the vacuum test chamber 3.

[0116] The exhaust port of the gas collecting chamber 1 is connected to a set of steam jet pumps 4 via a second valve 8. The inlet of the steam jet pump 4 is connected to the exhaust port of the gas collecting chamber 1, and the exhaust port of the steam jet pump 4 is connected to the atmosphere. The steam inlet of the steam jet pump 4 is connected to a steam generator 9, which supplies steam to the steam jet pump 4 through the steam generator 9 so that the pressure before the valve of the second valve 8 reaches the rated ejector pressure value. ;

[0117] In this embodiment, the inlet of the first-stage steam jet pump 401 and the exhaust port of the gas collecting chamber 1 are connected through the second valve 8, and the exhaust port of the second-stage steam jet pump 402 is connected to the atmosphere.

[0118] The spherical tank connection port of the gas collection chamber 1 is connected to two vacuum spherical tanks 6 through the third valve 10;

[0119] The mechanical pump connection port of the gas collection chamber 1 is connected to the mechanical vacuum pump 5 through the fourth valve 11, and is used to perform vacuuming operations on the gas collection chamber 1, vacuum spherical tank 6, diffuser 2 and vacuum test chamber 3 by means of the mechanical vacuum pump 5.

[0120] The steam generator 9 has a first exhaust port and a second exhaust port; its first exhaust port is connected to the steam inlet of the first-stage steam jet pump 401, and its second exhaust port is connected to the steam inlet of the second-stage steam jet pump 402. By supplying steam to the first-stage steam jet pump 401 and the second-stage steam jet pump 402, the pressure before the second valve 8 reaches the rated ejector pressure value. .

[0121] One end of the gas collection chamber connecting pipe 13 is connected to the air ejector port of the gas collection chamber 1 through the fifth valve 14, and the other end is closed. Multiple air jet pump mounting holes are provided on it.

[0122] Each air jet pump 12 includes a primary air jet pump 121 and a secondary air jet pump 122 arranged in series. Both include a compressed air inlet, an ejected gas inlet and an exhaust port.

[0123] The inlet of the primary air jet pump 121 is connected to the gas collection chamber connecting pipe 13 through the first air jet pump mounting hole, and the exhaust port of the primary air jet pump 121 is connected to the gas collection chamber connecting pipe 13 through the second air jet pump mounting hole.

[0124] The inlet of the secondary air jet pump 122 is connected to the gas collection chamber connecting pipe 13 through the seventh valve 17, and its exhaust port is connected to the atmosphere.

[0125] The fifth valve 14 is installed on the air collection chamber connecting pipe 13 and is located between the first air injection pump mounting hole and the second air injection pump mounting hole;

[0126] The power air source 15 is connected to the compressed air inlet of the first-stage air jet pump 121 via the sixth valve 16, and is used to supply compressed air to the first-stage air jet pump 121 so that the inlet pressure of the ejected gas in the first-stage air jet pump 121 reaches the rated ejection pressure value. The power air source 15 is connected to the compressed air inlet of the secondary air injection pump 122 via the eighth valve 18, and is used to supply compressed air to the secondary air injection pump 122 so that the pressure before the seventh valve 17 reaches the rated ejector pressure value. .

[0127] This application also provides an ejection relay method based on the above-mentioned multimodal vacuum ejection relay system, including the following steps:

[0128] Step 1: Based on the test duration T of the rocket engine to be tested, if... If so, proceed to step 2; if Then proceed to step 7;

[0129] Step 2: Based on the parameter information of the rocket engine to be tested, obtain the test pressure value of the rocket engine to be tested. The rated ejector pressure values ​​of the first-stage steam ejector pump 401 and the second-stage steam ejector pump 402 are... The equivalent flow rate q of the entrained gas inside vacuum test chamber 3; the formula for calculating the equivalent flow rate q of the entrained gas is as follows:

[0130] ;

[0131] in, The gas flow rate for the high-temperature combustion gases produced after the rocket engine ignites;

[0132] After the rocket engine is ignited, the sprayed cooling water generates water vapor flow.

[0133] An air temperature correction factor to equate the temperature of high-temperature gas combustion gas to 20 degrees Celsius air.

[0134] This is the correction factor for the average molecular weight of high-temperature gas;

[0135] This is a correction factor for water vapor temperature.

[0136] This is the correction factor for the molecular weight of water vapor.

[0137] Step 3: Open the third valve 10, the fourth valve 11, and the first valve 7 corresponding to the vacuum test chamber 3 where the rocket engine to be tested is located, so that the gas collecting chamber 1, the vacuum spherical tank 6, the diffuser 2, and the vacuum test chamber 3 are connected into a single integrated chamber. Use the mechanical vacuum pump 5 to evacuate the integrated chamber until its pressure reaches the test pressure value. Then, close the fourth valve 11 and the mechanical vacuum pump 5;

[0138] Step 4: Start the steam generator 9 to charge steam into the primary steam jet pump 401 and the secondary steam jet pump 402 respectively, so that the pressure before the second valve 8 reaches the rated ejector pressure value. ;

[0139] Step 5: The test rocket engine is ignited. The ejected gas generated during the test is pressurized by diffuser 2 and then enters gas collection chamber 1 and vacuum spherical tank 6.

[0140] Step 6: At time t after the start of the test, the external control device sends a control command to the second valve 8 to open the second valve 8, so that the pressure value in the gas collecting chamber 1 increases to [value missing]. At this time, the second valve 8 is fully opened, and the ejected gas is discharged into the atmosphere after passing through the primary steam jet pump 401 and the secondary steam jet pump 402, completing the ejection relay of the multi-mode vacuum ejection relay system. In this embodiment The pressure is 5 kPa. The formula for calculating time t is as follows:

[0141] ;

[0142] ;

[0143] in, The pressure inside the gas collecting chamber 1 is determined by... Rise to Time required;

[0144] V is the total volume of gas collecting chamber 1 and vacuum spherical tank 6;

[0145] M is the mass number of molecules of the entrained gas:

[0146] R is the gas constant;

[0147] T is the temperature of the ejected gas;

[0148] The time required for the second valve 8 to be fully opened.

[0149] Step 7: Based on the parameter information of the rocket engine to be tested, obtain the test pressure value of the rocket engine to be tested. The rated ejector pressure values ​​of the primary air ejector pump 121 and the secondary air ejector pump 122 And the equivalent flow rate q of the ejected gas in vacuum test chamber 3; the formula for calculating the equivalent flow rate q of the ejected gas is as follows:

[0150] ;

[0151] in, The gas flow rate for the high-temperature combustion gases produced after the rocket engine ignites;

[0152] After the rocket engine is ignited, the sprayed cooling water generates water vapor flow.

[0153] An air temperature correction factor to equate the temperature of high-temperature gas combustion gas to 20 degrees Celsius air.

[0154] This is the correction factor for the average molecular weight of high-temperature gas;

[0155] This is a correction factor for water vapor temperature.

[0156] This is the correction factor for the molecular weight of water vapor.

[0157] Step 8: Based on the test pressure value of the rocket engine to be tested. Judgment, if The pressure is atmospheric pressure P, and Where K is a constant with a value range of 1.0-1.2, the first valve 7, the fifth valve 14, and the seventh valve 17 corresponding to the vacuum test chamber where the rocket engine to be tested is located are opened, and the gas discharged from the diffuser 2 is directly discharged into the atmosphere through the gas collection chamber 1, the gas collection chamber connecting pipe 13, the first-stage air jet pump 121, and the second-stage air jet pump 122. At this time, the first-stage air jet pump 121 and the second-stage air jet pump 122 do not perform air ejection action; if If the pressure is less than atmospheric pressure P, proceed to step 9;

[0158] Step 9: Open the third valve 10, the fourth valve 11, and the first valve 7 to connect the gas collecting chamber 1, the vacuum spherical tank 6, the diffuser 2, and the vacuum test chamber 3 into a single integrated chamber. Use the mechanical vacuum pump 5 to evacuate the integrated chamber until the pressure reaches the specified value. Then, close the fourth valve 11 and the mechanical vacuum pump 5;

[0159] Step 10: Start the power air source 15 and open the eighth valve 18 to fill the secondary air injection pump 122 with compressed air, so that the pressure before the seventh valve 17 reaches the rated ejector pressure value. ;

[0160] Step 11: The test rocket engine is ignited. The ejected gas generated during the test is pressurized by diffuser 2 and then enters gas collection chamber 1 and vacuum spherical tank 6.

[0161] Step 12: After the test begins, control the test via an external control device. At any given time, a control command is sent to the seventh valve 17 to open it, thereby increasing the pressure value inside the gas collecting chamber 1 to [a certain value]. At this time, the seventh valve 17 is fully open, and the ejected gas is discharged into the atmosphere through the first-stage air jet pump 121 and the second-stage air jet pump 122 in sequence. At this time, the first-stage air jet pump 121 does not perform air ejection action. The formula for calculating time is as follows:

[0162] ;

[0163] ;

[0164] in, The pressure inside the gas collecting chamber 1 is determined by... Rise to Time required;

[0165] V is the total volume of gas collecting chamber 1 and vacuum spherical tank 6;

[0166] M is the mass number of molecules of the entrained gas:

[0167] R is the gas constant;

[0168] T is the temperature of the ejected gas;

[0169] The time required for the seventh valve 17 to be fully opened.

[0170] Step 13: Open the sixth valve 16, and pressurize the first-stage air jet pump 121 with compressed air through the power air source 15. Start the first-stage air jet pump 121, and the first-stage air jet pump 121 and the second-stage air jet pump 122 connected in series will jointly discharge the ejected gas into the atmosphere, completing the multi-mode vacuum ejection relay.

[0171] Example 2

[0172] The multimodal vacuum ejector relay system of this embodiment is based on Embodiment 1, except for the gas collection chamber connecting pipe 13, power air source 15 and air jet pump 12. The corresponding ejector relay method executes steps 2-6.

[0173] The above are merely specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed in the present invention should be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A multi-modal vacuum-evacuation ejector relay method, characterized by, Includes the following steps: Step 1: Construct a multimodal vacuum ejector relay system for exhausting the vacuum test chamber (3); including a gas collection chamber (1), a vacuum spherical tank (6), a mechanical vacuum pump (5), a steam jet pump (4), a steam generator (9), and a diffuser (2); The gas collecting chamber (1) is provided with an air inlet, an exhaust outlet, a mechanical pump connection port, and a spherical tank connection port; the air inlet of the gas collecting chamber (1) is connected to the exhaust outlet of the diffuser (2) through a first valve (7), and the air inlet of the diffuser (2) is connected to the exhaust outlet of the vacuum test chamber (3); the exhaust outlet of the gas collecting chamber (1) is connected to a set of steam jet pumps (4) through a second valve (8), the inlet of the steam jet pumps (4) is connected to the gas collecting chamber (1), the exhaust outlet of the steam jet pumps (4) is connected to the atmosphere, and the steam inlet of the steam jet pumps (4) is connected to the steam generator (9) for supplying steam to the steam jet pumps (4) through the steam generator (9) so that the pressure before the valve of the second valve (8) reaches the rated ejection pressure value. The spherical tank connection port of the gas collecting chamber (1) is connected to the vacuum spherical tank (6) through the third valve (10); the mechanical pump connection port of the gas collecting chamber (1) is connected to the mechanical vacuum pump (5) through the fourth valve (11), which is used to evacuate the gas collecting chamber (1), vacuum spherical tank (6), diffuser (2) and vacuum test chamber (3) through the mechanical vacuum pump (5); the formula for calculating the equivalent flow rate q of the ejected gas is as follows: ； in, The gas flow rate for the high-temperature combustion gases produced after the rocket engine ignites; After the rocket engine is ignited, the sprayed cooling water generates water vapor flow. Kt = air temperature correction factor to equate high temperature gas temperature to 20 degrees Celsius air temperature; M is the average molecular weight correction factor for high temperature gas; Kw is the water vapor temperature correction factor; Mw is the molecular weight of water; and Step 2: Based on the parameter information of the rocket engine to be tested, obtain the test pressure value of the rocket engine to be tested. The rated ejector pressure of the steam jet pump (4) is [value missing]. The equivalent flow rate q of the ejected gas inside the vacuum test chamber (3); Step 3: Open the third valve (10), the fourth valve (11), and the first valve (7) to connect the gas collecting chamber (1), the vacuum spherical tank (6), the diffuser (2), and the vacuum test chamber (3) into a single integrated chamber. Use a mechanical vacuum pump (5) to evacuate the integrated chamber until its pressure reaches the test pressure value. Then, close the fourth valve (11) and the mechanical vacuum pump (5); Step 4: Start the steam generator (9) to charge steam into the steam jet pump (4) so ​​that the pressure before the second valve (8) reaches the rated ejector pressure value. ; Step 5: The rocket engine to be tested is ignited. The ejected gas generated during the test is pressurized by the diffuser (2) and then enters the gas collection chamber (1) and the vacuum spherical tank (6); the formula for calculating time t is as follows: ； ； wherein the time required for the pressure in the gas collection chamber (1) to rise from p1 to p2 ; V is the total volume of the gas collecting chamber (1) and the vacuum spherical tank (6); M is the mass number of molecules of the entrained gas: R is the gas constant; T is the temperature of the ejected gas; time taken for the second valve (8) to fully open; Step 6: At time t after the start of the test, send a control command to the second valve (8) through the external control device to open the second valve (8) so that the pressure value in the gas collecting chamber (1) increases to t. At that time, the second valve (8) is fully opened, and the ejected gas is discharged into the atmosphere after passing through the steam jet pump (4), thus completing the multi-mode vacuum ejection relay.

2. A multimode vacuum evacuation ejector relay system for the evacuation of a vacuum test chamber (3); characterized by: It includes a gas collection chamber (1), a vacuum spherical tank (6), a mechanical vacuum pump (5), a steam jet pump (4), a steam generator (9) and a diffuser (2), a gas collection chamber connecting pipe (13), a power air source (15) and at least one set of air jet pumps (12). The gas collection chamber (1) is provided with an air inlet, an exhaust outlet, a mechanical pump connection port and a spherical tank connection port; The air inlet of the gas collecting chamber (1) is connected to the exhaust port of the diffuser (2) through the first valve (7), and the air inlet of the diffuser (2) is connected to the exhaust port of the vacuum test chamber (3). The exhaust port of the gas collecting chamber (1) is connected to a set of steam jet pumps (4) through a second valve (8). The inlet of the steam jet pump (4) is connected to the gas collecting chamber (1), the exhaust port of the steam jet pump (4) is connected to the atmosphere, and the steam inlet of the steam jet pump (4) is connected to the steam generator (9) for supplying steam to the steam jet pump (4) through the steam generator (9) so that the pressure before the valve of the second valve (8) reaches the rated ejection pressure value. ; The spherical tank connection port of the gas collection chamber (1) is connected to the vacuum spherical tank (6) through the third valve (10); The mechanical pump connection port of the gas collection chamber (1) is connected to the mechanical vacuum pump (5) through the fourth valve (11) for evacuating the gas collection chamber (1), vacuum spherical tank (6), diffuser (2) and vacuum test chamber (3) by the mechanical vacuum pump (5); One end of the gas collection chamber connecting pipe (13) is connected to the gas collection chamber (1) through the fifth valve (14), and the other end is closed. Multiple air jet pump mounting holes are provided on it. Each air jet pump (12) includes a primary air jet pump (121) and a secondary air jet pump (122) arranged in series, both of which include a compressed air inlet, an ejected gas inlet and an exhaust port; The inlet of the primary air jet pump (121) is connected to the gas collection chamber connecting pipe (13) through the first air jet pump mounting hole, and the exhaust port of the primary air jet pump (121) is connected to the gas collection chamber connecting pipe (13) through the second air jet pump mounting hole. The inlet of the secondary air jet pump (122) is connected to the gas collection chamber connecting pipe (13) through the seventh valve (17), and its exhaust port is connected to the atmosphere; The fifth valve (14) is installed on the gas collection chamber connecting pipe (13) and is located between the first air jet pump mounting hole and the second air jet pump mounting hole; The power air source (15) is connected to the compressed air inlet of the first-stage air jet pump (121) through the sixth valve (16), and is used to supply compressed air to the first-stage air jet pump (121) through the power air source (15) so that the inlet pressure of the ejected gas of the first-stage air jet pump (121) reaches the rated ejection pressure value. The power air source (15) is connected to the compressed air inlet of the secondary air injection pump (122) through the eighth valve (18), and is used to supply compressed air to the secondary air injection pump (122) through the power air source (15) so that the pressure before the seventh valve (17) reaches the rated ejector pressure value. .

3. The multimodal vacuum ejection relay system according to claim 2, characterized in that: The air jet pump (12) consists of two sets, which are connected in parallel on the air collection chamber connecting pipe (13).

4. The multimodal vacuum ejection relay system according to claim 2, characterized in that: The gas collecting chamber (1) has at least two air inlets and two air outlets; Each air inlet of the gas collecting chamber (1) is connected to the exhaust port of a diffuser (2), and each air inlet of the diffuser (2) is connected to the exhaust port of a vacuum test chamber (3). Each exhaust port of the gas collection chamber (1) is connected to a set of steam jet pumps (4), and each set of steam jet pumps (4) includes a first-stage steam jet pump (401) and a second-stage steam jet pump (402) connected in series. The inlet of the first-stage steam jet pump (401) is connected to an exhaust port of the gas collection chamber (1) via a second valve (8), and the exhaust port of the second-stage steam jet pump (402) is connected to the atmosphere. The steam generator (9) has a first exhaust port and a second exhaust port; its first exhaust port is connected to the steam inlet of the first-stage steam jet pump (401), and its second exhaust port is connected to the steam inlet of the second-stage steam jet pump (402). By supplying steam to the first-stage steam jet pump (401) and the second-stage steam jet pump (402), the pressure before the valve of the second valve (8) reaches the rated ejector pressure value. .

5. The multi-modal vacuum-evacuating ejector relay system of claim 4, wherein: The gas collection chamber (1) has three air inlets, and at most one of the three air inlets is in working condition; The gas collection chamber (1) has three sets of exhaust ports, and all three sets of exhaust ports work simultaneously.

6. The multi-modal vacuum-evacuating ejector relay system of claim 5, wherein: There are two vacuum spherical tanks (6), and the two vacuum spherical tanks (6) are respectively connected to the gas collection chamber (1); The mechanical vacuum pump (5) is a Roots pump unit.

7. A multi-modal vacuum evacuation ejector relay method based on the multi-modal vacuum evacuation ejector relay system of claim 2, characterized by, Includes the following steps: Step S1: Based on the test duration T of the rocket engine to be tested, if... If so, proceed to step S2; if If so, proceed to step S7; Step S2: Obtain the test pressure value of the rocket engine under test based on the parameter information of the rocket engine under test. The rated ejector pressure of the steam jet pump (4) is [value missing]. The equivalent flow rate q of the ejected gas inside the vacuum test chamber (3); Step S3: Open the third valve (10), the fourth valve (11), and the first valve (7) to connect the gas collecting chamber (1), the vacuum spherical tank (6), the diffuser (2), and the vacuum test chamber (3) into a single integrated chamber. Use a mechanical vacuum pump (5) to evacuate the integrated chamber until its pressure reaches the test pressure value. Then, close the fourth valve (11) and the mechanical vacuum pump (5); Step S4, start the steam generator (9) to fill steam into the steam jet pump (4), so that the valve front pressure of the second valve (8) reaches the rated injection pressure value ; Step S5: The rocket engine to be tested is ignited. The ejected gas generated during the test is pressurized by the diffuser (2) and then enters the gas collection chamber (1) and the vacuum spherical tank (6). Step S6, at time t after the start of the test, the external control device sends a control command to the second valve (8) to open the second valve (8) to increase the pressure in the plenum (1) to When the second valve (8) is fully open, the gas being injected is discharged into the atmosphere after passing through the steam ejector pump (4). Step S7: Obtain the test pressure value of the rocket engine under test based on the parameter information of the rocket engine under test. The rated ejector pressure of the air jet pump (12) The equivalent flow rate q of the ejected gas inside the vacuum test chamber (3); Step S8: Based on the test pressure value of the rocket engine to be tested. Judgment, if If the pressure is atmospheric P, then the first valve (7), the fifth valve (14), and the seventh valve (17) are opened, and the gas discharged from the diffuser (2) is directly discharged into the atmosphere through the gas collection chamber (1), the gas collection chamber connecting pipe (13), the first-stage air jet pump (121), and the second-stage air jet pump (122). At this time, the first-stage air jet pump (121) and the second-stage air jet pump (122) do not perform air ejection. If the pressure is less than atmospheric pressure P, then proceed to step S4; Step S9, open the third valve (10), the fourth valve (11) and the first valve (7), make the gas collecting chamber (1), the vacuum ball tank (6), the diffuser (2), the vacuum test cabin (3) communicate as a whole chamber, carry out vacuumizing to the whole chamber through the mechanical vacuum pump (5), make its pressure value reach Afterwards, close the fourth valve (11) and the mechanical vacuum pump (5); Step S10, start the power source (15), and open the eighth valve (18) to fill compressed air into the secondary air injection pump (122), so that the pressure before the seventh valve (17) reaches the rated injection pressure value ; Step S11: The rocket engine to be tested is ignited. The ejected gas generated during the test is pressurized by the diffuser (2) and then enters the gas collection chamber (1) and the vacuum spherical tank (6). Step S12: After the test begins, the external control device is used to control the test. At any given time, a control command is sent to the seventh valve (17) to open the seventh valve (17) so that the pressure value in the gas collecting chamber (1) increases to a certain level. At this time, the seventh valve (17) is fully opened, and the ejected gas is discharged into the atmosphere through the first-stage air jet pump (121) and the second-stage air jet pump (122) in sequence. At this time, the first-stage air jet pump (121) does not perform air ejection action. Step S13: Open the sixth valve (16) and fill the first-stage air jet pump (121) with compressed air through the power air source (15). Start the first-stage air jet pump (121). The first-stage air jet pump (121) and the second-stage air jet pump (122) connected in series will jointly discharge the ejected gas into the atmosphere, completing the multi-mode vacuum ejection relay.

8. The multi-modal vacuum-evacuation bootstrapping method of claim 7, wherein, In steps S2 and S7, the formula for calculating the equivalent flow rate q of the ejected gas is as follows: ； wherein, is the gas flow rate of the high-temperature combustion gas generated after the rocket engine is ignited; For the rocket engine ignition, the spray cooling water produces water vapor flow; Kt = air temperature correction factor to equate high temperature gas temperature to 20 degrees Celsius air temperature; M is the average molecular weight correction factor for high temperature gas; Kw is the water vapor temperature correction factor; Mw is the molecular weight of water; and In step S6, the formula for calculating time t is as follows: ； ； wherein is the time required for the pressure in the gas collection chamber (1) to rise from to to V is the total volume of the gas collecting chamber (1) and the vacuum spherical tank (6); M is the mass number of molecules of the entrained gas; R is the gas constant; T is the temperature of the ejected gas; time taken for the second valve (8) to fully open; In step S13, The time calculation formula is as follows: ； ； wherein is the time required for the pressure in the gas collection chamber (1) to rise from to to V is the total volume of the gas collecting chamber (1) and the vacuum spherical tank (6); M is the mass number of molecules of the entrained gas; R is the gas constant; T is the temperature of the ejected gas; the time taken for the seventh valve (17) to fully open.

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