CN114414248B - Liquid rocket engine test water hammer pressure wave reduction pipeline and reduction method - Google Patents
Liquid rocket engine test water hammer pressure wave reduction pipeline and reduction method Download PDFInfo
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- CN114414248B CN114414248B CN202111434759.7A CN202111434759A CN114414248B CN 114414248 B CN114414248 B CN 114414248B CN 202111434759 A CN202111434759 A CN 202111434759A CN 114414248 B CN114414248 B CN 114414248B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention belongs to a water hammer pressure wave reduction method, and provides a water hammer pressure wave reduction pipeline and a water hammer pressure wave reduction method for a liquid rocket engine test, which are used for solving the technical problem that the reliability of an engine inlet valve, a propellant supply system valve and a test system clamp bracket is extremely risky due to secondary pressure waves of system water hammer pressure in the conventional propellant high-flow high-pressure extrusion liquid rocket engine test.
Description
Technical Field
The invention belongs to a water hammer pressure wave reduction method, and particularly relates to a water hammer pressure wave reduction pipeline and a water hammer pressure wave reduction method for a liquid rocket engine test.
Background
In the conventional propellant high-flow high-pressure extrusion liquid rocket engine test, when the engine is shut down, the propellant supply system can generate water hammer pressure related to flow and pressure, and the water hammer pressure of the system under the high flow can reach 70MPa or higher in the valve response time of 10ms, and a plurality of secondary pressure waves exist in the water hammer pressure, and the peak value of the secondary pressure waves reaches more than 50MPa, so that great risks are caused to the reliability of an engine inlet valve, a propellant supply system valve and a test system clamp bracket.
Disclosure of Invention
The invention provides a liquid rocket engine test water hammer pressure wave reduction pipeline and a reduction method, which are used for solving the technical problem that the reliability of an engine inlet valve, a propellant supply system valve and a test system clamp bracket is greatly risked by secondary pressure waves of system water hammer pressure when an engine is shut down in the conventional high-flow high-pressure extrusion liquid rocket engine test of a propellant.
In order to achieve the above purpose, the present invention provides the following technical solutions:
the liquid rocket engine test water hammer pressure wave reduction pipeline is characterized by comprising a high-pressure discharge pipeline and a recovery container;
the inlet end of the high-pressure discharge pipeline is used for being communicated with a main pipeline of a propellant supply system at the front end of the opposite joint of the engine, and the outlet end of the high-pressure discharge pipeline is connected with the recovery container;
and a manual valve, a flowmeter and a pneumatic valve are sequentially arranged between the engine butt joint and the recovery container in the high-pressure discharge pipeline.
Further, the calibers of the manual valve and the pneumatic valve are 20mm, and the nominal pressure is 23MPa;
the caliber of the flowmeter is 15mm, and the nominal pressure is 15MPa.
The invention also provides a liquid rocket engine test water hammer pressure wave reduction method, which is characterized by comprising the following steps of:
s1, a high-pressure discharge pipeline is built at the front end of a main pipeline of a propellant supply system, which is positioned at an opposite joint of an engine;
the inlet end of the high-pressure discharge pipeline is communicated with a main pipeline of a propellant supply system at the front end of the opposite joint of the engine, and the outlet end of the high-pressure discharge pipeline is connected with the recovery container;
a manual valve, a flowmeter and a pneumatic valve are sequentially arranged between the high-pressure discharge pipeline and the recovery container from the engine butt joint;
s2, before the engine is ignited, opening a pneumatic valve, controlling the opening of a manual valve, discharging propellant to a recovery container through a high-pressure discharge pipeline, regulating the target flow of the high-pressure discharge pipeline to 2-3kg/S through observing a flowmeter, closing the pneumatic valve, and fixing a handle of the manual valve; s3, when the engine is started for 1-3 seconds, remotely opening the pneumatic valve, discharging the propellant to the recovery container through the high-pressure discharge pipeline, and keeping the pneumatic valve open in the test process;
and S4, remotely closing the pneumatic valve after the engine is shut down for 1-3 seconds, and stopping discharging the propellant to the recovery container through the high-pressure discharge pipeline.
Further, in step S2, the target flow rate is 3kg/S.
Further, in step S3, the time is 1-3S before the ignition of the engine, specifically 3S before the ignition of the engine; in step S4, the time is 1-3S after the engine is shut down, specifically 3S after the engine is shut down.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the liquid rocket engine test water hammer pressure wave reduction pipeline, the water hammer secondary pressure wave can be effectively restrained by adding the high-pressure discharge pipeline, the reliability of an engine inlet valve, a propellant supply system valve and a test system clamp bracket can be improved only by slightly changing an existing test system, and the discharge flow of the high-pressure discharge pipeline can be adjusted by arranging the manual valve, the flowmeter and the pneumatic valve.
2. The calibers and nominal pressures of the manual valve, the pneumatic valve and the flowmeter are designed aiming at the liquid rocket engine test, and can meet the test requirements.
3. According to the liquid rocket engine test water hammer pressure wave reduction method, the target flow of the high-pressure discharge pipeline, namely the discharge flow after test shutdown, is adjusted in advance, the pneumatic valve is opened to discharge in a certain time before the engine is ignited, and the discharge is stopped until the engine is shut down in a certain time, and through comparison verification, the secondary water hammer pressure wave peak value can be well reduced under the condition that the high-pressure discharge pipeline is arranged to discharge the propellant through the method.
Drawings
FIG. 1 is a schematic illustration of an embodiment of a liquid rocket engine test water hammer pressure wave attenuation line of the present invention;
FIG. 2 is a graph of shutdown water hammer pressure for a conventional propellant high flow high pressure extrusion liquid rocket engine test without a high pressure discharge line;
FIG. 3 is a graph of shutdown water hammer pressure after installation of the liquid rocket engine test water hammer pressure wave reduction circuit of the present invention under the same conditions as FIG. 2.
Wherein, 1-high pressure discharge pipeline, 2-recovery container, 3-manual valve, 4-flowmeter, 5-pneumatic valve, 6-propellant supply system main line, 7-engine interface.
Detailed Description
The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention and the accompanying drawings, and it is apparent that the described embodiments do not limit the present invention.
Because the secondary pressure wave peak value of the system water hammer can influence the reliability of an engine inlet valve, a propellant supply system valve and a test system clamp bracket, the invention aims at the water hammer pressure wave generated when the engine is shut down, avoids the damage to the system and products caused by repeated impact of the secondary water hammer pressure wave in the process of testing, and provides a liquid rocket engine test water hammer pressure wave reduction pipeline and a liquid rocket engine test water hammer pressure wave reduction method, which can effectively reduce the secondary water hammer pressure wave. The water hammer pressure wave reduction pipeline comprises a high-pressure discharge pipeline 1 and a recovery container 2, wherein the inlet end of the high-pressure discharge pipeline 1 is communicated with a main pipeline 6 of a propellant supply system at the front end of an engine butt joint 7, the outlet end of the high-pressure discharge pipeline 1 is connected with the recovery container 2, the inlet end of the high-pressure discharge pipeline 1 is arranged close to the front end of the engine butt joint 7, and a manual valve 3, a flowmeter 4 and a pneumatic valve 5 are sequentially arranged between the engine butt joint 7 of the high-pressure discharge pipeline 1 and the recovery container 2. As a preferable scheme, for adapting to test requirements, the flowmeter 4 can adopt a DN20/23MPa turbine flowmeter, the pneumatic valve 5 can adopt a DN20/23MPa pneumatic stop valve for controlling the high-pressure discharge pipeline 1 to be opened and closed in the test process, and the pneumatic valve 5 is mainly arranged because the pneumatic valve cannot be closed in the test process, and can be conveniently operated through the cooperation of the manual valve 3 and the pneumatic valve 5, and the purpose of opening and closing the high-pressure discharge pipeline 1 according to requirements is achieved.
The high-pressure discharge pipeline 1 is arranged in front of the propellant supply pipeline 6 to the engine butt joint 7, the manual valve 3 on the high-pressure discharge pipeline 1 is always opened before and during the test, and when the engine is shut down, the secondary pressure peak of the water hammer pressure can be discharged through the high-pressure discharge pipeline 1, so that the damage of the secondary water hammer pressure wave to the system is effectively reduced. Meanwhile, as the high-pressure discharge pipeline 1 of the discharge path is kept open in the whole test run process, the abrupt change of the system flow cannot occur in the working process of the engine, the technical risk caused by the excretion of the propellant can be avoided, the high-pressure discharge pipeline 1 is connected into the recovery container 2 of the propellant, and the discharged propellant is recovered into the recovery container 2.
Before the test, the opening of the manual valve 3 is adjusted to control the flow of the high-pressure discharge pipeline 1, after the target flow is achieved through adjustment, the handle of the manual valve 3 is fixed, the pneumatic valve 5 is opened remotely 1-3s before the engine is ignited, the high-pressure discharge pipeline 1 is kept open in the test process, and the secondary water hammer pressure wave peak value is restrained when the engine is shut down. And after the engine is shut down, the pneumatic valve 5 is remotely closed for 1-3 seconds, and the high-pressure discharge pipeline 1 is disconnected.
The specific water hammer pressure wave reduction flow is as follows:
1) At the front end of the engine butt joint 7, a high-pressure discharge pipeline 1 is arranged, the inlet end of the high-pressure discharge pipeline 1 is communicated with a main pipeline 6 of the propellant supply system at the front end of the engine butt joint 7, the outlet end of the high-pressure discharge pipeline 1 is connected with the recovery container 2, the high-pressure discharge pipeline 1 adopts a DN20 pipeline, the design pressure of the high-pressure discharge pipeline 1 and a valve thereon is 23MPa, and the high-pressure discharge pipeline is aligned with the main pipeline 6 of the propellant supply system.
2) A manual valve 3, a flowmeter 4, a pneumatic valve 5 and the like are sequentially arranged between the engine butt joint 7 and the recovery container 2 on the high-pressure discharge pipeline 1.
3) The high-pressure discharge pipeline 1 is connected with a liquid inlet of the recovery container 2, and propellant discharged in the whole test run process flows into the recovery container 2.
4) The test run goes forward to debug the high-pressure discharge pipeline 1, opens the pneumatic valve 5, controls the flow through controlling the opening degree of the manual valve 3, discharges the propellant to the recovery container 2 through the high-pressure discharge pipeline 1, adjusts the target flow of the high-pressure discharge pipeline 1 through observing the flowmeter 4, achieves the target flow through debugging, and the optimal flow is 3kg/s, closes the pneumatic valve 5 after the debugging is completed, and fixes the handle of the manual valve 3.
5) The pneumatic valve 5 is remotely opened for 1-3s before the engine is ignited, the propellant is discharged through the high-pressure discharge pipeline 1, the high-pressure discharge pipeline 1 is kept open in the test process, and the secondary water hammer pressure wave is restrained through the high-pressure discharge pipeline 1 when the engine is shut down.
6) And after the engine is shut down, the optimal time is 3s, the pneumatic valve 5 is remotely closed, the high-pressure discharge pipeline 1 is disconnected, and the propellant discharge is stopped.
As shown in FIG. 2, the highest water hammer pressure is 66.55MPa when the propellant is not discharged through the high-pressure discharge pipeline 1 under the condition of the system flow of the order of 50kg/s, and the second pressure peak value is still in the order of 58 MPa. As shown in fig. 3, after the high-pressure discharge pipeline 1 is arranged, in the test process, the high-pressure discharge pipeline 1 is opened to a flow of 1.2kg, and the second pressure peak can be controlled to be below 30MPa, so that a good secondary water hammer pressure wave peak reduction effect is achieved.
The foregoing description is only illustrative of the present invention and is not intended to limit the scope of the invention, and all equivalent structural changes made by the present invention and the accompanying drawings, or direct or indirect application in other related technical fields, are included in the scope of the present invention.
Claims (4)
1. A liquid rocket engine test water hammer pressure wave reduction method is realized through a reduction pipeline, wherein the reduction pipeline comprises a high-pressure discharge pipeline (1) and a recovery container (2);
the method is characterized by comprising the following steps of:
s1, a high-pressure discharge pipeline (1) is built at the front end of a main pipeline (6) of a propellant supply system, which is positioned at an engine butt joint (7);
the inlet end of the high-pressure discharge pipeline (1) is communicated with a main pipeline (6) of a propellant supply system at the front end of the engine butt joint (7), and the outlet end of the high-pressure discharge pipeline is connected with the recovery container (2);
a manual valve (3), a flowmeter (4) and a pneumatic valve (5) are sequentially arranged between the engine butt joint (7) and the recovery container (2) in the high-pressure discharge pipeline (1);
s2, before the engine is ignited, opening a pneumatic valve (5), controlling the opening of a manual valve (3), discharging propellant to a recovery container (2) through a high-pressure discharge pipeline (1), regulating the target flow of the high-pressure discharge pipeline (1) to 2-3kg/S through observing a flowmeter (4), closing the pneumatic valve (5), and fixing a handle of the manual valve (3);
s3, when the engine is started for 1-3 seconds, the pneumatic valve (5) is opened remotely, propellant is discharged to the recovery container (2) through the high-pressure discharge pipeline (1), and the pneumatic valve (5) is kept open in the test process;
and S4, remotely closing the pneumatic valve (5) when the engine is shut down for 1-3S, and stopping discharging the propellant to the recovery container (2) through the high-pressure discharge pipeline (1).
2. A method of damping water hammer pressure waves in a liquid rocket engine test as recited in claim 1, wherein: in the step S2, the target flow is 3kg/S.
3. A method for damping water hammer pressure waves in a liquid rocket engine test as recited in claim 1 or 2, wherein: in step S3, the time is 1-3S before the ignition of the engine, specifically 3S before the ignition of the engine; in step S4, the time is 1-3S after the engine is shut down, specifically 3S after the engine is shut down.
4. A method of damping water hammer pressure waves for liquid rocket engine test as recited in claim 3, wherein: the caliber of the manual valve (3) and the caliber of the pneumatic valve (5) are 20mm, and the nominal pressure is 23MPa; the caliber of the flowmeter (4) is 15mm, and the nominal pressure is 15MPa.
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| CN202111434759.7A CN114414248B (en) | 2021-11-29 | 2021-11-29 | Liquid rocket engine test water hammer pressure wave reduction pipeline and reduction method |
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| CN202111434759.7A CN114414248B (en) | 2021-11-29 | 2021-11-29 | Liquid rocket engine test water hammer pressure wave reduction pipeline and reduction method |
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| CN114414248B true CN114414248B (en) | 2023-08-22 |
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| CN106415215A (en) * | 2014-06-03 | 2017-02-15 | 赛峰航空器发动机 | Method and system for evaluating a flow rate of a fluid |
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| CN214309491U (en) * | 2021-03-23 | 2021-09-28 | 中国航发商用航空发动机有限责任公司 | Engine test bed and fuel system thereof |
| CN113446132A (en) * | 2021-06-29 | 2021-09-28 | 西安航天动力试验技术研究所 | Water hammer suppression system and method for liquid rocket engine test propellant supply system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| IT1286107B1 (en) * | 1996-06-18 | 1998-07-07 | Simpro S P A | METHOD AND SYSTEM FOR CARRYING OUT COLD TESTS ON AN INTERNAL ICE ENGINE AND ENGINE SUITABLE TO BE TESTED WITH THIS METHOD. |
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Patent Citations (8)
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| US6336440B1 (en) * | 1998-06-10 | 2002-01-08 | Fev Motorentechnik Gmbh | Misfire detection method for a piston combustion engine with electromagnetic fuel charge valve |
| CN101539485A (en) * | 2009-04-24 | 2009-09-23 | 北京航空航天大学 | Electric propulsion test platform liquid propellant supplying device |
| CN101706368A (en) * | 2009-11-04 | 2010-05-12 | 北京航空航天大学 | Multifunction test control desk design of high-saturation vapour pressure liquid at room temperature |
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| JP2016061263A (en) * | 2014-09-19 | 2016-04-25 | 三菱重工メカトロシステムズ株式会社 | Rocket engine high altitude combustion test equipment, and method of operating rocket engine high altitude combustion test equipment |
| CN110595760A (en) * | 2019-10-27 | 2019-12-20 | 楼蓝科技(苏州)有限公司 | Test bed system suitable for measuring fuel nozzle main pipe of combustion chamber of gas turbine |
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