CN111677600B - Method for accurately controlling blowing pressure of floating ring of multi-start rocket engine - Google Patents
Method for accurately controlling blowing pressure of floating ring of multi-start rocket engine Download PDFInfo
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- CN111677600B CN111677600B CN202010512510.2A CN202010512510A CN111677600B CN 111677600 B CN111677600 B CN 111677600B CN 202010512510 A CN202010512510 A CN 202010512510A CN 111677600 B CN111677600 B CN 111677600B
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- 238000007667 floating Methods 0.000 title claims abstract description 83
- 238000007664 blowing Methods 0.000 title claims abstract description 71
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000012360 testing method Methods 0.000 claims abstract description 30
- 239000011148 porous material Substances 0.000 claims abstract description 24
- 238000009826 distribution Methods 0.000 claims abstract description 11
- 239000007789 gas Substances 0.000 claims description 54
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 24
- 229910052757 nitrogen Inorganic materials 0.000 claims description 12
- 210000001503 joint Anatomy 0.000 claims description 6
- 230000006641 stabilisation Effects 0.000 claims description 6
- 238000011105 stabilization Methods 0.000 claims description 6
- 238000001914 filtration Methods 0.000 claims description 4
- 238000004140 cleaning Methods 0.000 claims description 3
- 238000005238 degreasing Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 claims description 3
- 238000002474 experimental method Methods 0.000 claims description 3
- 239000000126 substance Substances 0.000 claims description 3
- 239000007788 liquid Substances 0.000 abstract description 8
- 238000007789 sealing Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 abstract description 2
- 238000007796 conventional method Methods 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a sealing method for a floating ring of a turbopump of a liquid rocket engine, in particular to blowing off of the floating ring of the rocket engine after multiple startingAnd (3) a pressure precise control method. The invention aims to solve the technical problems of poor control accuracy, high difficulty in replacing a flow distribution pore plate and long time consumption in the conventional method for controlling the blowing pressure of the floating ring of the multi-start rocket engine, and provides a method for accurately controlling the blowing pressure of the floating ring of the multi-start rocket engine. The method comprises the following steps: 1) blowing test is carried out on the floating ring, and the pressure P of the blowing gas circuit of the floating ring is recorded2And the aperture D of the flow distribution orifice plate2The value of (d); 2) setting the pressure P of the source of the blowing-off total gas path1Blowing off the aperture D of the total gas path pore plate1And a series of floating ring medium leakage equivalent apertures D3Drawing a model selection diagram of the shunt hole plate; 3) finding and point (D) on the selection graph of the splitter plate2，P2) Determining the aperture of the required splitter plate according to the closest curve; 4) and placing the shunt hole plate in the blowing pipeline.
Description
Technical Field
The invention relates to a sealing method for a floating ring of a turbopump of a liquid rocket engine, in particular to a method for accurately controlling blowing pressure of the floating ring of the rocket engine after multiple starts.
Background
The sealing performance of the floating ring is one of key indexes which restrict the working efficiency, reliability, operation cost and energy consumption of mechanical equipment, and directly influences the safety performance and continuous operation capability of the whole unit. In the fields of aerospace, metallurgical machinery, petrochemical industry and the like, along with the development of high speed and large scale of equipment, the requirement on the sealing performance of the floating ring is higher and higher, and especially the requirement on the sealing performance of the floating ring is more rigorous under the special working conditions of high pressure, high speed, high temperature, low temperature and the like of a liquid rocket engine. The floating ring seal belongs to clearance seal, mainly seals by blowing pressure in the working process, and how to control the blowing pressure is a key factor for realizing the sealing performance of the floating ring.
The floating ring of the turbopump of the liquid rocket engine can be worn to different degrees after test run, so that the leakage amount of a medium is changed, the blowing pressure is changed, the blowing test must be carried out because the liquid rocket engine needs to be started for many times, the blowing pressure of the floating ring is changed, the effective sealing of the medium cannot be realized, and the adjustment of the blowing pressure of the floating ring is realized by generally replacing a flow dividing pore plate in a pipeline so as to ensure the blowing pressure.
At present, the initial diffluence orifice plate aperture of liquid rocket engine is 1.8mm, after the test run, if the floating ring department medium leakage volume increase, then change the diffluence orifice plate in aperture, if the floating ring department medium leakage volume reduces, then change the diffluence orifice plate of aperture, because of unable accurate estimation diffluence orifice plate aperture size, generally need to change the orifice plate more than 3 times, could blow off pressure adjustment for 0.5 +/-0.05 MPa, the accuracy is relatively poor, and because liquid rocket engine system pipeline is very complicated, the diffluence orifice plate is changed the degree of difficulty greatly, the floating ring blows off simultaneously experimental multi-system collaborative operation that relates to, often consuming time about one day, the efficiency of handling after the engine test run has seriously been influenced.
Disclosure of Invention
The invention aims to solve the technical problems of poor control accuracy, high difficulty in replacing a flow distribution pore plate and long time consumption in the prior art, and provides a method for accurately controlling the blowing pressure of a floating ring of a multi-start rocket engine.
In order to solve the technical problems, the technical solution provided by the invention is as follows:
a method for accurately controlling blowing pressure of a floating ring of a multi-start rocket engine is characterized by comprising the following steps:
1) the method comprises the steps of carrying out blowing test on a floating ring after test run of a rocket engine, enabling a medium of a blowing total gas circuit to pass through the floating ring, and leaking part of the medium at the floating ring, so that the blowing total gas circuit is divided into two paths, one path is a floating ring blowing shunt gas circuit, the other path is a floating ring medium leakage gas circuit, a total gas circuit pore plate is arranged in the blowing total gas circuit, a shunt pore plate is arranged in the floating ring blowing shunt gas circuit, and the pressure P of the floating ring blowing gas circuit in a system to be blown2After stabilization, record P2And the aperture D of the flow distribution orifice plate2The value of (d);
2) setting the pressure P of the source of the blowing-off total gas path1Blowing off the aperture D of the total gas path pore plate1And a series of floating ring medium leakage equivalent apertures D3According to the following formula:
by the aperture D of the shunting pore plate2Blowing off the gas path pressure P for a horizontal coordinate, floating ring2Drawing a model selection graph of the shunt hole plate for a vertical coordinate,
wherein,
P1in order to blow off the pressure of the source of the total gas path, the pressure is MPa;
P2blowing off the pressure of a gas circuit for the floating ring, wherein the pressure is MPa;
D1blowing off the aperture of the total gas path pore plate, which is mm;
D2the aperture of the shunting hole plate is mm;
D3the equivalent aperture of floating ring medium leakage is mm;
3) d obtained according to step 1)2、P2Determining the point (D)2，P2) Finding an AND point (D) on the type selection graph of the shunt orifice plate obtained in the step 2)2，P2) Setting a longitudinal coordinate value according to the experiment requirement for the closest curve, and finding a horizontal coordinate value corresponding to the longitudinal coordinate set value by using the curve, wherein the horizontal coordinate value is the aperture of the required splitter plate;
4) placing the shunting hole plate with the aperture specification of the shunting hole plate obtained in the step 3) in a floating ring blowing pipeline of a multi-start rocket engine.
Further, the specific operation of step 1) is as follows:
1.1) configuring a filter, degreasing and cleaning the filter and a nitrogen supply pipeline of a test bed, connecting the cleaned nitrogen supply pipeline of the test bed to an air inlet of an engine, arranging the filter on a butt joint pipeline of the test bed and the engine, and preventing redundant substances from entering the engine when the filter is in butt joint with the test bed;
1.2) introducing nitrogen into an air inlet of the engine to carry out nitrogen blowing, and blowing the pressure P of a gas circuit of a floating ring in a system to be blown2After stabilization, record P2And the aperture D of the flow distribution orifice plate2The numerical value of (c).
Further, in the step 1.2), the pressure P of the air inlet of the blowing-off total air path is set1Is 4 MPa.
Further, in the step 2), the source pressure P of the blowing-off total gas path is set according to the design requirement1Is 4MPa, and the aperture D of the total gas path pore plate is blown off1Is 0.82mm, and a series of equivalent apertures D of floating ring medium leakage are set according to the specification30.6, 0.8, 1.0, 1.2, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9, 2.0, 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.8, 3.0mm, respectively.
Further, in the step 1.1), the filtering precision of the filter is not lower than 5 μm.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention provides a method for accurately controlling blowing pressure of a floating ring of a multi-start rocket engine, which is based on pressure P of a floating ring blowing gas circuit after a liquid rocket engine test2Diameter D of flow distribution orifice plate2Directly on the selection pattern of the shunt orifice plateThe required diameter of the shunt orifice plate is obtained, the pressure for blowing can be accurately controlled only by replacing the shunt orifice plate once, repeated replacement of the shunt orifice plate through repeated tests is avoided, manpower and material resources are consumed, the precision and efficiency of the floating ring blowing test after the engine is tested are improved, and the reliability of the technical state of the engine is effectively guaranteed.
2. The invention provides a method for accurately controlling blowing pressure of a floating ring of a multi-start rocket engine, which sets pressure P of an air inlet of a blowing total gas path1Is 4MPa, and the aperture D of the total gas path pore plate is blown off10.82mm and a series of equivalent aperture diameters D for floating ring medium leakage30.6, 0.8, 1.0, 1.2, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9, 2.0, 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.8 and 3.0mm respectively, and the filtration precision of the filter is not less than 5 mu m, namely the blow-off pressure is controlled to be 0.5 +/-0.05 MPa.
Drawings
FIG. 1 is a schematic diagram of a floating ring blow-off system in the method for precisely controlling the pressure of the floating ring blow-off of a multi-start rocket engine according to the present invention;
FIG. 2 is a sectional view of a flow distribution orifice plate used in an embodiment of a precise control method for blow-off pressure of a floating ring of a multi-start rocket engine according to the present invention;
description of reference numerals:
1-blowing a total gas circuit, 2-blowing a shunt gas circuit by a floating ring, 3-a medium leakage gas circuit by a floating ring, 4-a total gas circuit pore plate and 5-a shunt pore plate;
P1blowing off the total gas path source pressure, P2Blow off gas path pressure by float ring, D1Blowing off the total gas path orifice diameter, D2Split orifice plate Aperture, D3-floating ring media leakage equivalent pore size.
Detailed Description
The invention will be further described with reference to the accompanying drawings.
The invention provides a method for accurately controlling blowing pressure of a floating ring of a multi-start rocket engine, which comprises the following steps:
1) blow-off test was performed on the floating ring after test run of the rocket engine, as shown in FIG. 1The medium of the blowing-off total gas circuit 1 passes through the floating ring, and part of the medium leaks from the floating ring, so that the blowing-off total gas circuit 1 is divided into two paths, one path is a floating ring blowing-off shunting gas circuit 2, the other path is a floating ring medium leakage gas circuit 3, a total gas circuit pore plate 4 is arranged in the blowing-off total gas circuit 1, a shunting pore plate 5 is arranged in the floating ring blowing-off shunting gas circuit 2, and the pressure P of the floating ring blowing-off gas circuit in the blowing-off system is treated2After stabilization, record P2And the aperture D of the flow distribution orifice plate2The value of (d);
the specific operation of the step 1) is as follows:
1.1) configuring a filter, wherein the filtering precision is not lower than 5 mu m, degreasing and cleaning the filter and a nitrogen supply pipeline of a test bed, connecting the cleaned nitrogen supply pipeline of the test bed to an air inlet of an engine, arranging the filter on a butt joint pipeline of the test bed and the engine, and preventing redundant substances from entering the engine when the filter is in butt joint with the test bed;
1.2) introducing nitrogen into an air inlet of the engine, and setting the pressure P of the air inlet1Blowing off nitrogen at 4MPa for 50s, and blowing off the pressure P of the floating ring blowing off gas circuit in the system to be blown off2After stabilization, record P2And the aperture D of the flow distribution orifice plate2Numerical value of (A), P2＝0.39MPa、D2＝1.8mm。
2) Setting the pressure P of the source of the blowing-off total gas path according to the design requirement14MPa, blowing out the aperture D of the total gas path pore plate1Setting a series of floating ring medium leakage equivalent apertures D according to the specification, wherein the equivalent aperture D is 0.82mm30.6, 0.8, 1.0, 1.2, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9, 2.0, 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.8, 3.0mm, respectively; according to the following formula:
as shown in FIG. 2, the aperture D of the orifice plate is divided2Blowing off the gas path pressure P for a horizontal coordinate, floating ring2Drawing a model selection graph of the shunt hole plate for a vertical coordinate,
wherein,
P1in order to blow off the pressure of the source of the total gas path, the pressure is MPa;
P2blowing off the pressure of a gas circuit for the floating ring, wherein the pressure is MPa;
D1blowing off the aperture of the total gas path pore plate, which is mm;
D2the aperture of the shunting hole plate is mm;
D3the equivalent aperture of floating ring medium leakage is mm;
3) p obtained by experiment20.39 (ordinate), D21.8 (abscissa), finding the curve closest to this point on the manifold plate sizing graph as D31.9; at D3On the 1.9 curve, find and P2If the abscissa of the intersection point of the horizontal line is 1.3, the diameter of the required diversion orifice plate for replacement is 1.3 mm;
4) placing the shunting hole plate 5 with the aperture specification of the shunting hole plate obtained in the step 3) in a floating ring blowing pipeline of the rocket engine for multiple times of starting, carrying out a blowing test, and carrying out P after the blowing test20.51MPa, meets the requirement.
The examination results of multiple heat tests and flight tests show that: the method can accurately control the pressure of the blowing pipeline of the floating ring of the rocket engine which is started for many times.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, and it is obvious for a person skilled in the art to modify the specific technical solutions described in the foregoing embodiments or to substitute part of the technical features, and these modifications or substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions protected by the present invention.
Claims (5)
1. A method for accurately controlling blowing pressure of a floating ring of a multi-start rocket engine is characterized by comprising the following steps:
1) the method is characterized in that a blowing test is carried out on a floating ring after test run of the rocket engine, a medium for blowing the total gas circuit (1) passes through the floating ring, and partial medium leaks from the floating ring, so that the blowing total gas circuit (1) is divided into two paths, one path is divided into two paths by blowing the floating ringThe other path of the air path (2) is a floating ring medium leakage air path (3), a total air path pore plate (4) is arranged in the blowing total air path (1), a shunt pore plate (5) is arranged in the floating ring blowing shunt air path (2), and the pressure P of the floating ring blowing air path in the system to be blown off is2After stabilization, record P2And the aperture D of the flow distribution orifice plate2The value of (d);
2) setting the pressure P of the source of the blowing-off total gas path1Blowing off the aperture D of the total gas path pore plate1And a series of floating ring medium leakage equivalent apertures D3According to the following formula:
by the aperture D of the shunting pore plate2Blowing off the gas path pressure P for a horizontal coordinate, floating ring2Drawing a model selection graph of the shunt hole plate for a vertical coordinate,
wherein,
P1in order to blow off the pressure of the source of the total gas path, the pressure is MPa;
P2blowing off the pressure of a gas circuit for the floating ring, wherein the pressure is MPa;
D1blowing off the aperture of the total gas path pore plate, which is mm;
D2the aperture of the shunting hole plate is mm;
D3the equivalent aperture of floating ring medium leakage is mm;
3) d obtained according to step 1)2、P2Determining the point (D)2，P2) Finding an AND point (D) on the type selection graph of the shunt orifice plate obtained in the step 2)2，P2) Setting a longitudinal coordinate value according to the experiment requirement for the closest curve, and finding a horizontal coordinate value corresponding to the longitudinal coordinate set value by using the curve, wherein the horizontal coordinate value is the aperture of the required splitter plate;
4) placing the shunting hole plate (5) with the aperture specification of the shunting hole plate obtained in the step 3) in a floating ring blowing pipeline of the multi-start rocket engine.
2. The method for precisely controlling the blow-off pressure of the floating ring of the multi-start rocket engine according to claim 1, wherein the specific operations of step 1) are as follows:
1.1) configuring a filter, degreasing and cleaning the filter and a nitrogen supply pipeline of a test bed, connecting the cleaned nitrogen supply pipeline of the test bed to an air inlet of an engine, arranging the filter on a butt joint pipeline of the test bed and the engine, and preventing redundant substances from entering the engine when the filter is in butt joint with the test bed;
1.2) introducing nitrogen into an air inlet of the engine to carry out nitrogen blowing, and blowing the pressure P of a gas circuit of a floating ring in a system to be blown2After stabilization, record P2And the aperture D of the flow distribution orifice plate2The numerical value of (c).
3. The method for precisely controlling blow-off pressure of a floating ring of a multi-start rocket engine according to claim 2, wherein: in the step 1.2), setting the pressure P of an air inlet of a blowing total gas path1Is 4 MPa.
4. The method for precisely controlling blow-off pressure of a floating ring of a multi-start rocket engine according to claim 3, wherein: in the step 2), the pressure P of the source of the blowing-off total gas path is set according to the design requirement1Is 4MPa, and the aperture D of the total gas path pore plate is blown off1Is 0.82mm, and a series of equivalent apertures D of floating ring medium leakage are set according to the specification30.6, 0.8, 1.0, 1.2, 1.4, 1.5, 1.6, 1.7, 1.8, 1.9, 2.0, 2.1, 2.2, 2.3, 2.4, 2.5, 2.6, 2.8, 3.0mm, respectively.
5. The method for precisely controlling blow-off pressure of a floating ring of a multi-start rocket engine according to any one of claims 2 to 4, wherein: in the step 1.1), the filtering precision of the filter is not lower than 5 μm.
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| CN113002808A (en) * | 2021-02-07 | 2021-06-22 | 上海宇航系统工程研究所 | Rocket blowing centralized gas supply system |
| CN113188379A (en) * | 2021-05-14 | 2021-07-30 | 北京宇航系统工程研究所 | Low-temperature carrier rocket cabin section environment temperature control gas blowing system |
| CN114856865B (en) * | 2022-05-05 | 2023-08-08 | 西安航天动力研究所 | Method for monitoring test run bellows type end face seal fault of liquid rocket engine |
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| IL159248A (en) * | 2003-12-08 | 2011-10-31 | Aharon Oren | Thruster with electro-thermal thrust augmentation |
| CN202453012U (en) * | 2012-03-14 | 2012-09-26 | 广州飞机维修工程有限公司 | Multi-step dual-pore plate differential pressure fluid flow measurement device |
| CN102620786B (en) * | 2012-03-14 | 2013-07-03 | 广州飞机维修工程有限公司 | Cascade-type double-orifice-plate differential pressure fluid flow measuring device and measuring method thereof |
| CN107543663B (en) * | 2016-09-14 | 2019-09-10 | 北京卫星环境工程研究所 | Aerostatics Helium Leak Test |
| CN110821879B (en) * | 2019-09-30 | 2021-06-11 | 北京航天动力研究所 | Helium flame-retardant sealing structure of turbopump of liquid rocket engine |
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