CN117759456A - Rocket engine blow-off gas supply device for restraining vibration and design method thereof - Google Patents
Rocket engine blow-off gas supply device for restraining vibration and design method thereof Download PDFInfo
- Publication number
- CN117759456A CN117759456A CN202311747187.7A CN202311747187A CN117759456A CN 117759456 A CN117759456 A CN 117759456A CN 202311747187 A CN202311747187 A CN 202311747187A CN 117759456 A CN117759456 A CN 117759456A
- Authority
- CN
- China
- Prior art keywords
- gas supply
- pressure
- throttling element
- gas
- supply device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000000452 restraining effect Effects 0.000 title claims abstract description 6
- 230000010355 oscillation Effects 0.000 claims abstract description 25
- 238000007664 blowing Methods 0.000 claims abstract description 22
- 239000007789 gas Substances 0.000 claims description 78
- 238000010926 purge Methods 0.000 claims description 14
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 10
- 238000012360 testing method Methods 0.000 claims description 6
- 229910052757 nitrogen Inorganic materials 0.000 claims description 5
- 230000035939 shock Effects 0.000 claims description 3
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 230000002401 inhibitory effect Effects 0.000 abstract description 8
- 239000003350 kerosene Substances 0.000 description 11
- 239000000446 fuel Substances 0.000 description 9
- 238000007872 degassing Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 3
- 230000010349 pulsation Effects 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000004939 coking Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000009514 concussion Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
Landscapes
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
Abstract
The invention relates to a gas supply device, which aims to solve the problem that the supply of the blowing gas in a head cavity of an engine is fluctuated to bring safety risks to the engine due to the fact that low-frequency and high-amplitude oscillation is generated by blowing gas in a pipeline when high-flow and high-pressure blowing gas is conveyed in the prior art, and provides a rocket engine blowing gas supply device for restraining the oscillation and a design method thereof. The invention provides a rocket engine blowing-off gas supply device for inhibiting oscillation, which comprises a gas source, an engine gas supply cavity, a gas supply pipeline and a flow control assembly arranged on the gas supply pipeline, wherein the gas source is connected with the engine gas supply cavity; the flow control assembly comprises a mass flowmeter, a filter, a first throttling element, a high-pressure hand valve, a high-pressure electromagnetic valve and a second throttling element from the near to the far from the air source; the first throttling piece and the second throttling piece are flange covers; pressure sensors and temperature sensors are arranged between the filter and the first throttling element and between the high-pressure electromagnetic valve and the second throttling element.
Description
Technical Field
The invention relates to a gas supply device and a design method, in particular to a rocket engine blow-off gas supply device for inhibiting oscillation and a design method thereof.
Background
According to the working principle of the existing liquid oxygen kerosene engine, the liquid oxygen kerosene engine needs to be supplied with blowing and degassing with certain pressure and flow by a test bed in the working process. The functions of the blowing gas mainly comprise: 1) Preventing moist air from condensing inside the engine; 2) Blowing off a fuel path of the thrust chamber to prevent channeling; 3) The fuel path of the generator blows off the emulsifiable kerosene, so as to improve the pressure drop of the nozzle; 4) When the engine is shut down, the generator blows off the fuel gas which can be rapidly discharged, so that the engine is rapidly and stably shut down; 5) When the engine is shut down, the fuel inlet blows off to ensure that the residual kerosene of the thrust chamber is in a flowing state, and the kerosene is prevented from coking in a cooling channel of the thrust chamber. The purge gas may be helium or nitrogen, and may be classified into strong purge and weak purge according to the magnitude of the gas source pressure.
In the starting process of the engine, the high-pressure blowing gas can emulsify the low-flow kerosene, so that the atomization effect of the kerosene is improved, and the combustion efficiency is improved. FIG. 1 is a schematic view of a rocket engine generator fuel cavity blow-down. During engine starting, a small amount of kerosene flows out of the fuel chamber 101 under the action of the purge gas (nitrogen) and enters the generator through the fuel nozzle 102 to burn, and a part of kerosene fills the head chamber. As the generator pressure increases, the purge gas flow gradually becomes smaller, and the kerosene filling is finally completed. The stable supply of high-pressure blow-out gas thus plays an important role in the stable start-up of the engine. The gas pipeline behind the electromagnetic valve forms a cavity with a certain volume, when the control valve is opened, high-flow supersonic blowing and degassing is filled in the cavity, but supersonic compression shock waves are formed in the cavity at the same time, so that the blowing and degassing forms low-frequency high-amplitude oscillation, the supply of the blowing and degassing in the engine head cavity fluctuates, and finally the safety risk is brought to the engine.
Disclosure of Invention
The invention aims to solve the problem that the supply of the blowing gas in the engine head cavity fluctuates and causes the safety risk to the engine due to the fact that the blowing gas in a pipeline generates low-frequency and high-amplitude oscillation when the blowing gas with high flow and high pressure is conveyed in the prior art, and provides a rocket engine blowing gas supply device for inhibiting the oscillation and a design method thereof.
In order to achieve the above purpose, the technical solution provided by the present invention is:
the utility model provides a rocket engine blow-off gas supply device that restraines concussion which characterized in that:
the device comprises an air source, an engine air supply cavity, an air supply pipeline for connecting an air source output end with the engine air supply cavity, and a flow control assembly arranged on the air supply pipeline; the flow control assembly comprises a mass flowmeter, a filter, a first throttling element, a high-pressure hand valve, a high-pressure electromagnetic valve and a second throttling element from the near to the far from the air source in sequence; the first throttling piece and the second throttling piece are flange covers with a plurality of through holes for gas to pass through; pressure sensors and temperature sensors are arranged between the filter and the first throttling element and between the high-pressure electromagnetic valve and the second throttling element; the inner diameter of the through hole of the second throttling element is smaller than that of the first throttling element.
The mass flowmeter is used for measuring the supply flow rate of the gas; the filter is used for removing impurities in the gas.
Further, the gas source is a gas storage tank with the volume of 20m 3 。
Further, the filter has a plurality of micropores, the nominal diameter DN of the filter is 32mm, the nominal pressure PN of the filter is 350MPa, and the diameter of each micropore in the filter is 5 mu m.
Further, the outer diameter of the gas supply pipeline is 48mm, the wall thickness is 8mm, the strength of the pipeline is high, and the pipeline can be prevented from being damaged by vibration generated during test run of the liquid oxygen kerosene engine.
Meanwhile, the invention also provides a design method of the oscillation-inhibiting rocket engine blowing gas supply device, which is characterized by comprising the following steps:
step 1, installing a rocket engine blow-off gas supply device for restraining oscillation;
step 2, filling blowing gas with preset pressure into the air source;
step 3, sequentially opening a high-pressure hand valve and a high-pressure electromagnetic valve to supply the blow-off gas to the gas supply cavity of the engine;
step 4, adjusting and determining the inner diameter size and flow coefficient of the through hole of the first throttling element and the second throttling element according to the mass flow data acquired by the mass flowmeter, the pressure data acquired by the two pressure sensors and the temperature data acquired by the two temperature sensors;
step 5, testing the maximum values of the filling time, the pressure stabilizing time and the pressure fluctuation of the gas supply pipeline, drawing a curve, and if the preset target is reached, completing the design of a blowing gas supply device for the rocket engine; if the preset target is not reached, returning to the step 4, and redefining the inner diameter sizes and the flow coefficients of the through holes of the first throttling element and the second throttling element until the preset target is reached.
Further, the pressure of the charging purge gas in step 1 was 23MPa.
Further, the purge gas in step 2 is nitrogen.
Compared with the prior art, the invention has the beneficial effects that:
1. the rocket engine blow-off gas supply device for inhibiting the oscillation is provided with the first throttling piece and the second throttling piece, and can inhibit the pressure oscillation in the pipeline filling process and prolong the filling time of the closed pipeline by adjusting the size of the first throttling piece;
2. the oscillation-inhibiting rocket engine blowing-off gas supply device provided by the invention adopts the high-pressure-resistant and large-volume gas storage tank, and adopts the gas supply pipeline to directly supply blowing-off gas, so that the stability of the gas flow is ensured;
3. the rocket engine blow-off gas supply device for inhibiting oscillation has the advantages of simple principle and good process reliability.
Drawings
FIG. 1 is a schematic view of a rocket engine generator fuel cavity blow-down;
FIG. 2 is a schematic structural diagram of an embodiment of a purging gas supply device for a rocket engine for suppressing oscillation provided by the invention;
FIG. 3 is a graph comparing a pressure surge curve of an embodiment of the present invention with a prior art surge pressure surge curve;
reference numerals illustrate:
1-an air source; 2-a gas supply line; 3-an engine air supply cavity; 4-a mass flowmeter; 5-a filter; 61-a first restriction, 62-a second restriction; 71-high pressure hand valve, 72-high pressure solenoid valve; 81-a pressure sensor, 82-a temperature sensor; 101-fuel chamber, 102-fuel nozzle.
Detailed Description
The invention will be further described with reference to the drawings and specific examples.
The rocket engine blow-off gas supply device for inhibiting oscillation comprises a gas source 1, an engine gas supply cavity 3, a gas supply pipeline 2 for connecting the output end of the gas source 1 with the engine gas supply cavity 3 and a flow control assembly arranged on the gas supply pipeline 2, wherein the gas supply pipeline 2 is provided with a plurality of air supply channels; the flow control assembly comprises a mass flowmeter 4, a filter 5, a first throttling element 61, a high-pressure hand valve 71, a high-pressure electromagnetic valve 72 and a second throttling element 62 from the near to the far from the air source 1; the first throttle 61 and the second throttle 62 are flange covers with a plurality of through holes for gas to pass through; a pressure sensor 81 and a temperature sensor 82 are provided between the filter 5 and the first throttle 61, and between the high-pressure solenoid valve 72 and the second throttle 62; the through-hole inner diameter dimension of the second throttle 62 is smaller than the through-hole inner diameter dimension of the first throttle 61.
Wherein the gas source 1 is a gas storage tank with the volume of 20m 3 The working pressure is 35MPa. The filter 5 has a plurality of micropores, the nominal diameter DN of the filter 5 is 32mm, the nominal pressure PN of the filter 5 is 350MPa, and each micropore in the filter 5 is straightThe diameters were 5. Mu.m. The gas supply line had a specification of Φ48mm×8mm.
Meanwhile, the embodiment also provides a design method of the rocket engine blow-off gas supply device for suppressing oscillation, which comprises the following steps:
step 1, installing a rocket engine blow-off gas supply device for restraining oscillation;
step 2, filling 23MPa of nitrogen into the air source 1 as blowing gas;
step 3, sequentially opening the high-pressure hand valve 71 and the high-pressure electromagnetic valve 72 to supply the blow-off gas to the engine gas supply cavity 3;
step 4, adjusting and determining the inner diameter sizes and flow coefficients of the through holes of the first throttling element 61 and the second throttling element 62 according to the mass flow data acquired by the mass flowmeter 4, the pressure data acquired by the two pressure sensors 81 and the temperature data acquired by the two temperature sensors 82;
step 5, testing the maximum values of the filling time, the pressure stabilizing time and the pressure fluctuation of the gas supply pipeline 2, drawing a curve, and if the preset target is reached, completing the design of a blowing gas supply device for the rocket engine; if the preset target is not reached, the process returns to step 4, and the through hole inside diameter dimensions and flow coefficients of the first and second throttle members 61 and 62 are redetermined until the preset target is reached.
In the present embodiment, the through-hole inner diameter dimension of the first throttle 61 is finally determined to be Φ8.5mm.
Fig. 3 is a graph showing the comparison of pressure pulsation in a blow-off test without a throttle (prior art) and with a throttle (invention), wherein curve (a) is a prior art pressure pulsation curve and curve (b) is a pressure pulsation curve of the invention, and the following data can be seen from the graph:
TABLE 1
As can be seen from table 1 and fig. 3, the maximum value of the improved fluctuation is reduced, and compared with the prior art, the throttle member can obviously inhibit the oscillation, and the throttle member can inhibit the compression wave from forming periodical oscillation amplitude and frequency in the blind cavity pipeline.
It should be noted that the above is only a specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any equivalent modifications or substitutions can be easily made by those skilled in the art within the technical scope of the present invention, and these modifications or substitutions should be covered in the scope of the present invention.
Claims (7)
1. The utility model provides a inhibit rocket engine blow off gas supply device of shock which characterized in that:
the device comprises an air source (1), an engine air supply cavity (3), an air supply pipeline (2) for connecting the output end of the air source (1) with the engine air supply cavity (3) and a flow control assembly arranged on the air supply pipeline (2);
the flow control assembly comprises a mass flowmeter (4), a filter (5), a first throttling element (61), a high-pressure hand valve (71), a high-pressure electromagnetic valve (72) and a second throttling element (62) from the near to the far from the air source (1);
the first throttling element (61) and the second throttling element (62) are flange covers with a plurality of through holes for gas to pass through;
a pressure sensor (81) and a temperature sensor (82) are arranged between the filter (5) and the first throttling element (61) and between the high-pressure electromagnetic valve (72) and the second throttling element (62);
the through hole inner diameter of the second throttling element (62) is smaller than that of the first throttling element (61).
2. A rocket engine purge gas supply device for suppressing oscillations according to claim 1, wherein:
the gas source (1) is a gas storage tank with the volume of 20m 3 。
3. A rocket engine purge gas supply device for suppressing oscillations according to claim 2, wherein:
the filter (5) is provided with a plurality of micropores, the nominal diameter DN of the filter (5) is 32mm, the nominal pressure PN of the filter (5) is 350MPa, and the diameter of each micropore in the filter (5) is 5 mu m.
4. A rocket engine purge gas supply device for suppressing oscillations according to claim 3, wherein:
the outer diameter of the gas supply pipeline (2) is 48mm, and the wall thickness is 8mm.
5. A method of designing a shock suppressing rocket engine purge gas supply apparatus as recited in any one of claims 1 to 4, comprising the steps of:
step 1, installing a rocket engine blow-off gas supply device for restraining oscillation;
step 2, filling blowing gas with preset pressure in the air source (1);
step 3, sequentially opening a high-pressure hand valve (71) and a high-pressure electromagnetic valve (72) to supply the blow-off gas to the engine gas supply cavity (3);
step 4, according to the mass flow data acquired by the mass flowmeter (4), the pressure data acquired by the two pressure sensors (81) and the temperature data acquired by the two temperature sensors (82), the inner diameter sizes and the flow coefficients of the through holes of the first throttling element (61) and the second throttling element (62) are adjusted and determined;
step 5, testing the filling time, the pressure stabilizing time and the maximum value of pressure fluctuation of the gas supply pipeline (2) and drawing a curve, if a preset target is reached, completing the design of a blowing gas supply device for a rocket engine; if the preset target is not reached, returning to the step 4, and redefining the inner diameter sizes and the flow coefficients of the through holes of the first throttling element (61) and the second throttling element (62) until the preset target is reached.
6. The method for designing a blow-off gas supply device for a rocket engine for suppressing oscillations according to claim 5, wherein:
the pressure of the charged purge gas in step 2 was 23MPa.
7. The method for designing a blow-off gas supply device for a rocket engine for suppressing oscillations according to claim 6, wherein:
the purge gas in step 2 is nitrogen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311747187.7A CN117759456A (en) | 2023-12-18 | 2023-12-18 | Rocket engine blow-off gas supply device for restraining vibration and design method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311747187.7A CN117759456A (en) | 2023-12-18 | 2023-12-18 | Rocket engine blow-off gas supply device for restraining vibration and design method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117759456A true CN117759456A (en) | 2024-03-26 |
Family
ID=90311643
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311747187.7A Pending CN117759456A (en) | 2023-12-18 | 2023-12-18 | Rocket engine blow-off gas supply device for restraining vibration and design method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117759456A (en) |
-
2023
- 2023-12-18 CN CN202311747187.7A patent/CN117759456A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP4597505B2 (en) | Acoustic impedance matching fuel nozzle device and tunable fuel injection resonator assembly | |
| WO2007112442A2 (en) | Valveless pulsed detonation combustor | |
| JP2014517893A (en) | Supply system and method for suppressing pogo effect | |
| CN104329187A (en) | Variable working condition type primary rocket system of rocket based combined cycle engine | |
| CN111810319A (en) | Rocket engine low-frequency pulsation suppression device containing gas-liquid separation and discharge system | |
| JP2012140958A5 (en) | ||
| CN117759456A (en) | Rocket engine blow-off gas supply device for restraining vibration and design method thereof | |
| CN107023393A (en) | Pressure decay apparatus for fuel manifold | |
| CN111655992A (en) | Fuel supply device and gas turbine | |
| CN111766091B (en) | Calibration system and method of low-frequency pulsation suppression device for ground test | |
| CN117006111B (en) | Gas injection type pressure accumulator, POGO vibration suppression system and POGO vibration suppression method | |
| CN113175394B (en) | Hydrogen-oxygen rocket engine dynamic combustion stability identification test system and method | |
| CN112595491B (en) | Cavitation pipe liquid flow test method | |
| CN206175928U (en) | Pipeline depressurization device | |
| WO2014022831A1 (en) | Downhole gas generator with multiple combustion chambers and method of operation | |
| RU2014110031A (en) | COMBUSTION SYSTEM AND TURBINE CONTAINING A DUMPING DEVICE | |
| CN116025488B (en) | Engine working condition adjustment test device and adjustment method | |
| CN115628153B (en) | Engine boost control method and device, computer equipment and storage medium | |
| Qin et al. | Experimental study on vibration and noise of throttle valve in water-conveying systems | |
| JPH0719759A (en) | Pressure control device | |
| CN116150922B (en) | Design method of energy storage pipeline system | |
| CN117703635A (en) | Graded starting heat test system and method for liquid rocket engine | |
| CN113431706B (en) | Venturi tube combination device and system for liquid engine and operation method of venturi tube combination device | |
| CN115824657A (en) | Engine post-test treatment test tool, simulation system and simulation method | |
| CN117490987A (en) | Air pressure and current stabilizing device for testing flow of gas nozzle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |