CN213540587U - Correction device for mass flow of rocket engine gas metering nozzle - Google Patents
Correction device for mass flow of rocket engine gas metering nozzle Download PDFInfo
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- CN213540587U CN213540587U CN202022834690.4U CN202022834690U CN213540587U CN 213540587 U CN213540587 U CN 213540587U CN 202022834690 U CN202022834690 U CN 202022834690U CN 213540587 U CN213540587 U CN 213540587U
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Abstract
The utility model discloses a correcting unit for being directed at rocket engine gas metering nozzle mass flow, include: the temperature compensation piece is used for enabling the metering valve core to move upwards or downwards through deformation so as to adjust the intersection area of the outer gas outlet corresponding to the inner gas outlet, and the reset spring is positioned in the valve core channel and below the metering valve core and used for providing supporting force for the metering valve core; the utility model discloses according to the medium temperature, compensate and rectify output gas volume flow, greatly reduced gas supply system's mass flow change.
Description
Technical Field
The utility model belongs to rocket engine gas medium measures the regulation field, especially relates to a correcting unit for being directed at rocket engine gas measurement nozzle mass flow.
Background
The gas supply and regulation system of the rocket engine is a system for providing various gases for the operation of the engine through a storage tank valve combination, an electromagnetic valve, a pipeline and the like. The gas supply and regulation system mainly comprises a pump valve regulation scheme and a gas bottle decompression scheme, wherein the pump valve regulation scheme has large flow, good regulation performance but complex system and heavy weight, and is generally used for engines with complex working conditions; the gas cylinder decompression scheme reduces the high gas pressure of the gas cylinder into the gas with the pressure required by the engine to provide oxygen for the engine to work.
No matter what kind of gas is supplied, high-pressure gas is converted into low-pressure gas through a pressure reducer after a high-pressure gas cylinder, and elements such as a buffer, a sonic nozzle and the like are added according to different system requirements. The typical gas supply system comprises a controller, a gas cylinder, an electromagnetic stop valve, a pressure reducing valve, a pressure sensor before measurement, a sonic nozzle, a temperature sensor after measurement and a connector leading to a combustion chamber, wherein gas flows out of the gas cylinder, the electromagnetic stop valve controls whether the gas is led to a subsequent component or not, if the electromagnetic stop valve is opened, the gas outputs stable pressure after passing through the pressure reducing valve and then leads to the combustion chamber after passing through the sonic nozzle, and the pressure sensors are arranged in front of and behind the sonic nozzle.
The volume flow of the gas is only related to the pressure in front of the nozzle and the throat area due to the characteristics of the sonic nozzle, and when the pressure in front of the nozzle is constant, the volume flow of the gas is also constant. However, although the gas supply path, especially the oxidant supply path and the sonic nozzle can ensure stable volume flow, the temperature of the gas path including the gas cylinder outlet, the front and the back of the pressure reducing valve and the whole gas path is changed, and according to the gas characteristics, under the working environmental condition of the gas supply system, the density of the gas is greatly influenced by the temperature, so that the mass flow is greatly changed, and the performance of the engine is greatly influenced.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a correcting unit for being directed at rocket engine gas metering nozzle mass flow to solve the gas mass flow that current gas supply system supplied with and cause the great problem of error because of temperature variation.
The utility model adopts the following technical scheme: a calibration device for metering nozzle mass flow to rocket engine gas, comprising:
a casing, which is vertically arranged, a valve core channel is vertically arranged in the casing, an outer air inlet is arranged on the side wall of the lower end of the casing, an outer air outlet is arranged on the side wall of the upper end of the casing, the valve core channel is communicated with a pressure reducing valve behind the gas supply device through the outer air inlet, the valve core channel is communicated with a rocket engine thrust chamber through the outer air outlet,
the metering valve core is vertically arranged and positioned in the middle of the valve core channel, an airflow channel is vertically arranged in the metering valve core, an inner air inlet is arranged on the outer wall of the lower end of the metering valve core, an inner air outlet is arranged on the outer wall of the upper end of the metering valve core, the inner air inlet and the outer air inlet are oppositely arranged, the inner air outlet and the outer air outlet are oppositely arranged so that air can enter from the outer air inlet and the inner air inlet in sequence and flow to a rocket engine thrust chamber from the inner air outlet and the outer,
the temperature compensation sheet is positioned in the valve core channel and above the metering valve core, the lower end of the temperature compensation sheet is abutted against the upper end of the metering valve core and is used for enabling the metering valve core to move upwards or downwards through deformation so as to adjust the intersection area of the outer air outlet corresponding to the inner air outlet,
and the return spring is positioned in the valve core channel and below the metering valve core, and the upper end of the return spring is propped against the lower side of the metering valve core and is used for providing supporting force for the metering valve core.
Furthermore, the inner end edge of the outer air outlet is vertically expanded to form a funnel shape, the cross-sectional area of the outer air outlet is increased, and then the adjusting range of the intersection area of the outer air outlet and the inner air outlet is increased.
Furthermore, the inner end edge of the outer air inlet is vertically expanded to form a funnel shape, the cross section area of the outer air inlet is increased, and then the adjusting range of the outer air inlet for adjusting the intersection area of the outer air inlet and the inner air inlet is enlarged.
Furthermore, the top of the upper end of the air flow channel is fixedly connected with a valve cover, and the temperature compensation sheet is positioned below the valve cover.
Further, the outer air outlet is positioned above the return spring.
The utility model has the advantages that: the utility model compensates and corrects the volume flow of the output gas according to the medium temperature, greatly reduces the mass flow change of the gas supply system, improves the combustion efficiency of the engine, and simultaneously improves the performance, the economy and the reliability of the engine; the gas mass flow is compensated through a mechanical principle, so that the complexity of the system is reduced, the control calculation difficulty is simplified, and the metering precision is improved; can output gas with stable mass flow.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Wherein: 1. a housing; 2. a return spring; 3. an outer air inlet; 4. an inner air inlet; 5. an outer air outlet; 6. an inner air outlet; 7. a temperature compensation sheet; 8. a valve cover; 9. a metering valve core; 10. an air flow channel.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
The utility model discloses a correcting unit for being directed at rocket engine gas measurement nozzle mass flow, as shown in fig. 1, including casing 1, measurement case 9, temperature compensation piece 7, reset spring 2, casing 1 is the column, the vertical setting of casing 1, the vertical case passageway of having seted up in the casing 1, outer air inlet 3 has been seted up to casing 1 lower extreme lateral wall, has seted up out gas port 5 on the casing 1 upper end lateral wall, and the case passageway communicates through the relief pressure valve behind outer air inlet 3 and the gas supply device, and the case passageway communicates through going out gas port 5 and rocket engine thrust chamber.
The vertical setting of measurement case 9, measurement case 9 is the column, and measurement case 9 is located the middle part of case passageway, and air flow channel 10 has vertically been seted up in measurement case 9, and air flow channel 10's upper end top fixedly connected with valve gap 8, temperature-compensated piece 7 are located valve gap 8 downside. An inner air inlet 4 is formed in the outer wall of the lower end of the metering valve core 9, an inner air outlet 6 is formed in the outer wall of the upper end of the metering valve core 9, the inner air inlet 4 is arranged opposite to the outer air inlet 3, and the inner air outlet 6 is arranged opposite to the outer air outlet 5, so that air enters from the outer air inlet 3 and the inner air inlet 4 in sequence and flows to a rocket engine thrust chamber from the inner air outlet 6 and the outer air outlet 5 after passing through the airflow channel 10.
The inner end edge of the outer air outlet 5 is vertically expanded to form a funnel shape, so that the cross section area of the outer air outlet 5 is increased, and the adjusting range of the outer air outlet 5 for adjusting the intersection area of the outer air outlet 5 and the inner air outlet 6 is further increased; the inner end edge of the outer air inlet 3 is vertically expanded to form a funnel shape, the cross section area of the outer air inlet 3 is increased, and then the adjusting range of the intersection area of the outer air inlet 3 and the inner air inlet 4 is enlarged, wherein the intersection area of the outer air inlet 3 and the inner air inlet 4 is adjusted.
Temperature-compensated piece 7 is located the case passageway and measures the top of case 9, 7 lower extremes of temperature-compensated piece support the upper end at measurement case 9, temperature-compensated piece 7 is used for making measurement case 9 upwards or downstream through deformation, and then adjusts the crossing area that goes out gas port 5 and correspond interior gas outlet 6, reset spring 2 is located the case passageway and measures case 9 downside, 2 upper ends of reset spring support the downside at measurement case 9, reset spring 2 is used for providing holding power for measurement case 9, it is located reset spring 2 top to go out gas port 5.
The utility model discloses install after rocket engine's gas supply device, because gas supply device generally is not used for exporting the gas of stabilizing mass flow, only need keep system outlet pressure invariable can, and the utility model discloses then can export the gas of stabilizing mass flow, compensate this shortcoming of gas supply device.
The temperature compensation sheet 7 is positioned in the valve core channel and above the metering valve core 9, the lower end of the metering valve core 9 is provided with a return spring 2, and the three components are jointly installed in the shell 1 and fixed by a valve cover 8. The gas flow of flowing through measurement case 9 is relevant with the area of measurement case 9 and front and back pressure differential, and when current back pressure differential is fixed, only relevant with the area, process the utility model discloses a gas flow is relevant with throttle area and front and back pressure. In a steady state at normal temperature, the pressure difference between the outer inlet 3 and the outer outlet 5 is considered to be constant, and the intersection area of the outer outlet 5 with the inner outlet 6, i.e., the throttle area, is considered to be constant, so that the flow rate is constant.
When the gas temperature changes, the thickness of the temperature compensation sheet 7 changes due to physical characteristics, so that the metering valve core 9 is pushed to change the throttle area, and the volume flow rate of the gas to the combustion chamber changes due to the fact that the pressure difference between the outer gas inlet 3 and the outer gas outlet 5 can be considered to be constant, so that the function of correcting the mass flow rate of the gas is achieved.
The temperature compensation plate 7 can be a single temperature compensation plate 7 or formed by combining temperature compensation plates 7 with different numbers in parallel and series; the temperature compensation sheet 7 can be a corrugated pipe with temperature sensitivity, and when the gas density change range is small, the corrugated pipe can be selected to increase the metering precision; the temperature compensation plates 7 can be corrugated pipes with temperature sensitivity and different numbers of temperature compensation plates 7 which are connected in parallel and in series. The gas medium can be oxygen, hydrogen and other common gases, and when the types of the gases are different, the structural size change of the temperature compensation sheet 7 is positively or negatively correlated with the gas temperature change according to the gas characteristics.
If the gas supply device is provided with a plurality of metering spray pipes which are connected in parallel, a stop valve can be arranged in front of each metering spray pipe, the controller receives state information of the metering device and expected index information of a controlled object, and a stop valve control signal is calculated through a preset algorithm; the metering flow is adjusted by controlling the on-off of each stop valve.
The above description is only for the preferred embodiment of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (5)
1. A calibration device for metering nozzle mass flow to rocket engine gases, comprising:
the shell (1) is vertically arranged, a valve core channel is vertically arranged in the shell, an outer air inlet (3) is arranged on the side wall of the lower end of the shell, an outer air outlet (5) is arranged on the side wall of the upper end of the shell, the valve core channel is communicated with a pressure reducing valve behind the gas supply device through the outer air inlet (3), the valve core channel is communicated with a thrust chamber of the rocket engine through the outer air outlet (5),
the metering valve core (9) is vertically arranged and positioned in the middle of the valve core channel, an airflow channel (10) is vertically arranged in the metering valve core, an inner air inlet (4) is arranged on the outer wall of the lower end of the metering valve core, an inner air outlet (6) is arranged on the outer wall of the upper end of the metering valve core, the inner air inlet (4) is opposite to the outer air inlet (3), the inner air outlet (6) is opposite to the outer air outlet (5), so that gas can enter from the outer air inlet (3) and the inner air inlet (4) in sequence and flows to a rocket engine thrust chamber from the inner air outlet (6) and the outer air outlet (5) after,
the temperature compensation sheet (7) is positioned in the valve core channel and above the metering valve core (9), the lower end of the temperature compensation sheet is abutted against the upper end of the metering valve core (9) and is used for enabling the metering valve core (9) to move upwards or downwards through deformation so as to adjust the intersection area of the outer air outlet (5) corresponding to the inner air outlet (6),
and the return spring (2) is positioned in the valve core channel and below the metering valve core (9), and the upper end of the return spring is abutted against the lower side of the metering valve core (9) and is used for providing supporting force for the metering valve core (9).
2. A correction device for rocket engine gas metering nozzle mass flow according to claim 1, characterized in that the inner end edge of the outer gas port (5) is expanded vertically to form a funnel shape, increasing the cross-sectional area of the outer gas port (5), and further increasing the adjusting range of the outer gas port (5) for adjusting the intersection area of the outer gas port (5) and the inner gas outlet (6).
3. A device for correcting the mass flow of a rocket engine gas metering nozzle according to claim 2, characterized in that the inner end edge of the outer air inlet (3) is vertically expanded to form a funnel shape, the cross-sectional area of the outer air inlet (3) is increased, and the adjusting range of the outer air inlet (3) for adjusting the intersection area of the outer air inlet (3) and the inner air inlet (4) is further increased.
4. A device for calibrating the mass flow of a rocket engine gas metering nozzle according to any one of claims 1-3, wherein a valve cover (8) is fixedly connected to the top of the upper end of the gas flow channel (10), and the temperature compensation plate (7) is positioned below the valve cover (8).
5. A correction device for metering nozzle mass flow for rocket engine gases according to claim 4, characterized in that the outer air outlet (5) is located above the return spring (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022834690.4U CN213540587U (en) | 2020-12-01 | 2020-12-01 | Correction device for mass flow of rocket engine gas metering nozzle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202022834690.4U CN213540587U (en) | 2020-12-01 | 2020-12-01 | Correction device for mass flow of rocket engine gas metering nozzle |
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| CN213540587U true CN213540587U (en) | 2021-06-25 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114810428A (en) * | 2022-03-30 | 2022-07-29 | 北京航天动力研究所 | Precooling device and method for engine hydrogen system under simulation verification flight state |
| CN114810428B (en) * | 2022-03-30 | 2024-05-31 | 北京航天动力研究所 | Precooling device and method for simulating and verifying engine hydrogen system under flight state |
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2020
- 2020-12-01 CN CN202022834690.4U patent/CN213540587U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114810428A (en) * | 2022-03-30 | 2022-07-29 | 北京航天动力研究所 | Precooling device and method for engine hydrogen system under simulation verification flight state |
| CN114810428B (en) * | 2022-03-30 | 2024-05-31 | 北京航天动力研究所 | Precooling device and method for simulating and verifying engine hydrogen system under flight state |
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