CN113074065B - Power system for comprehensive research of heat transfer multiphase flow noise - Google Patents
Power system for comprehensive research of heat transfer multiphase flow noise Download PDFInfo
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- CN113074065B CN113074065B CN202110368227.1A CN202110368227A CN113074065B CN 113074065 B CN113074065 B CN 113074065B CN 202110368227 A CN202110368227 A CN 202110368227A CN 113074065 B CN113074065 B CN 113074065B
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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
- F02K9/96—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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- 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
- F02K9/62—Combustion or thrust chambers
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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
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
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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
- F02K9/97—Rocket nozzles
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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
- F02K9/97—Rocket nozzles
- F02K9/972—Fluid cooling arrangements for nozzles
Abstract
The invention relates to a power system for comprehensively researching heat transfer multiphase flow noise, which comprises a rocket engine and a temperature control device, wherein the rocket engine comprises a combustion chamber and an engine spray pipe arranged at the right end of the combustion chamber, the combustion chamber is connected with a fuel source and a combustion assisting gas source through pipelines, the engine spray pipe is a Laval type spray pipe, the temperature control device comprises a temperature control cylinder and a temperature control spray pipe arranged at the right end of the temperature control cylinder, the left end of the temperature control cylinder is hermetically connected with the combustion chamber, the engine spray pipe is arranged in an inner cavity of the temperature control cylinder, the temperature control cylinder is connected with a temperature control gas source through a pipeline, and the temperature control spray pipe is a Laval type spray pipe. The device has the advantages of simple structure, convenience in regulation and control, strong functionality, high accuracy and wide application range.
Description
Technical Field
The invention relates to an experimental device, in particular to a power system for comprehensively researching heat transfer characteristics, multiphase flow characteristics and noise characteristics of a gas flow.
Background
In the field of aerospace, high-temperature and high-speed gas flow generated by rocket launching can generate strong ablation effect on a launching system and a rocket body on one hand, and can generate strong noise (the sound pressure level is usually more than 160dB) on the other hand, the strong noise can change the propagation direction under the disturbance of a complex structure of the launching system, and can damage electrical components of a launching instrument, thereby affecting the safety. For ablation damage of gas flow, two countermeasures are mainly adopted in the field at present, namely, the ablation resistance of a launching system and an rocket body is enhanced, such as coating a thermal protection coating, adopting a composite material skin structure and the like, and water or other cooling media are sprayed; for the noise impairment of gas flows, the prior art mainly adopts the counter measures of spray water or other cooling media. In order to accurately judge the ablation prevention and noise reduction effects, the heat transfer, distribution and change characteristics of the gas flow and the multiphase flow and the generation mechanism and the transmission characteristics of noise need to be researched, under the condition that the current theory cannot obtain an accurate result, the research developed by using a test is a unique feasible mode, the test research needs to determine the inflow conditions (temperature, pressure and flow rate) of the gas flow or the multiphase flow, and at present, no technology or equipment capable of accurately controlling the inflow conditions of the gas flow or the multiphase flow exists in the field.
Disclosure of Invention
The invention aims to provide a power system for comprehensively researching heat transfer multiphase flow noise, which has the advantages of simple structure, convenience in regulation and control, strong functionality, high accuracy and wide application range.
In order to solve the problems in the prior art, the power system for comprehensively researching heat transfer multiphase flow noise comprises a rocket engine and a temperature control device, wherein the rocket engine comprises a combustion chamber and an engine spray pipe arranged at the right end of the combustion chamber, the combustion chamber is connected with a fuel source and a combustion assisting gas source through pipelines, the engine spray pipe is a Laval type spray pipe, the temperature control device comprises a temperature control cylinder and the temperature control spray pipe arranged at the right end of the temperature control cylinder, the left end of the temperature control cylinder is hermetically connected with the combustion chamber, the engine spray pipe is arranged in an inner cavity of the temperature control cylinder, the temperature control cylinder is connected with a temperature control gas source through a pipeline, and the temperature control spray pipe is a Laval type spray pipe.
Furthermore, the invention relates to a power system for comprehensive research on heat transfer multiphase flow noise, wherein a spray cover is arranged at an outlet of the temperature control spray pipe, and the spray cover is connected with a spray medium source through a pipeline.
Furthermore, the invention relates to a power system for comprehensive research of heat transfer multiphase flow noise, wherein the fuel source is a fuel storage tank, the fuel storage tank is sequentially connected with a first extrusion gas tank and a first extrusion gas source through a pipeline, and a first pressure reducing valve is arranged on the pipeline between the first extrusion gas tank and the fuel storage tank.
Further, the power system for comprehensively researching heat transfer multiphase flow noise is characterized in that the spraying medium source is a spraying medium storage tank, the spraying medium storage tank is sequentially connected with a second extrusion gas tank and a second extrusion gas source through a pipeline, and a second pressure reducing valve is arranged on the pipeline between the second extrusion gas tank and the spraying medium storage tank.
Furthermore, the invention relates to a power system for comprehensive research of heat transfer multiphase flow noise, wherein a combustion-supporting gas storage tank is arranged on a pipeline between a combustion-supporting gas source and a combustion chamber, and a third pressure reducing valve is arranged on a pipeline between the combustion-supporting gas storage tank and the combustion chamber.
Furthermore, the invention relates to a power system for comprehensive research of heat transfer multiphase flow noise, wherein a temperature control air storage tank is arranged on a pipeline between the temperature control air source and the temperature control cylinder, and a fourth pressure reducing valve is arranged on a pipeline between the temperature control air storage tank and the temperature control cylinder.
Furthermore, the power system for comprehensively researching heat transfer multiphase flow noise is characterized in that a spraying cavity is arranged in the peripheral wall of the spraying cover, a plurality of nozzles communicated with the spraying cavity are arranged on the inner wall of the spraying cover, and the spraying medium source is communicated with the spraying cavity through a pipeline.
Furthermore, the invention relates to a power system for comprehensively researching heat transfer multiphase flow noise, wherein the temperature control cylinder and the temperature control spray pipe are integrally manufactured; the left end of the spraying cover is connected with the temperature control device through the switching frame capable of moving left and right, and the right half part of the inner cavity of the spraying cover is in a round table shape with a small left and a large right.
Furthermore, the invention relates to a power system for comprehensive research on heat transfer multiphase flow noise, wherein the spraying medium source is also connected with a spraying medium liquid supplementing device through a pipeline.
Furthermore, the invention relates to a power system for comprehensive research on heat transfer multiphase flow noise, wherein stop valves are respectively arranged on a pipeline between the first pressure reducing valve and the fuel source, a pipeline between the fuel source and the rocket engine, a pipeline between the second pressure reducing valve and the spraying medium source, a pipeline between the spraying medium source and the spraying cover, a pipeline between the third pressure reducing valve and the rocket engine, a pipeline between the fourth pressure reducing valve and the temperature control cylinder, and a pipeline between the spraying medium liquid supplementing device and the spraying medium source.
Compared with the prior art, the power system for comprehensively researching heat transfer multiphase flow noise has the following advantages: the rocket engine comprises a combustion chamber and an engine spray pipe arranged at the right end of the combustion chamber, the combustion chamber is connected with a fuel source and a combustion-supporting gas source through a pipeline, the engine spray pipe is made to be a Laval type spray pipe, the temperature control device is provided with a temperature control cylinder and the temperature control spray pipe arranged at the right end of the temperature control cylinder, the left end of the temperature control cylinder is hermetically connected with the combustion chamber, the engine spray pipe is arranged in an inner cavity of the temperature control cylinder, the temperature control cylinder is connected with a temperature control gas source through a pipeline, and the temperature control spray pipe is made to be a Laval type spray pipe. Therefore, the power system for comprehensively researching the heat transfer multiphase flow noise is simple in structure, convenient to regulate and control, strong in functionality, high in accuracy and wide in application range. In practical application, according to inflow conditions (temperature, pressure and flow velocity) required by experimental heat transfer research or noise research, the temperature, pressure and flow of gas flow ejected by a rocket engine and the temperature, pressure and flow of temperature control air flow are regulated and controlled, the gas flow and the temperature control air flow are mixed in a temperature control cylinder and carry out momentum and energy exchange, and the temperature, pressure and flow velocity of the mixed air flow are changed after the mixed air flow is contracted and expanded through a temperature control spray pipe, so that the requirement of the inflow conditions required by the heat transfer research or the noise research is met.
The power system for comprehensively researching the heat transfer multiphase flow noise is described in detail below by referring to the specific embodiment shown in the attached drawings.
Drawings
FIG. 1 is a schematic diagram of a power system for noise synthesis of heat transfer multiphase flow in accordance with the present invention;
FIG. 2 is a schematic diagram of a partial structure of a power system for comprehensive study of noise of heat transfer multiphase flow according to the present invention.
Detailed Description
First, it should be noted that, the directional terms such as up, down, left, right, front, rear, etc. described in the present invention are only described with reference to the accompanying drawings for easy understanding, and do not limit the technical solution and the claimed scope of the present invention.
Fig. 1 and 2 show an embodiment of a power system for comprehensive research of heat transfer multiphase flow noise, which comprises a rocket engine 1 and a temperature control device 2. The rocket engine 1 comprises a combustion chamber 11 and an engine nozzle 12 at the right end of the combustion chamber 11. The combustion chamber 11 is connected with the fuel source 3 and the combustion-supporting gas source 4 through pipelines, and the engine nozzle 12 adopts a Laval type nozzle. Let temperature control device 2 set up temperature control section of thick bamboo 21 and be in the temperature control spray tube 22 of temperature control section of thick bamboo 21 right-hand member, with the left end of temperature control section of thick bamboo 21 and combustion chamber 11 sealing connection and make engine spray tube 12 be in the inner chamber of temperature control section of thick bamboo 21, let temperature control section of thick bamboo 21 pass through pipe connection temperature control air supply 5, make temperature control spray tube 22 adopt the laval type spray tube. The power system for comprehensively researching the heat transfer multiphase flow noise is simple in structure, convenient to regulate and control, strong in functionality, high in accuracy and wide in application range. In practical application, according to inflow conditions (temperature, pressure and flow velocity) required by experimental heat transfer research or noise research, the temperature, pressure and flow of gas flow ejected by the rocket engine 1 and the temperature, pressure and flow of temperature-controlled air flow are regulated and controlled, the gas flow and the temperature-controlled air flow are mixed in the temperature-controlled cylinder 21 and subjected to momentum and energy exchange, and the temperature, pressure and flow velocity of the mixed air flow are changed after the mixed air flow contracts and expands through the temperature-controlled spray pipe 22, so that the requirements of the inflow conditions required by the heat transfer research or the noise research are met. It should be noted that once the rocket engine is determined, the working conditions, particularly the gas components and the combustion temperature conditions are relatively determined, and the invention realizes the precise regulation and control of the temperature, the pressure and the flow rate of the mixed gas flow mainly by changing the mixing ratio of the temperature control gas flow and the gas flow ejected by the rocket engine. In practical application, the invention generally adopts air or oxygen as combustion-supporting gas and adopts air, nitrogen or helium as temperature control gas.
As an optimized scheme, the spray hood 6 is arranged at the outlet of the temperature control spray pipe 22, and the spray hood 6 is connected with the spray medium source 7 through a pipeline. According to the inflow conditions (temperature, pressure and flow rate) required by experimental multiphase flow research or noise research, the spraying medium and the mixed gas flow can exchange momentum and energy in the spraying cover 6 and form multiphase flow by combining regulation of the output conditions of the spraying medium on the basis of regulation of the mixed gas flow, so that the requirement of the inflow conditions required by the multiphase flow research or noise research is met. It should be noted that, in practical applications, the present invention generally uses water as the spraying medium, but is not limited to water, and other types of spraying media, such as ether, glycerol, ammonia water, etc., may also be used according to experimental research needs.
As an optimized solution, the present embodiment employs a fuel storage tank as the fuel source 3, and the fuel storage tank is sequentially connected to the first extrusion gas tank 31 and the first extrusion gas source 32 through a pipeline, and a first pressure reducing valve 33 is provided on the pipeline between the first extrusion gas tank 31 and the fuel storage tank. Because the working condition of the rocket engine is relatively determined, the arrangement forms an extrusion type fuel supply and delivery structure, the supply and delivery amount of fuel can be accurately controlled by regulating and controlling the working pressure of the first extrusion gas tank 31 and the first pressure reducing valve 33, the supply and delivery amount of combustion-supporting gas can be jointly regulated and controlled, the depth adjustment of the gas flow sprayed out by the rocket engine can be realized, and the functionality and the practicability are improved. Similarly, in the present embodiment, the spraying medium source 7 adopts a spraying medium storage tank, the spraying medium storage tank is sequentially connected to the second extrusion gas tank 71 and the second extrusion gas source 72 through a pipeline, and a second pressure reducing valve 73 is provided on the pipeline between the second extrusion gas tank 71 and the spraying medium storage tank. The arrangement forms an extrusion type spraying medium supply and delivery structure, the aim of accurately controlling the supply and delivery amount of the spraying medium is fulfilled by regulating and controlling the working pressure of the second extrusion gas tank 71 and the second pressure reducing valve 73, and the functionality, controllability and practicability are enhanced. It should be noted that, in practical applications, the present invention generally uses air, nitrogen or helium as the extrusion gas.
As an optimized scheme, in the present embodiment, a combustion-supporting gas tank 41 is disposed on a pipeline between the combustion-supporting gas source 4 and the combustion chamber 11, and a third pressure reducing valve 42 is disposed on a pipeline between the combustion-supporting gas tank 41 and the combustion chamber 11. This structural arrangement improves the stability of the supply and delivery of the combustion-supporting gas by the combustion-supporting gas tank 41, and improves the accuracy of the supply and delivery of the combustion-supporting gas by controlling the operating pressure of the third pressure reducing valve 42. Similarly, in the present embodiment, a temperature-controlled air tank 51 is provided in the pipeline between the temperature-controlled air source 5 and the temperature-controlled cylinder 21, and a fourth pressure reducing valve 52 is provided in the pipeline between the temperature-controlled air tank 51 and the temperature-controlled cylinder 21. This configuration improves the stability of temperature-controlled gas supply and delivery by the temperature-controlled gas tank 51, and improves the accuracy of temperature-controlled gas supply and delivery by the fourth pressure reducing valve 52.
As an optimized scheme, the present embodiment adopts the following structure for the spray cover 6: a spray chamber 61 is provided in the peripheral wall of the spray cover 6, a plurality of nozzles 62 communicating with the spray chamber 61 are provided on the inner wall of the spray cover 6, and the spray medium source 7 is made to communicate with the spray chamber 61 through a pipe. This structural arrangement can effectively improve the stability and the homogeneity of spraying. Meanwhile, the temperature control barrel 21 and the temperature control spray pipe 22 are integrally manufactured in the embodiment, so that the structure and the process are simplified; the left end of the spray cover 6 is connected with the temperature control device 2 through a switching frame 63 which can move left and right so as to adjust the position, and the right half part of the inner cavity of the spray cover 6 adopts a round table shape with a small left and a big right to match with the temperature control spray pipe 22.
It should be noted that, in practical application, the present invention also connects the spraying medium source 7 to the spraying medium replenishing device 74 through a pipeline so as to replenish the spraying medium clearly. And stop valves are respectively arranged on a pipeline between the first pressure reducing valve 33 and the fuel source 3, a pipeline between the fuel source 3 and the rocket engine 1, a pipeline between the second pressure reducing valve 73 and the spraying medium source 7, a pipeline between the spraying medium source 7 and the spray cover 6, a pipeline between the third pressure reducing valve 42 and the rocket engine 1, a pipeline between the fourth pressure reducing valve 52 and the temperature control cylinder 21, and a pipeline between the spraying medium liquid supplementing device 74 and the spraying medium source 7, so that the control and maintenance are convenient.
To assist the skilled person in understanding the present invention, the following brief description of the regulation of the power system is provided:
according to the temperature T of the air flow required by experimental heat transfer research or noise researchc2Pressure pc2And flow rate uc2Regulating the temperature T of the gas stream ejected from the rocket enginec0Pressure pc0And flow rate qc0And the temperature T of the temperature-controlled air flowc1Pressure pc1And flow rate qc1The mixed airflow sprayed out from the temperature control spray pipe can meet the requirement of inflow conditions. In practical application, coarse adjustment can be performed according to the relations of the formulas (1) to (6), and then fine adjustment can be performed according to the detection structure.
In formulae (1) to (6), cp0Constant pressure specific heat for gas flow, cp1Constant pressure specific heat for temperature-controlled airflow, cp2For the mixed gas flow with constant pressure and specific heat, R0Is the gas constant, R, of the gas stream1For temperature control of gas constant of gas flow, R2Is the gas constant of the mixed gas stream, gamma0Specific heat ratio of gas flow, gamma1For temperature control of specific heat ratio of air flow, gamma2Is the specific heat ratio of the mixed gas flow, V2Channel volume for mixed gas flow, Ma2The Mach number of the temperature control spray pipe.
Similarly, the temperature T of the multiphase flow is determined according to experimental multiphase flow research or noise researchc4Pressure pc4And flow rate uc4On the basis of mixed gas flow regulation and control, the temperature T of the spraying medium is regulated and controlled in a combined mannerc3Pressure pc3Flow rate qc3And flow rate uc3The multiphase flow sprayed out from the spray cover can meet the requirement of inflow conditions. In practical application, the coarse adjustment can be performed according to the relationship of the formulas (7) to (11), and then the fine adjustment can be performed according to the detection structure.
In formulae (7) to (11), cp3Constant pressure specific heat for spraying medium steam, cp4For constant pressure specific heat of multiphase flow, R3Is the gas constant of the spray medium vapor, R4Is a gas constant of multiphase flow, V4The delta H is the total energy consumed by latent heat of vaporization, spray medium droplet resistance and interphase resistance of the spray medium after the spray medium is mixed into the mixed gas flow.
The above examples are only for describing the preferred embodiments of the present invention, and do not limit the scope of the claimed invention, and various modifications made by those skilled in the art according to the technical solutions of the present invention should fall within the scope of the invention defined by the claims without departing from the design concept of the present invention.
Claims (9)
1. A power system for comprehensive research of heat transfer multiphase flow noise comprises a rocket engine (1) and a temperature control device (2), wherein the rocket engine (1) comprises a combustion chamber (11) and an engine spray pipe (12) arranged at the right end of the combustion chamber (11), the power system is characterized in that the combustion chamber (11) is connected with a fuel source (3) and a combustion-supporting gas source (4) through pipelines, the engine spray pipe (12) is a Laval type spray pipe, the temperature control device (2) comprises a temperature control cylinder (21) and a temperature control spray pipe (22) arranged at the right end of the temperature control cylinder (21), the left end of the temperature control cylinder (21) is hermetically connected with the combustion chamber (11) and enables the engine spray pipe (12) to be arranged in an inner cavity of the temperature control cylinder (21), the temperature control cylinder (21) is connected with a temperature control gas source (5) through a pipeline, the temperature control spray pipe (22) is a Laval type spray pipe, and a spray cover (6) is arranged at an outlet of the temperature control spray pipe (22), the spraying cover (6) is connected with a spraying medium source (7) through a pipeline.
2. The power system for comprehensive research on heat transfer multiphase flow noise according to claim 1, wherein the fuel source (3) is a fuel storage tank, the fuel storage tank is sequentially connected with a first extrusion gas tank (31) and a first extrusion gas source (32) through a pipeline, and a first pressure reducing valve (33) is arranged on the pipeline between the first extrusion gas tank (31) and the fuel storage tank.
3. The power system for comprehensively researching heat transfer multiphase flow noise according to claim 2, wherein the spraying medium source (7) is a spraying medium storage tank, the spraying medium storage tank is sequentially connected with a second extrusion gas tank (71) and a second extrusion gas source (72) through a pipeline, and a second pressure reducing valve (73) is arranged on the pipeline between the second extrusion gas tank (71) and the spraying medium storage tank.
4. The power system for comprehensive research on heat transfer multiphase flow noise according to claim 3, wherein a combustion-supporting gas storage tank (41) is arranged on a pipeline between the combustion-supporting gas source (4) and the combustion chamber (11), and a third pressure reducing valve (42) is arranged on a pipeline between the combustion-supporting gas storage tank (41) and the combustion chamber (11).
5. The power system for comprehensive research on heat transfer multiphase flow noise as claimed in claim 4, wherein a temperature-controlled air storage tank (51) is arranged on a pipeline between the temperature-controlled air source (5) and the temperature-controlled cylinder (21), and a fourth pressure reducing valve (52) is arranged on a pipeline between the temperature-controlled air storage tank (51) and the temperature-controlled cylinder (21).
6. The power system for comprehensively researching heat transfer multiphase flow noise according to claim 5, wherein a spraying cavity (61) is formed in the peripheral wall of the spraying cover (6), a plurality of nozzles (62) communicated with the spraying cavity (61) are formed in the inner wall of the spraying cover (6), and the spraying medium source (7) is communicated with the spraying cavity (61) through a pipeline.
7. The power system for comprehensive research on heat transfer multiphase flow noise as claimed in claim 6, wherein the temperature control barrel (21) and the temperature control nozzle (22) are made in one piece; the left end of the spraying cover (6) is connected with the temperature control device (2) through a switching frame (63) capable of moving left and right, and the right half part of the inner cavity of the spraying cover (6) is in a truncated cone shape with a small left and a large right.
8. The power system for comprehensive research on heat transfer multiphase flow noise as recited in claim 7, characterized in that the spraying medium source (7) is further connected with a spraying medium liquid supplementing device (74) through a pipeline.
9. The power system for comprehensive research on heat transfer multiphase flow noise according to claim 8, wherein stop valves are respectively arranged on a pipeline between the first pressure reducing valve (33) and the fuel source (3), a pipeline between the fuel source (3) and the rocket engine (1), a pipeline between the second pressure reducing valve (73) and the spraying medium source (7), a pipeline between the spraying medium source (7) and the spray hood (6), a pipeline between the third pressure reducing valve (42) and the rocket engine (1), a pipeline between the fourth pressure reducing valve (52) and the temperature control cylinder (21), and a pipeline between the spraying medium liquid supplementing device (74) and the spraying medium source (7).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110368227.1A CN113074065B (en) | 2021-04-06 | 2021-04-06 | Power system for comprehensive research of heat transfer multiphase flow noise |
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| CN202110368227.1A CN113074065B (en) | 2021-04-06 | 2021-04-06 | Power system for comprehensive research of heat transfer multiphase flow noise |
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| CN113074065B true CN113074065B (en) | 2022-04-01 |
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