CN111397833B - High-enthalpy supersonic wind tunnel airflow generation method - Google Patents
High-enthalpy supersonic wind tunnel airflow generation method Download PDFInfo
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- CN111397833B CN111397833B CN202010322141.0A CN202010322141A CN111397833B CN 111397833 B CN111397833 B CN 111397833B CN 202010322141 A CN202010322141 A CN 202010322141A CN 111397833 B CN111397833 B CN 111397833B
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Abstract
The embodiment of the invention relates to a method for generating high-enthalpy supersonic wind tunnel airflow, which comprises the following steps: acquiring an experimental gas, and heating the experimental gas to a preset temperature; determining target temperature and target pressure required by a hypersonic equipment experiment; after the experimental gas heated to the target temperature is flushed into the heat-insulating container, carrying out heat-insulating compression to reach the target temperature and the target pressure; discharging the experimental gas reaching the target temperature and the target pressure into a gas collector; the pressure and the temperature in the gas collector reach a stable state through the continuous inflation, compression and exhaust cycle working process of the pistons and the cooperation of the multiple groups of pistons, and the gas collector is used as a continuous high-temperature and high-pressure gas source of the wind tunnel. According to the scheme, the gas pressure is improved in a piston compression mode, so that high-temperature and high-pressure gas is obtained, and the total enthalpy value of the gas is improved in a compression work mode. The method can design the heating temperature and pressure according to the parameters of the requirement to meet the requirement of the wind tunnel on the temperature and the pressure at the same time.
Description
Technical Field
The embodiment of the invention relates to a method for generating high-enthalpy supersonic wind tunnel airflow.
Background
At present, hypersonic ground simulation equipment capable of simulating a real flight state mainly adopts a pulse type and a temporary impulse type. The heating mode of the pulse wind tunnel is mainly by shock wave pressurization heating, and the principle is that the working medium is heated by the shock wave generated by high-pressure gas at the instant of membrane rupture. The high-pressure gas is generated by methods such as piston compression, detonation and the like. The action time is short, the experiment time is limited by the total amount of experiment working media, generally in the range of microseconds to milliseconds, and the magnitude of seconds is difficult to exceed.
The other temporary-impulse type mainly takes combustion heating and heat accumulation heating as main parts, the time is from several seconds to hundreds of seconds, the running time of the combustion mode equipment can be infinitely long theoretically, and as long as air supply can be continuous; the heat storage mode is limited by the volume of the energy storage body, namely the total heat storage energy. However, generally, the total temperature is below 2100K, which is suitable for combustion and heat accumulation heating modes, and thus, longer experimental time can be obtained. Above 2100K total temperature, combustion and heat storage modes can be achieved, but the system design and operation are extremely complex.
For the study of air-breathing propulsion system combustion, it is desirable to simulate the combustion process so that in addition to the reynolds number, mach number and prandtl number, the temperature needs to be uniform and the incoming flow composition is preferably pure air. In addition, the operating time of the equipment cannot be too short, mainly the time scale required for establishing the temperature boundary layer is longer, and is generally about several seconds to tens of seconds. The current common wind tunnel heat source mode of combustion heating can not obtain more accurate combustion research results in practice.
Because this device can obtain the state that surpasss above the adiabatic temperature of burning flame through adiabatic compressed energy addition mode, adopts heat accumulation or indirect heating to avoid experimental gas component's pollution simultaneously, to the research in the aspect of breathing in formula propulsion system and aerodynamic heat, the influence of component is very important, and the flight state that can be completely reappeared and obtain longer experimental time of this scheme of adoption.
Disclosure of Invention
In order to solve the technical problem or at least partially solve the technical problem, an embodiment of the present application provides a method for continuously generating a high enthalpy supersonic wind tunnel airflow, including:
acquiring an experimental gas, and heating the experimental gas to a preset temperature;
determining target temperature and target pressure required by a hypersonic equipment experiment;
filling the experimental gas heated to the preset temperature into a heat-insulating container, and then performing heat-insulating compression to reach the target temperature and the target pressure;
discharging the test gas reaching the target temperature and target pressure into a gas collector;
the pressure and the temperature in the gas collector reach a stable state through the continuous inflation, compression and exhaust cycle working process of the pistons and the cooperation of the multiple groups of pistons, and the gas collector is used as a continuous high-temperature and high-pressure gas source of the wind tunnel.
In one possible embodiment, the heating of the test gas comprises: regenerative heating or heat exchange preheating.
In one possible embodiment, the target temperature is calculated by:
wherein, P2Is a target pressure, P1For pre-charge pressure, T2Is the target total temperature, T1At a preset temperature, Z is a compression ratio, and k is a specific heat ratio of the experimental gas.
In one possible embodiment, the target pressure is calculated by:
P2＝P1Zk
wherein, P2Is a target pressure, P1Z is the compression ratio and k is the specific heat ratio of the experimental gas.
The temperature and pressure in the working container are ensured to be stable through the continuous work of a plurality of groups of pistons, and the aim of continuous work is fulfilled
According to the scheme, the gas under low pressure is heated to the preset temperature and is added into the heat insulation container, the pressure and the temperature of the gas are improved in a piston compression mode, so that the high-temperature and high-pressure gas is obtained, and the total enthalpy value of the gas is improved in a compression work mode. The method can design preheating temperature and pressure according to required parameters to meet the simultaneous requirements of the wind tunnel on the temperature and the pressure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.
Fig. 1 is a flowchart of a method for generating high-enthalpy supersonic wind tunnel airflow according to an embodiment of the present application;
fig. 2 is a schematic view of an operation principle of a novel wind tunnel air source provided in an embodiment of the present application.
FIG. 3 is a schematic diagram of the operation of the continuous air supply provided in the embodiments of the present application
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, technical methods in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without any creative effort, shall fall within the scope of the present invention.
It should be noted that, if directional indications (such as up, down, left, right, front, back, etc.) are involved in the embodiment of the present invention, the directional indications are only used for explaining the relative positional relationship between the components in a certain posture, the motion situation, etc., and if the certain posture is changed, the directional indications are changed accordingly.
Fig. 1 is a flowchart of a method for generating a high enthalpy supersonic wind tunnel airflow according to an embodiment of the present application, and as shown in fig. 1, the method includes:
step S11, obtaining experimental gas, and heating the experimental gas to a preset temperature;
step S12, determining a target temperature and a target pressure required by the experiment of the hypersonic equipment;
in the step, the target temperature and the target pressure in front of the hypersonic equipment nozzle can be determined according to the experimental requirements.
Step S13, after the experimental gas heated to the preset temperature is flushed into the heat-insulating container, the experimental gas is subjected to heat-insulating compression to reach the target temperature and the target pressure; wherein the pre-charge pressure of the experimental gas during the injection into the heat-insulating container is P1。
In this embodiment, the experimental gas is an ideal or truly compressible gas, and is particularly suitable for experimental working media such as air, oxygen, nitrogen and the like which follow the law of compressible gas. The manner of heating the test gas includes: heat accumulation heating or heat exchange heating. In the step, the purity of the heated gas is ensured by pre-compressing the hot gas and adopting heat storage heating or heat exchange heating.
The target pressure in this step is calculated in the following manner:
P2＝P1Zk
wherein, P2Is a target pressure, P1Z is the compression ratio and k is the specific heat ratio of the experimental gas. The compression ratio Z is an adjustable parameter, so the operating parameters of the plant, pressure, temperature and time, can be set more flexibly.
The target temperature in this step is calculated in the following manner:
wherein, T2Is a target temperature, T1At a preset temperature, Z is a compression ratio, and k is a specific heat ratio of the experimental gas. The compression ratio Z is an adjustable parameter, so the operating parameters of the plant, pressure, temperature and time, can be set more flexibly.
Step S14, discharging the experimental gas reaching the target temperature and the target pressure into a gas collector;
and step S15, the pressure and temperature in the gas collector reach stable states through the continuous inflation, compression and exhaust cycle working process of the pistons and the cooperation of the multiple groups of pistons, and the gas collector is used as a continuous high-temperature and high-pressure gas source of the wind tunnel.
In this step, the compression work is used to drive the compression process by accumulating high-pressure gas, and the constant compression pressure and the stable working gas pressure can be obtained by maintaining the stable inflation pressure.
The compressed gas driven mode can adopt a method that a large piston drives a small piston to obtain pressurization. Therefore, the requirement on energy storage pressure can be greatly reduced when ultrahigh pressure is realized, and the energy consumption of the whole operation is reduced.
Specifically, according to newton's first law, it can be determined that the forces before and after the piston are balanced. And the force experienced by the piston is the front and rear piston pressures multiplied by the area. The calculation formula is as follows:
wherein, P0Is the driving pressure of the piston, S0Is the area of the driving side of the piston, S2Is the experimental gas side piston area. d0Is the large piston diameter, d2Is the small piston diameter.
In the embodiment, the working process is controlled by the experimental gas through the switch of the quick switch valve, namely the valve is closed in the processes of inflation and compression, the valve is opened in the working process, and the valve is closed after the working process is finished. Fig. 2 is a schematic view of a novel wind tunnel operation principle provided by an embodiment of the present application, and as shown in fig. 2, a working process of each piston, namely "inflation-compression-exhaust" may be regarded as an independent working process, and a plurality of independent processes may be performed in parallel to achieve continuous generation of high-pressure high-temperature gas. With reference to fig. 3, the finally generated high-temperature gas has a stable pressure state and small pulsation, and is very good wind tunnel airflow.
The embodiments of the present invention have been described in detail, but the present invention is not limited to the embodiments described above as examples. It will be appreciated by those skilled in the art that various equivalent changes and modifications can be made without departing from the spirit and scope of the invention, and it is intended to cover all such modifications and alterations as fall within the true spirit and scope of the invention.
Claims (3)
1. A high-enthalpy supersonic wind tunnel airflow generation method is characterized by comprising the following steps:
determining total temperature and total pressure required by a hypersonic equipment experiment;
acquiring an experimental gas, and heating the experimental gas to a preset temperature;
filling the experimental gas heated to the preset temperature into a heat-insulating container, and then performing heat-insulating compression to reach the target temperature and the target pressure;
discharging the experimental gas reaching the target temperature and the target pressure into a gas collector;
the pressure and the temperature in the gas collector reach a stable state through the continuous inflation, compression and exhaust cycle working process of the pistons and the cooperation of a plurality of groups of pistons, and the gas is used as a continuous high-temperature and high-pressure gas source of the wind tunnel;
the target temperature is calculated by the following method:
wherein, P2Is a target pressure, P1For pre-charge pressure, T2Is the target total temperature, T1For the total pre-heating temperature, Z is the compression ratio and k is the specific heat ratio of the test gas.
2. The method of claim 1, wherein preheating the test gas comprises: heat accumulation heating or heat exchange heating.
3. The method of claim 1, wherein the target pressure is calculated by:
P2＝P1Zk
wherein, P2Is a target pressure, P1The total pressure, Z the compression ratio and k the specific heat ratio of the test gas.
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| CN112762444B (en) * | 2020-12-31 | 2022-08-12 | 中国航天空气动力技术研究院 | Optimization method for heat accumulator temperature distribution curve at initial moment of ventilation process |
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| JP5936367B2 (en) * | 2012-01-20 | 2016-06-22 | 三菱重工業株式会社 | Combustion control device and control method for internal combustion engine |
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