Quick temperature and pressure change device and temperature and pressure change method for high-temperature wind tunnel

Abstract

The invention provides a quick temperature and pressure change device and a temperature and pressure change method for a high-temperature wind tunnel and belongs to the technical field of high-temperature wind tunnels. Aiming at the problem that under certain pressure and flow conditions, a single adjustment mode can not meet the requirement of the high-temperature wind tunnel with a high Mach number, the following technical scheme is provided and the quick temperature and pressure change device and the temperature and pressure change method for the high-temperature wind tunnel is characterized in that the device comprises a main gas inlet pipe, a first annular gas inlet pipe, a second annular gas inlet pipe, a pressure stabilizing box and a gas outlet pipe, wherein the first annular gas inlet pipe is mounted at the left side of the main gas inlet pipe, the second annular gas inlet pipe is arranged at the other side of the main gas inlet pipe, the connecting part of each of the first annular gas inlet pipe and the second annular gas inlet pipe and the main gas inlet pipe is provided with an opening, the main gas inlet pipe is connected with one end of the pressure stabilizing box,and the other end of the pressure stabilizing box is connected with the gas outlet pipe. The flow ratio of cold gas flow to hot gas flow is automatically converted, and a back pressure valve bank is additionally arranged to filter total pressure fluctuations in an adjustment process so as to ensure the constant upper limits of a total temperature value and a total pressure threshold value in the adjustment process and avoid the linkage between the aperture of a pressure adjusting valve and the flow of cold and hot pipelines, thereby ensuring quick adjustment of the total pressure of a system.

Description

technical field [0001] The invention relates to the technical field of high-temperature wind tunnels, in particular to a rapid temperature-variable-pressure device and a temperature-variable-pressure method for high-temperature wind tunnels. Background technique [0002] With the continuous development of aerospace technology, the development of high Mach aircraft in close space has attracted more and more attention. Compared with traditional aircraft and catapult aircraft, high Mach aircraft has a very wide flight envelope, showing a wide range of altitudes and flying Mach numbers. Due to the wide range, the complexity of aerodynamic problems is greatly increased, and the complex flow physical process brings severe challenges to the integrated design. Simulating the actual flow process as much as possible puts forward high requirements for the ground wind tunnel experimental equipment, and the high Mach The number of aircraft must keep flying within a range of dynamic press...

AI Technical Summary

Problems solved by technology

[0002] With the continuous development of aerospace technology, the development of high Mach aircraft in close space has attracted more and more attention. Compared with traditional aircraft and catapult aircraft, high Mach aircraft has a very wide flight envelope, showing a wide range of altitudes and flying Mach numbers. Due to the wide range, the complexity of aerodynamic problems is greatly increased, and the complex flow physical process brings severe challenges to the integrated design. Simulating the actual flow process as much as possible puts forward high requirements for the ground wind tunnel experimental equipment, and the high Mach The number of aircraft must keep flying within a range of dynamic pressure. In addition to cruising, some special conditions during the flight (such as changes in the flight Mach number caused by acceleration and deceleration) will, on the one hand, lead to changes in the overall performance of the aircraft and dynamic Response prediction is difficult. On the other hand, the internal flow parameters of the engine change greatly, which directly affects the working state of the combustion chamber. In order to study the performance of high Mach number aircraft under incoming flow conditions, ground experimental equipment is required to simulate the aircraft as accurately as possible. real working environment

[0003] Conventional high-temperature wind tunnels use solid block nozzle experiments, which cannot simulate abnormal flight processes, which largely limits the development of high-Mach number aircraft. High-temperature variable Mach number wind tunnels are an effective way to realize flow field changes in ground test equipment , using soft-wall nozzles or rotating nozzles to achieve real-time adjustable throat cross-sectional area, but the current high-temperature variable Mach number schemes can only achieve rapid changes in flight speed, and cannot achieve temperature and temperature along a certain flight envelope. The pressure can be adjusted in real time. In general, the most commonly used method of variable pressure and temperature is to achieve the purpose of pressure control and temperature control through the adjustment of pressure regulating valves and combustion heaters. Once it is necessary to simulate at the same time under certain pressure and flow conditions When matching the complex flight state change process of high-temperature airflow, a single adjustment method cannot meet the actual needs of high-Mach number high-temperature wind tunnels

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