UNIT FOR GAS DYNAMIC TESTING Russian patent published in 2021 - IPC G01N25/72 G01N25/24 G01M9/00 G01M13/00 

FIELD: measuring.

SUBSTANCE: invention relates to the field of industrial aerothermodynamics and can be used in studying the aerothermomechanical resistance of materials and structural elements of aviation and rocket eqiupment for the effects of high-enthalpy high-speed gas flows. The unit comprises at least one combustion chamber with an aerodynamic nozzle, equipped with an ignition system, a fuel supply system connected to the first input of the combustion chamber and including a fuel source, a fuel line, a first controlled valve, a fuel flow rate regulator, a first flowmeter equipped with a nozzle, an oxygen supply system connected to the second input of the combustion chamber and including an oxygen source, an oxygen line, an oxygen flow rate regulator, a second controlled valve, a second flowmeter equipped with a nozzle, a neutral gas supply system including a neutral gas line, a neutral gas source, the output whereof is connected to the input of the neutral gas pressure regulator, the output whereof is connected with the third and fourth controlled valves installed in parallel, pressure sensors, the inputs of the first ones whereof are connected to the cavities of the flowmeter apparatuses before and the inputs of the second ones after the nozzles installed therein, a controlling and recording block connected to the corresponding inputs of the controlled valves, the corresponding input of the ignition system, and the outputs of the pressure sensors. The new feature of the invention consists in the fact that the ignition system is made in the form of a pilot burner containing at least one spark plug connected to the controlling and recording unit, a combustion chamber with an own nozzle, equipped with separate inputs for connecting to the fuel and oxygen supply systems, connected by the nozzle thereof to the bottom of the combustion chamber with an aerodynamic nozzle. The fuel and oxygen supply systems of the combustion chamber are additionally equipped with a fuel intake collector and an oxygen intake collector, a fifth and a sixth controlled valves, respectively. The unit is additionally equipped with a flame extinguishing sensor and a video surveillance camera, the outputs whereof are connected with the inputs of the controlling and recording unit, configured to record the state of the gas flow at the output of the aerodynamic nozzle. The unit can be equipped with a system for monitoring the gas concentration in the ambient air, the output whereof can be connected with the corresponding input of the controlling and recording unit.

EFFECT: implementation of the parameters of thermomechanical impact on the tested material or structure of a high-enthalpy high-speed gas flow characteristic of the movement of an aerial vehicle in the atmosphere with a hypersonic speed, most closely resembling the full-scale parameters, provided possibility of growing the productivity of the unit by connecting additional fuel and oxygen modules, as well as provided possibility of complying with the conditions for safe operation of the unit when using gaseous explosive and flammable high-energy components of the fuel - hydrogen and oxygen.

4 cl, 1 dwg