DEVICE FOR TESTING SAMPLES thermodynamic heat protection AIRCRAFT WITH aircraft gas turbine engines with afterburner combustion

摘要

The utility model relates to a ground test samples heat-shielding area hypersonic aircraft dynamic pressure effect on the high-temperature gas jet and can be used in the selection of heat and sound insulation in gas ducts of power plants. Installation comprising aircraft gas turbine engine with afterburner mounted on an airplane or stand adjustable height and distance from the aircraft stand nozzle test samples thermal protection for hypersonic aircraft and pressure sensors and the gas flow temperature, sets of test and recording apparatus, and a source of high pressure and high temperature gas stream is a standard aircraft gas turbine engine afterburner combustion chamber, it is established nny plane or stand. The technical result in the achievement of which the claimed utility model consists in combining 2 parameters - speed pressure and the gas stream temperature in a single installation, while providing both parameters close to the parameters circumfluent flow in real hypersonic flight, with the necessary length and mobility of experiment.