THE EQUIPMENT OF RELIABILITY TEST OF THE GAS TURBINE BLADE WITH INTERNAL COOLING HOLES AND THE TEST METHOD

摘要

PURPOSE: A device and method of testing the durability of a hollow shape of a gas turbine blade are provided to measure the performance of a gas turbine blade having a complex cooling path to lower the temperature of metal. CONSTITUTION: A device for testing the durability of a hollow shape of a gas turbine blade comprises an air compressor(10), a first air tank(20), a second air tank(40), an air heater(70), a third air tank(110), a gas tank(120), and a combustor(160). The air compressor compresses air and stores it under high pressure. The first air tank is connected to the air compressor and stores air. The second air tank is connected to the first air tank and stores air flowing into the air compressor. The air heater is connected to the second air tank. The air heater heats air, which is supplied to the inner surface of a blade. The third air tank is connected to the first air tank and stores air flowing into the air compressor.