Calibration of turbine test rig with impulse turbine at high pressure ratios

摘要

The Transonic Turbine Test Rig of the Turbo- PropulsionLaboratory, Department of Aeronautics, of the Naval PostgraduateSchool was designed to investigate the performanceof turbines with transonic or supersonic rotor inletvelocities. The test rig has provisions for testing singlestage axial turbines at high pressure ratios and at variableaxial and radial clearances. The present study describesthe calibration of the turbine test rig with an impulseturbine at high pressure ratios. The turbine stage consistsof a double circular-arc rotor with sharp leading edges anda stator with converging nozzle type blading. The resultsof the flow rate calibration and labyrinth seal leakage testsare described. The instrumentation necessary to separaterotor and stator losses is also discussed.