Calibration of turbine test rig with impulse turbine at high pressure ratios
calibrationoftur00lenz.pdf (6.179Mb)Abstract
The Transonic Turbine Test Rig of the Turbo- Propulsion
Laboratory, Department of Aeronautics, of the Naval Postgraduate
School was designed to investigate the performance
of turbines with transonic or supersonic rotor inlet
velocities. The test rig has provisions for testing single
stage axial turbines at high pressure ratios and at variable
axial and radial clearances. The present study describes
the calibration of the turbine test rig with an impulse
turbine at high pressure ratios. The turbine stage consists
of a double circular-arc rotor with sharp leading edges and
a stator with converging nozzle type blading. The results
of the flow rate calibration and labyrinth seal leakage tests
are described. The instrumentation necessary to separate
rotor and stator losses is also discussed.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
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