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

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Author
Lenzini, Martin Joseph
Date
1968-06
Advisor
Vavra, M.H.
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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.
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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.
URI
http://hdl.handle.net/10945/11753
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  • 1. Thesis and Dissertation Collection, all items

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