Calibration of turbine test rig with impulse turbine at high pressure ratios
Lenzini, Martin Joseph
MetadataShow full item record
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.
Showing items related by title, author, creator and subject.
Newell, Brandon H. (Monterey, California. Naval Postgraduate School, 2010-09);In this thesis, the author evaluated whether HOMER Micropower Optimization should be used by the Marine Corps as a pre-deployment tool for meeting expeditionary energy demands. The author created two unique experiments ...
Turner, Philip H. (Monterey, California. Naval Postgraduate School, 1995-12);The measurement of soot particulates densities in gas turbine engine and rocket exhausts is an area of continuing scientific investigation. Knowledge of exhaust plume soot concentration and sizing is critical for plume ...
Esdaile, Stewart Gary (Monterey, California. U.S. Naval Postgraduate School, 1969-10);The Transonic Turbine Test Rig installed in the Turbo-Propulsion Laboratory at the Naval Postgraduate School was designed such that losses in nozzles and rotor blading and overall performance characteristics can be determined ...