Accession Number : AD0847619
Title : Calibration of Turbine Test Rig with Impulse Turbine at High Pressure Ratios.
Descriptive Note : Thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Lenzini, Martin Joseph
Report Date : JUN 1968
Pagination or Media Count : 143
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. (Author)
Descriptors : (*AXIAL FLOW TURBINES, TRANSONIC CHARACTERISTICS), (*TEST FACILITIES, CALIBRATION), TURBINE BLADES, TURBINE STATORS, GAS TURBINE NOZZLES, GAS SEALS, NOZZLE GAS FLOW, LEAKAGE(FLUID), SUBROUTINES, COMPUTER PROGRAMS, THESES.
Subject Categories : Non-electrical Energy Conversion
Test Facilities, Equipment and Methods
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE