Accession Number : ADA306473
Title : Turbine Performance Mapping of the Space-Shuttle Main Engine High-Pressure Fuel Turbopump.
Descriptive Note : Master's thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Greco, Philip A.
PDF Url : ADA306473
Report Date : SEP 1995
Pagination or Media Count : 162
Abstract : The redesign, data acquisition system installation, and software development for the cold-flow Turbine Test Rig is reported. The turbine tested was the Space Shuttle Main Engine High Pressure Fuel Turbopump first stage 'Alternate Turbopump Development' model designed and manufactured by Pratt & Whitney. The purpose of - this research was to establish a continuously operating, cdd-flow, turbine test facility which could be used for future laser-Doppler-velocimetry measurements in the tip leakage region of the turbine rotor blades. Also, to determine both the single and two stage turbine performance parameters, and to provide a test model for comparison with numerical simulations using a three-dimensional viscous flow code. A throttle valve was designed and installed at the turbine exit to control the pressure ratio in order to map the turbine performance. Data acquisition, reduction and display programs were developed using LabVIEW Visual Instrument software in order to collect, and process the data. The first-stage turbine exit velocity profile was measured using a cobra probe. Also, the first-stage turbine performance characteristics were determined. Flow-field characteristics of the first stage turbine were predicted using a three-dimensional viscous flow code.
Descriptors : *SPACE SHUTTLES, *ROCKET ENGINES, *TURBOPUMPS, COMPUTER PROGRAMS, MATHEMATICAL MODELS, CONTROL, THROTTLING, PROBES, RATIOS, PERFORMANCE(ENGINEERING), NUMERICAL ANALYSIS, HIGH PRESSURE, TEST EQUIPMENT, LASERS, REGIONS, DISPLAY SYSTEMS, CODING, FLOW FIELDS, MODEL TESTS, PRESSURE, DATA ACQUISITION, INSTRUMENTATION, MAPS, TURBINES, MAPPING, VISION, VALVES, FUEL PUMPS, DOPPLER SYSTEMS, VISCOUS FLOW, EXITS, TEST FACILITIES, THREE DIMENSIONAL FLOW, COLD FLOW, ROTOR BLADES(TURBOMACHINERY).
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE