Accession Number : AD0503303
Title : Propulsion System Flow Stability Program (Dynamic). Part XI. Lift Engine Compressor Tests and Response to Steady-State Distortion.
Descriptive Note : Final technical rept. 20 Jun 67-30 Sep 68 on Phase 1,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV
Personal Author(s) : Korn,James A.
Report Date : DEC 1968
Pagination or Media Count : 134
Abstract : A four-stage lift engine type compressor was tested over its complete operating range with and without combined circumferential and radial distortion of inlet total pressure. The compressor rig was equipped with interstage instrumentation at each rotor exit and the test procedure was such that a circumferential and radial survey of interstage data were obtained at each test point. Analysis of the data showed that interstage flow mixing and distortion attenuation was related to the slope of the characteristics of the individual stages. Detailed observations of the interstage data are presented which provide considerable insight into distorted compressor operation. A simple analytical procedure to describe compressor events is proposed. Recommendations are made for additional analytical and empirical investigations to corroborate the analysis and conclusions. (Author)
Descriptors : (*TURBOJET ENGINES, *AXIAL FLOW COMPRESSORS), (*TURBOJET INLETS, DISTORTION), FLOW FIELDS, PRESSURE, JET MIXING FLOW, ENGINE SURGE, ATTENUATION, COMPUTER PROGRAMS, PREDICTIONS, STALLING, COMPRESSOR ROTORS, TEST FACILITIES, INSTRUMENTATION, COMPRESSOR STATORS, TRANSONIC CHARACTERISTICS, CALIBRATION
Subject Categories : Hydraulic and Pneumatic Equipment
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE