Accession Number : AD0886888
Title : Exploratory Research into Combustor Inlet Distortion Tolerance. Volume I. Compressor Tests.
Descriptive Note : Final technical rept. 2 Jan 69-31 Mar 71 on Task A,
Corporate Author : GENERAL MOTORS CORP INDIANAPOLIS IN ALLISON GAS TURBINE DIV
Personal Author(s) : Korn, James A. ; Garzon, Julian R.
Report Date : JUL 1971
Pagination or Media Count : 152
Abstract : The fan-low compressor system of an aircraft turbofan engine was tested with steady and discrete frequency total pressure distortion imposed over a 90-degree sector of inlet annulus. Steady and dynamic total pressure instrumentation was installed at the fan inlet and discharge and at the low compressor discharge. The stability of the fan hubs and the low compressor was tested for steady and discrete frequency distortion. Attenuation through the fan blading was examined through the tip sections. Transport times were identified through the low compressor stages. Transport time through the fan blading was observed. (Author)
Descriptors : (*AXIAL FLOW COMPRESSORS, PERFORMANCE(ENGINEERING)), TURBOFAN ENGINES, AIRCRAFT ENGINES, COMPRESSOR BLADES, JET ENGINE INLETS, ATTENUATION, TEST METHODS, STATISTICAL DATA, TEST FACILITIES, FLOW FIELDS, TOLERANCES(MECHANICS), PRESSURE.
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE