Exploratory Research into Combustor Inlet Distortion Tolerance. Volume I. Compressor Tests.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1971
- Accession Number
- AD0886888
Entities
People
- James A. Korn
- Julian R. Garzon
Organizations
- General Motors