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Some Experiences in the Scaling of the NASA 8-Stage Transonic Axial Flow Compressor
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English
Abstract
An eight-stage transonic axial flow compressor was scaled to three-tenths its original size. The scaled compressor was built and tested as a separate component, and as a component of a gas turbine engine. This paper summarizes the work done on this compressor, including the aerodynamic design considerations and overall performance results.
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Topic
Citation
Wiggins, J. and Waltz, G., "Some Experiences in the Scaling of the NASA 8-Stage Transonic Axial Flow Compressor," SAE Technical Paper 720711, 1972, https://doi.org/10.4271/720711.Also In
References
- Geye Richard P. Budinger Ray E. Voit Charles H. “Investigation of a High-Pressure-Ratio-Eight-Stage Axial Flow Research Compressor with Two Transonic Inlet Stages. II-Preliminary Analysis of Overall Performance.” NASA RME53J06
- Mellor G. L. Strong R. E. “End-Wall Effects in Axial Compressors.” ASME Paper 67-FE-16
- Staff, Lewis Research Center “Aerodynamic Design of Axial Flow Compressors.” NASA SP-36
- Voit Charles H. “Investigation of a High-Pressure-Ratio Eight-Stage Axial-Flow Research Compressor with Two Transonic Inlet Stages. I-Aerodynamic Design.” NASA RME53124 1953