Experimental and Computational Analysis of Advanced Casing Treatments in a Transonic Compressor
Abstract
Turbo-fan engines seek to achieve the highest compression ratios possible with the minimum number of parts by driving compressor stages to the extremes of their operating limits, which can risk compressor stall. This study expands on previous work by combining experimental and computational methods to evaluate the effectiveness of advanced transonic compressor casing treatments at increasing stall margin while minimizing losses. The NPS Turbopropulsion Lab Transonic Compressor Rig was used to characterize the performance of an advanced transonic compressor in the stage and stage-and-a-half configurations; additionally, inlet guide vanes were installed and evaluated. After characterization of the base performance, s-shaped axial endwall grooves were added to improve stall margin of the compressor stage.. Experimental results proved the casing treatments were successful only in the subsonic regime. Stall margin increases of at least 286 percent were seen in low speed tests with 117 percent observed in high speed operation. Computational analysis simulated advanced casing treatments and effects of inlet whirl and was correlated to experimental data to shed light on the recirculation mechanisms active in casing treatments. The simulations provided insight for further development of novel self-recirculating endwall treatments and associated technologies.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2022
- Accession Number
- AD1184958
Entities
People
- Matthew B. Jones
Organizations
- Naval Postgraduate School