NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsProgress of High Efficiency Centrifugal Compressor Simulations Using TURBOThree-dimensional, time-accurate, and phase-lagged computational fluid dynamics (CFD) simulations of the High Efficiency Centrifugal Compressor (HECC) stage were generated using the TURBO solver. Changes to the TURBO Parallel Version 4 source code were made in order to properly model the no-slip boundary condition along the spinning hub region for centrifugal impellers. A startup procedure was developed to generate a converged flow field in TURBO. This procedure initialized computations on a coarsened mesh generated by the Turbomachinery Gridding System (TGS) and relied on a method of systematically increasing wheel speed and backpressure. Baseline design-speed TURBO results generally overpredicted total pressure ratio, adiabatic efficiency, and the choking flow rate of the HECC stage as compared with the design-intent CFD results of Code Leo. Including diffuser fillet geometry in the TURBO computation resulted in a 0.6 percent reduction in the choking flow rate and led to a better match with design-intent CFD. Diffuser fillets reduced annulus cross-sectional area but also reduced corner separation, and thus blockage, in the diffuser passage. It was found that the TURBO computations are somewhat insensitive to inlet total pressure changing from the TURBO default inlet pressure of 14.7 pounds per square inch (101.35 kilopascals) down to 11.0  pounds per square inch (75.83 kilopascals), the inlet pressure of the component test. Off-design tip clearance was modeled in TURBO in two computations: one in which the blade tip geometry was trimmed by 12 mils (0.3048 millimeters), and another in which the hub flow path was moved to reflect a 12-mil axial shift in the impeller hub, creating a step at the hub. The one-dimensional results of these two computations indicate non-negligible differences between the two modeling approaches.Document ID20170002701Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsKulkarni, Sameer*(NASA Glenn Research Center Cleveland, OH United States)*Beach, Timothy A.*(Vantage Partners, LLC Cleveland, OH, United States)*Date AcquiredMarch 30, 2017Publication DateMarch 1, 2017Subject CategoryAircraft Propulsion And PowerFluid Mechanics And ThermodynamicsReport/Patent NumberGRC-E-DAA-TN31275NASA/TM-2017-219418E-19315Funding Number(s)WBS: WBS 664817.02.03.02.03.01CONTRACT_GRANT: NNC12BA01BDistribution LimitsPublicCopyrightPublic Use Permitted.Keywordsturbomachinerycomputational fluid dynamicscentrifugal compressorsAvailable DownloadsNameType20170002701.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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