NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsThree-Dimensional Flow Field Measurements in a Transonic Turbine CascadeThree-dimensional flow field measurements are presented for a large scale transonic turbine blade cascade. Flow field total pressures and pitch and yaw flow angles were measured at an inlet Reynolds number of 1.0 x 10(exp 6) and at an isentropic exit Mach number of 1.3 in a low turbulence environment. Flow field data was obtained on five pitchwise/spanwise measurement planes, two upstream and three downstream of the cascade, each covering three blade pitches. Three-hole boundary layer probes and five-hole pitch/yaw probes were used to obtain data at over 1200 locations in each of the measurement planes. Blade and endwall static pressures were also measured at an inlet Reynolds number of 0.5 x 10(exp 6) and at an isentropic exit Mach number of 1.0. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet and because of the high degree of flow turning. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification.Document ID19970009632Acquisition SourceLegacy CDMSDocument TypeConference PaperAuthorsGiel, P. W.*(NYMA, Inc. Brook Park, OH United States)*Thurman, D. R.*(Army Research Lab. Cleveland, OH United States)*Lopez, I.*(Army Research Lab. Cleveland, OH United States)*Boyle, R. J.*(NASA Lewis Research Center Cleveland, OH United States)*VanFossen, G. J.*(NASA Lewis Research Center Cleveland, OH United States)*Jett, T. A.*(NASA Lewis Research Center Cleveland, OH United States)*Camperchioli, W. P.*(NASA Lewis Research Center Cleveland, OH United States)*La, H.*(NASA Lewis Research Center Cleveland, OH United States)*Date AcquiredSeptember 6, 2013Publication DateDecember 1, 1996Subject CategoryAircraft Propulsion And PowerReport/Patent NumberE-10584NASA-TM-107388NAS 1.15:107388ARL-TR-1252Meeting InformationMeeting: Gas Turbine and Aeroengine CongressLocation: BirminghamCountry: United KingdomStart Date: June 10, 1996End Date: June 13, 1996Sponsors:American Society of Mechanical EngineersAccession Number97N15028Funding Number(s)CONTRACT_GRANT: NAS3-27186PROJECT: RTOP 523-26-13Distribution LimitsPublicCopyrightWork of the US Gov. Public Use Permitted.Available DownloadsNameType19970009632.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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