NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsPreliminary Results From a Heavily Instrumented Engine Ice Crystal Icing Test in a Ground Based Altitude Test FacilityPreliminary results from the heavily instrumented ALF502R-5 engine test conducted in the NASA Glenn Research Center Propulsion Systems Laboratory are discussed. The effects of ice crystal icing on a full scale engine is examined and documented. This same model engine, serial number LF01, was used during the inaugural icing test in the Propulsion Systems Laboratory facility. The uncommanded reduction of thrust (rollback) events experienced by this engine in flight were simulated in the facility. Limited instrumentation was used to detect icing on the LF01 engine. Metal temperatures on the exit guide vanes and outer shroud and the load measurement were the only indicators of ice formation. The current study features a similar engine, serial number LF11, which is instrumented to characterize the cloud entering the engine, detect/characterize ice accretion, and visualize the ice accretion in the region of interest. Data were acquired at key LF01 test points and additional points that explored: icing threshold regions, low altitude, high altitude, spinner heat effects, and the influence of varying the facility and engine parameters. For each condition of interest, data were obtained from some selected variations of ice particle median volumetric diameter, total water content, fan speed, and ambient temperature. For several cases the NASA in-house engine icing risk assessment code was used to find conditions that would lead to a rollback event. This study further helped NASA develop necessary icing diagnostic instrumentation, expand the capabilities of the Propulsion Systems Laboratory, and generate a dataset that will be used to develop and validate in-house icing prediction and risk mitigation computational tools. The ice accretion on the outer shroud region was acquired by internal video cameras. The heavily instrumented engine showed good repeatability of icing responses when compared to the key LF01 test points and during day-to-day operation. Other noticeable observations are presented.Document ID20160010560Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsFlegel, Ashlie B.*(NASA Glenn Research Center Cleveland, OH United States)*Oliver, Michael J.*(NASA Glenn Research Center Cleveland, OH United States)*Date AcquiredAugust 24, 2016Publication DateAugust 1, 2016Subject CategoryAircraft Design, Testing And PerformanceReport/Patent NumberE-19256NASA/TM-2016-219132GRC-E-DAA-TN33381Funding Number(s)WBS: WBS 081876.02.03.08.01.02Distribution LimitsPublicCopyrightWork of the US Gov. Public Use Permitted.KeywordsEnigine IcingTurbomachineryIce Crystal IcingAvailable DownloadsNameType20160010560.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsIDRelationTitle20170000236See AlsoPreliminary Results From a Heavily Instrumented Engine Ice Crystal Icing Test in a Ground Based Altitude Test Facility20170003992See AlsoPreliminary Results From a Heavily Instrumented Engine Ice Crystal Icing Test in a Ground Based Altitude Test Facilityvisibility_offNo Preview Available
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