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dc.contributor.authorCebeci, T.
dc.contributor.authorSimoneau, R.J.
dc.contributor.authorKrainer, A.
dc.contributor.authorPlatzer, M.F.
dc.dateJan 01, 1987en_US
dc.date.accessioned2018-09-27T00:06:54Z
dc.date.available2018-09-27T00:06:54Z
dc.date.issued1987-01
dc.identifier.citationStructural Integrity and Durability of Reusable Space Propulsion Systems; p. p 21-27en_US
dc.identifier.other19870013336
dc.identifier.urihttp://hdl.handle.net/10945/60128
dc.identifier.urihttps://ntrs.nasa.gov/search.jsp?R=19870013336
dc.descriptionApproved for public release, distribution unlimiteden_US
dc.description.abstractProgress toward developing a general method for predicting unsteady heat transfer on turbine blades subject to blade-passing frequencies and Reynolds numbers relevant to the Space Shuttle Main Engine (SSME) is discussed. The method employs an invisid/viscous interactive procedure which has been tested extensively for steady subsonic and transonic external airfoil problems. One such example is shown. The agreement with experimental data and with Navier-Stokes calculations yields confidence in the method. The technique is extended to account for wake generated unsteadiness. The flow reversals around the stagnation point caused by the nonuniform onset velocity are accounted for by using the Characteristic Box scheme developed by Cebeci and Stewartson. The coupling between the inviscid and viscous methods is achieved by using a special procedure, which, with a novel inverse finite-difference boundary-layer method, allows the calculations to be performed for a wide range of flow conditions, including separation. Preliminary results are presented for the stagnation region of turbine blades for both laminar and turbulent flows. A laminar model problem corresponding to a flow on a circular cylinder which experiences the periodic passing of wakes from turbine blades is presented to demonstrate the ability of the method to calculate flow reversals around the stagnation region.en_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titleProgress in the prediction of unsteady heat transfer on turbines bladesen_US
dc.typeConference Paper
dc.contributor.corporateGlenn Research Center
dc.subject.authorCIRCULAR CYLINDERSen_US
dc.subject.authorCOMPUTATIONAL FLUID DYNAMICSen_US
dc.subject.authorHEAT TRANSFERen_US
dc.subject.authorLAMINAR FLOWen_US
dc.subject.authorPREDICTIONSen_US
dc.subject.authorSTAGNATION POINTen_US
dc.subject.authorTURBINE BLADESen_US
dc.subject.authorTURBULENT FLOWen_US
dc.subject.authorBOUNDARY LAYER SEPARATIONen_US
dc.subject.authorFINITE DIFFERENCE THEORYen_US
dc.subject.authorFREQUENCIESen_US
dc.subject.authorNAVIER-STOKES EQUATIONen_US
dc.subject.authorREYNOLDS NUMBERen_US


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