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dc.contributor.advisorWright, Lesley Mae.
dc.creatorBonjonia, Berkley William, 1993-
dc.date.accessioned2018-05-30T13:29:47Z
dc.date.available2018-05-30T13:29:47Z
dc.date.created2018-05
dc.date.issued2018-01-05
dc.date.submittedMay 2018
dc.identifier.urihttp://hdl.handle.net/2104/10370
dc.description.abstractThe gas turbine engine operates at temperatures that far exceed the melting point of the metals from which they are made. Cooling air from the high pressure compressor must be used to cool the components in the hot sections of the turbine engines. Coolant must be used as effectively as possible in order to increase engine efficiency. The Pressure Sensitive Paint technique (PSP) is used to evaluate the effects of both compound angles and advanced shapes on the film cooling effectiveness. Most current film cooling geometries are orientated streamwise, with mainstream flow, and the addition of the compound angle has shown to both positive and negative effects on cooling effectiveness. These changes are seen based on the type of inlet, cooling geometry, and expansion of the outlet geometry onto the surface.
dc.format.mimetypeapplication/pdf
dc.language.isoen
dc.subjectFilm cooling.
dc.titleEffect of inlet hole geometry on surface film cooling effectiveness from compound angle, shaped holes.
dc.typeThesis
dc.rights.accessrightsNo access - Contact librarywebmaster@baylor.edu
dc.type.materialtext
thesis.degree.nameM.S.M.E.
thesis.degree.departmentBaylor University. Dept. of Mechanical Engineering.
thesis.degree.disciplineMechanical Engineering
thesis.degree.grantorBaylor University
thesis.degree.levelMasters
dc.date.updated2018-05-30T13:29:47Z
local.embargo.lift2023-05-01
local.embargo.terms2023-05-01


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