Numerical analysis of film cooling

dc.contributor	Graduate Program in Mechanical Engineering.
dc.contributor.advisor	Mengütürk, Muhsin.
dc.contributor.author	Taştekin, Ömer.
dc.date.accessioned	2023-03-16T11:17:20Z
dc.date.available	2023-03-16T11:17:20Z
dc.date.issued	1983.
dc.identifier.other	ME 1983 T18
dc.identifier.uri	http://digitalarchive.boun.edu.tr/handle/123456789/15131
dc.description.abstract	A numurical model is developed to investigate film cooling in compressible laminar boundary layer flows. This model is applied to the first stagi stator blade of a transonic gas turbine. As a prelude study, film cooling for incompressible flow over a flat plate is also included. Film cooling effectiveness ts reported for a variety of injection configurations so that the effects of .coolant mass flow, rate, injection angle, and slot width can be investigated. For the coolant mass flow rates considered, normal injection provides better cooling than inclined injection. However, normal injection brings about greater boundary layer thickness and may reduce aerodynamic performance. Use of multiple slots provides higher and more uniform effectiveness for the s me coolant mass flow rate.
dc.format.extent	30 cm.
dc.publisher	Thesis (M.S.) - Bogazici University. Institute for Graduate Studies in Science and Engineering, 1983.
dc.relation	Includes appendices.
dc.relation	Includes appendices.
dc.subject.lcsh	Boundary layer.
dc.subject.lcsh	Laminar flow.
dc.title	Numerical analysis of film cooling
dc.format.pages	xi, 73 leaves;