Fluid flow and heat transfer in transonic turbine cascades

Simple item page
dc.contributor.authorJanakiraman, S. V.en
dc.contributor.committeechairMoore, Johnen
dc.contributor.committeememberMoses, Hal L.en
dc.contributor.committeememberJayaram, Sankaren
dc.contributor.departmentMechanical Engineeringen
dc.date.accessioned2014-03-14T21:37:59Zen
dc.date.adate2009-06-11en
dc.date.available2014-03-14T21:37:59Zen
dc.date.issued1993-05-05en
dc.date.rdate2009-06-11en
dc.date.sdate2009-06-11en
dc.description.abstractThe aerodynamic and thermodynamic performance of an aircraft gas turbine directly affects the fuel consumption of the engine and the life of the turbine components. Hence, it is important to be able to understand and predict the fluid flow and heat transfer in turbine blades to enable the modifications and improvements in the design process. The use of numerical experiments for the above purposes is becoming increasingly common. The present thesis is involved with the development of a flow solver for turbine flow and heat transfer computations. A 3-D Navier-Stokes code, the Moore Elliptic Flow Program (MEFP) is used to calculate steady flow and heat transfer in turbine rotor cascades. Successful calculations were performed on two different rotor profiles using a one-equation q-L transitional turbulence model. A series of programs was developed for the post-processing of the output from the flow solver. The calculations revealed details of the flow including boundary layer development, trailing edge shocks, flow transition and stagnation and peak heat transfer rates. The calculated pressure distributions, losses, transition ranges, boundary layer parameters and peak heat transfer rates to the blade are compared with the available experimental data. The comparisons indicate that the q-L transitional turbulence model is successful in predicting flows in transonic turbine blade rows. The results also indicate that the calculated loss levels are independent of the gridding used while the heat transfer rate predictions improve with finer grids.en
dc.description.degreeMaster of Scienceen
dc.format.extentxiv, 122 leavesen
dc.format.mediumBTDen
dc.format.mimetypeapplication/pdfen
dc.identifier.otheretd-06112009-063614en
dc.identifier.sourceurlhttp://scholar.lib.vt.edu/theses/available/etd-06112009-063614/en
dc.identifier.urihttp://hdl.handle.net/10919/43173en
dc.language.isoenen
dc.publisherVirginia Techen
dc.relation.haspartLD5655.V855_1993.J363.pdfen
dc.relation.isformatofOCLC# 28726180en
dc.rightsIn Copyrighten
dc.rights.urihttp://rightsstatements.org/vocab/InC/1.0/en
dc.subject.lccLD5655.V855 1993.J363en
dc.subject.lcshAerodynamics, Transonicen
dc.subject.lcshAircraft gas-turbines -- Bladesen
dc.subject.lcshAircraft gas-turbines -- Dynamicsen
dc.titleFluid flow and heat transfer in transonic turbine cascadesen
dc.typeThesisen
dc.type.dcmitypeTexten
thesis.degree.disciplineMechanical Engineeringen
thesis.degree.grantorVirginia Polytechnic Institute and State Universityen
thesis.degree.levelmastersen
thesis.degree.nameMaster of Scienceen

Files

Original bundle
Now showing 1 - 1 of 1
Thumbnail Image
Name:
LD5655.V855_1993.J363.pdf
Size:
2.58 MB
Format:
Adobe Portable Document Format
Download

Collections

Masters Theses