Navier-stokes analysis of unsteady transonic flows through gas turbine cascadeswith and without coolant ejection

T. Tanuma, N. Shibukawa, S. Yamamoto

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

An implicit time-marching higher-order accurate finitedifference method for solving the two-dimensional cornpressible Navier-Stokes equations was applied to the numerical analyses of steady and unsteady, subsonic and transonic viscous flows through gas turbine cascades with trailing edge coolant ejection. Annular cascade tests were carried out to verify the accuracy of the present analysis. The unsteady aerodynamic mechanisms associated with the interaction between the trailing edge vortices and shock waves and the effect of coolant ejection were evaluated with the present analysis.

Original languageEnglish
Title of host publicationAircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791878682
DOIs
Publication statusPublished - 1997
EventASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997 - Orlando, United States
Duration: 1997 Jun 21997 Jun 5

Publication series

NameProceedings of the ASME Turbo Expo
Volume1

Conference

ConferenceASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997
Country/TerritoryUnited States
CityOrlando
Period97/6/297/6/5

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