Flow visualization in a linear turbine cascade of high performance turbine blades

Hai Ping Wang, Steven J. Olson, Richard J. Goldstein, Ernst R G Eckert

Research output: Chapter in Book/Report/Conference proceedingConference contribution

13 Scopus citations

Abstract

Multiple smoke wires are used to investigate the secondary flow near the endwall of a plane cascade with blade shapes as used in high performance turbine stages. The wires are positioned parallel to the endwall and ahead of the cascade, within and outside the endwall boundary layer. The traces of the smoke generated by the wires are visualized within a laser light sheet arranged at various crosssections around the cascade. During the experiment, a periodically fluctuating horseshoe vortex system of varying number of vortices is observed near the leading edge of the cascade. A series of photographs and video tapes was taken in the cascade to trace these vortices. The development and evolution of the horseshoe vortex and the passage vortex are clearly resolved in the photographs. The interaction between the suction side leg of the horseshoe vortex and the passage vortex is also observed in the experiment. A vortex induced by the passage vortex, starting about 1/4 of the curvilinear distance along the blade on the suction surface, is clearly shown in the photographs. This vortex stays close to the suction surface and above the passage vortex in the laminar flow region on the blade. From this flow visualization, a model describing the secondary flows in a cascade is proposed and compared with previous published models. Some naphthalene mass transfer results from a blade near an endwall are cited and compared with the current model. The flows inferred from both techniques agree well with each other.

Original languageEnglish (US)
Title of host publicationHeat Transfer; Electric Power; Industrial and Cogeneration
Editors Anon
PublisherAmerican Society of Mechanical Engineers (ASME)
Volume4
ISBN (Electronic)9780791878811
DOIs
StatePublished - 1995
EventASME 1995 International Gas Turbine and Aeroengine Congress and Exposition, GT 1995 - Houston, United States
Duration: Jun 5 1995Jun 8 1995

Other

OtherASME 1995 International Gas Turbine and Aeroengine Congress and Exposition, GT 1995
Country/TerritoryUnited States
CityHouston
Period6/5/956/8/95

Fingerprint

Dive into the research topics of 'Flow visualization in a linear turbine cascade of high performance turbine blades'. Together they form a unique fingerprint.

Cite this