Measurements and predictions of the three-dimensional boundary layer in a turbine blade passage

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

Abstract

The boundary layer on the endwall of a turbine blade cascade is subject to cross-stream pressure gradients in the blade passage, which generate a cross-stream velocity component to make it three-dimensional. This distorts the turbulence relative to a two-dimensional boundary layer, and impacts the endwall heat transfer. This study presents measurements of the three-dimensional boundary layer in a turbine cascade obtained with a laser Doppler velocimeter. In addition, two types of RANS models are compared to the measurements: the SST k-ω model using the isotropic eddy viscosity assumption, and a Reynolds stress model which allows for anisotropy of the Reynolds stress. Neither model fully captures the complexity of the three-dimensional boundary layer in a turbine blade passage, particularly for turbulence associated with the cross-stream flow and for the highly accelerated 3D boundary layer at the passage exit.

Original languageEnglish (US)
Title of host publication54th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103933
StatePublished - Jan 1 2016
Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
Duration: Jan 4 2016Jan 8 2016

Publication series

Name54th AIAA Aerospace Sciences Meeting

Other

Other54th AIAA Aerospace Sciences Meeting, 2016
CountryUnited States
CitySan Diego
Period1/4/161/8/16

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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  • Cite this

    Lynch, S. (2016). Measurements and predictions of the three-dimensional boundary layer in a turbine blade passage. In 54th AIAA Aerospace Sciences Meeting (54th AIAA Aerospace Sciences Meeting). American Institute of Aeronautics and Astronautics Inc, AIAA.