Three-dimensional boundary layer in a turbine blade passage

Research output: Contribution to journalArticlepeer-review

3 Scopus citations

Abstract

The boundary layer on the end wall 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 end wall 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 Reynolds-Averaged Navier-Stokes models are compared to the measurements: The Shear Stress Transport k - ω model using the isotropic eddy viscosity assumption and a Reynolds stress model that 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 three-dimensional boundary layer at the passage exit. Measurements at the passage exit indicate a very thin boundary layer with laminarlike qualities. Because of the boundary-layer complexity, end wall heat transfer is not well predicted toward the pressure side and the exit of the blade passage.

Original languageEnglish (US)
Pages (from-to)954-963
Number of pages10
JournalJournal of Propulsion and Power
Volume33
Issue number4
DOIs
StatePublished - 2017

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

Fingerprint Dive into the research topics of 'Three-dimensional boundary layer in a turbine blade passage'. Together they form a unique fingerprint.

Cite this