Numerical investigation of low-pressure turbine blade separation control

D. Postl, A. Gross, H. F. Fasel

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

6 Scopus citations

Abstract

Separation control mechanisms in low-pressure turbine (LPT) applications are investigated numerically. Two-dimensional simulations of boundary layer separation on the suction side of a turbine blade in a linear cascade are presented and compared to experimental data. Active flow control by means of pulsed blowing is employed and its impact on the separation behavior is discussed. Fundamental separation control mechanisms associated with steady and pulsed vortex generator jets (VGJs) are investigated by direct numerical simulations of a separating boundary layer under conditions comparable to those in low Reynolds number LPT applications. The vortex generator jets are employed in two configurations, vertical as well as angled with respect to the freestream direction. Our results confirm experimental findings that pulsed jet blowing is more effective than steady jet blowing. In addition, pulsed VGJs that are injected vertically are shown to achieve the greatest reduction in the extent of boundary layer separation.

Original languageEnglish (US)
Title of host publication41st Aerospace Sciences Meeting and Exhibit
StatePublished - Dec 1 2003
Event41st Aerospace Sciences Meeting and Exhibit 2003 - Reno, NV, United States
Duration: Jan 6 2003Jan 9 2003

Publication series

Name41st Aerospace Sciences Meeting and Exhibit

Other

Other41st Aerospace Sciences Meeting and Exhibit 2003
CountryUnited States
CityReno, NV
Period1/6/031/9/03

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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    Postl, D., Gross, A., & Fasel, H. F. (2003). Numerical investigation of low-pressure turbine blade separation control. In 41st Aerospace Sciences Meeting and Exhibit (41st Aerospace Sciences Meeting and Exhibit).