Investigation of low-pressure turbine separation control

A. Gross, Hermann F Fasel

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

10 Scopus citations

Abstract

Low-pressure turbines are a common element of many modern jet engines. Flow separation from the suction side of the constituent blades at low Reynolds number conditions can noticeably deteriorate overall engine performance. Two separation control strategies for an aggressive low-pressure turbine blade that was designed for an integrated flow control were investigated numerically using a hybrid turbulence modeling approach: Pulsed vortex generator jets are shown to result in an earlier transitioning of the flow and successful separation control. An even more efficient separation control can be accomplished by harmonic blowing through a slot. The astounding effectiveness of the latter control scheme is attributed to the suppression of three-dimensional structures. Instead, the flow is dominated by strong spanwise coherent structures that very effectively reduce separation.

Original languageEnglish (US)
Title of host publicationCollection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
Pages6300-6314
Number of pages15
Volume9
Publication statusPublished - 2007
Event45th AIAA Aerospace Sciences Meeting 2007 - Reno, NV, United States
Duration: Jan 8 2007Jan 11 2007

Other

Other45th AIAA Aerospace Sciences Meeting 2007
CountryUnited States
CityReno, NV
Period1/8/071/11/07

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ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Gross, A., & Fasel, H. F. (2007). Investigation of low-pressure turbine separation control. In Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting (Vol. 9, pp. 6300-6314)