Numerical Investigation of Fluidic Control on Supersonic Jet of a Gas Turbine Engine
2012 (English)In: 20th International Shock Interaction Symposium (ISIS 20) / [ed] Nicholas Apazidis, ISIS, KTH , 2012, 161-164 p.Conference paper (Refereed)
Use of fluidics on the supersonic flow exhausting a gas turbine engine is investigated. The purpose is to control the shock-waves i.e., their location and strength by using injection tubes disposed on the circumference of the nozzle. A parametric study has been performed for quantifying the effect on shock patterns of different parameters such the nozzle pressure ratio, the injection pressure ratio, location and inclination of the tubes. Different cases have been screened, using the steady-state Reynolds-averaged Navier-Stokes formulation. For the Baseline case (without injection) at the design conditions, a grid convergence study was performed and the results were compared with experimental Particle Imaging Velocimetry data. An overall fair agreement was found. In contrast with the Baseline, significant changes in shear-layer shape, mixing, and turbulence intensity are associated with vortical structures generated due to fluidic injection. With an appropriate choice of injection parameters the ability to shift or move shocks and reduce shock strength is proven. Improvement in terms of better mixing, better thrust performance, and the possibility of reducing acoustic radiation can be shown for some of the cases.
Place, publisher, year, edition, pages
ISIS, KTH , 2012. 161-164 p.
Fluid Mechanics and Acoustics
Research subject Aerospace Engineering
IdentifiersURN: urn:nbn:se:kth:diva-148036OAI: oai:DiVA.org:kth-148036DiVA: diva2:734397
20th International Shock Interaction Symposium (ISIS 20),Stockholm, August 20 - 24, 2012
QC 201408152014-07-172014-07-172015-03-05Bibliographically approved