Memorias de investigación
Research Publications in journals:
Pressure Bifurcation Phenomenon on Supersonic Blowing Trailing Edges
Year:2019

Research Areas
  • Hidrodynamics stability,
  • Turbomachinery,
  • Computacional fluid dynamics,
  • Aerodynamics

Information
Abstract
Turbine blades operating in transonic-supersonic regime develop a complex shock wave system at the trailing edge, a phenomenon that leads to unfavorable pressure perturbations downstream and can interact with other turbine stages. Understanding the fluid behavior of the area adjacent to the trailing edge is essential in order to determine the parameters that have influence on these pressure fluctuations. Colder flow, bled from the high-pressure compressor, is often purged at the trailing edge to cool the thin blade edges, affecting the flow behavior and modulating the intensity and angle of the shock waves system. However, this purge flow can sometimes generate non-symmetrical configurations due to a pressure difference that is provoked by the injected flow. In this work, a combination of RANS simulations and global stability analysis is employed to explain the physical reasons of this flow bifurcation. Analyzing the features that naturally appear in the flow and become dominant for some value of the parameters involved in the problem, an anti-symmetrical global mode, related to the sudden geometrical expansion of the trailing edge slot, is identified as the main mechanism that forces the changes in the flow topology.
International
Si
JCR
Si
Title
Aiaa Journal
ISBN
0001-1452
Impact factor JCR
1,556
Impact info
Datos JCR del año 2017
Volume
57
10.2514/1.J057056
Journal number
1
From page
153
To page
157
Month
SIN MES
Ranking
Participants

Research Group, Departaments and Institutes related
  • Creador: Grupo de Investigación: Métodos y Aplicaciones Numéricas a la Tecnología Aeroespacial
  • Departamento: Matemática Aplicada a la Ingeniería Aeroespacial