Observatorio de I+D+i UPM

Descripción
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.
Internacional	Si
JCR del ISI	Si
Título de la revista	Aiaa Journal
ISSN	0001-1452
Factor de impacto JCR	1,556
Información de impacto	Datos JCR del año 2017
Volumen	57
DOI	10.2514/1.J057056
Número de revista	1
Desde la página	153
Hasta la página	157
Mes	SIN MES
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Esta actividad pertenece a memorias de investigación

• Autor: Alejandro Martinez-Cava Aguilar (UPM)
• Autor: Yinzhu Wang . (UPM)
• Autor: Javier de Vicente Buendia (UPM)
• Autor: Eusebio Valero Sanchez (UPM)

• Creador: Grupo de Investigación: Métodos y Aplicaciones Numéricas a la Tecnología Aeroespacial
• Departamento: Matemática Aplicada a la Ingeniería Aeroespacial