Characterization of base bleed effects on subsonic trailing edge flows

Martínez-Cava Aguilar, Alejandro and Rodríguez Álvarez, Daniel and Valero Sánchez, Eusebio and Paniagua, Guillermo (2021). Characterization of base bleed effects on subsonic trailing edge flows. "Aerospace Science and Technology", v. 113 ; p. 106730. ISSN 1270-9638. https://doi.org/10.1016/j.ast.2021.106730.

Description

Title: Characterization of base bleed effects on subsonic trailing edge flows
Author/s:
  • Martínez-Cava Aguilar, Alejandro
  • Rodríguez Álvarez, Daniel
  • Valero Sánchez, Eusebio
  • Paniagua, Guillermo
Item Type: Article
Título de Revista/Publicación: Aerospace Science and Technology
Date: June 2021
ISSN: 1270-9638
Volume: 113
Subjects:
Freetext Keywords: Aerodynamics, Turbomachinery
Faculty: E.T.S. de Ingeniería Aeronáutica y del Espacio (UPM)
Department: Aeronaves y Vehículos Espaciales
UPM's Research Group: Métodos y Aplicaciones Numéricas a la Tecnología Aeroespacial
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

Trailing edge injection enables control of the detached and unsteady flow within the base region. The interaction of the jet with the base region alters the flow topology causing pressure bifurcations at the trailing edge that affect the aerodynamic performance of the system and modify the vortex patterns downstream the body. The purpose of this work is to fully characterize the physical effects related to the use of base bleed on the trailing edge of an airfoil at subsonic conditions. Defining a non-dimensional base bleed rate , a wide range from to is applied to a simplified model of a turbine blade. The influence of the trailing edge geometry shape is also evaluated, showing that rounded geometries have the potential to minimize the undesirable effects of the injection. Vortex shedding is neutralized when the (non-dimensional) ejected mass flow exceeds the value of and for straight and rounded geometries, respectively. Additionally, neutralization of the shedding also occurs for relatively low base bleed rates, often accompanied by the onset of a non-symmetrical configuration at the trailing edge. This work has particular relevance in aerothermal gas turbine design, where coolant flow may be ejected at the trailing edge to ensure adequate thermal protection of the airfoils.

Funding Projects

TypeCodeAcronymLeaderTitle
Government of SpainRTI2018-097075-B-I00SIMOPAIREusebio ValeroSimulaciones de Alta Precisión y Modelización para Diseño Optimo Aeronautico
Madrid Regional GovernmentAPOYO-JOVENES-WYOWRI-135-DZBLJUUnspecifiedUnspecifiedUnspecified

More information

Item ID: 66825
DC Identifier: https://oa.upm.es/66825/
OAI Identifier: oai:oa.upm.es:66825
DOI: 10.1016/j.ast.2021.106730
Official URL: https://www.sciencedirect.com/science/article/pii/S1270963821002406?via%3Dihub
Deposited by: Sr Alejandro Martinez-Cava
Deposited on: 22 Apr 2021 13:50
Last Modified: 01 Jun 2022 22:30
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