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Large-eddy simulations of supersonic axial turbines

Grant number: 19/26196-5
Support type:Scholarships in Brazil - Doctorate
Effective date (Start): March 01, 2020
Field of knowledge:Engineering - Aerospace Engineering - Aerodynamics
Principal researcher:William Roberto Wolf
Grantee:Hugo Felippe da Silva Lui
Home Institution: Faculdade de Engenharia Mecânica (FEM). Universidade Estadual de Campinas (UNICAMP). Campinas , SP, Brazil
Associated research grant:13/08293-7 - CCES - Center for Computational Engineering and Sciences, AP.CEPID
Associated scholarship(s):21/14199-0 - Investigation of shock-boundary layer interactions in supersonic axial turbines, BE.EP.DR


Rotating Detonation Combustors (RDCs) offer a potential cycle efficiency leap for gas turbine engines. This promising detonation combustor could potentially deliver a thermal performance increase of 20% compared to the current state-of-the-art engines. Different from conventional gas turbine combustors, the configuration of RDCs results in supersonic flows at the combustor exit. Traditional axial turbine designs exhibit unacceptable aerodynamic performance when exposed to supersonic inlet conditions due to the generation of a normal shock wave at the inlet. Recently, new designs have been developed in order to ingest the normal shock wave, thus allowing the turbine passage to operate in the supersonic regime. Axial turbines adequate for supersonic flows have been attracting the interest of engineers and scientists due to its high specific power, which may allow potential stage reduction in gas turbine engines. Supersonic axial turbines find application in propulsion and power generation systems. However, the efficient operation of these pioneering fluid machines is a challenge due to the complex physical mechanisms involved in supersonic flows such as shock wave reflections, shock wave/boundary layer interactions and the starting issues of such flows. In this work, a wall-resolving Large Eddy Simulation (LES) procedure will be adopted for studying the effects of different inlet flow conditions and leading edge shapes on the loss mechanisms of supersonic axial turbines. In order to obtain accurate solutions, a high order overset grid capability will be employed in the simulations. The fundamental purpose of the present study is to gain a better understanding of physical processes related to supersonic flows over turbine cascades. According to recent literature, high-fidelity simulations of supersonic turbines are not available and we would like to pioneer such studies. (AU)

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