Large-eddy simulations of supersonic axial turbines

• Grant number: 19/26196-5
• Support Opportunities: Scholarships in Brazil - Doctorate
• Start date: March 01, 2020
• End date: February 29, 2024
• Field of knowledge: Engineering - Aerospace Engineering - Aerodynamics
• Principal Investigator: William Roberto Wolf
• Grantee: Hugo Felippe da Silva Lui
• Host 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

Abstract

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)

Scientific publications

(References retrieved automatically from Web of Science and SciELO through information on FAPESP grants and their corresponding numbers as mentioned in the publications by the authors)

LUI, HUGO F. S.; RICCIARDI, TULIO R.; WOLF, WILLIAM R.; BRAUN, JAMES; RAHBARI, IMAN; PANIAGUA, GUILLERMO. Unsteadiness of shock-boundary layer interactions in a Mach 2.0 supersonic turbine cascade. PHYSICAL REVIEW FLUIDS, v. 7, n. 9, p. 31-pg., 2022-09-08. (19/26196-5, 13/08293-7, 21/06448-0)

Academic Publications

(References retrieved automatically from State of São Paulo Research Institutions)

LUI, Hugo Felippe da Silva. Investigação de interações choque-camada limite em uma turbina axial supersônica. 2024. Doctoral Thesis - Universidade Estadual de Campinas (UNICAMP). Faculdade de Engenharia Mecânica Campinas, SP.