题 目: Summary of DIME Turbomachinery Laboratory Research;
Boundary layer development and loss production in adverse pressure gradient flows on axial Compressor and Turbine Profiles
地 点：机械与动力工程学院 F301会议室
Biography: Porf. Pietro Zunino is the department head of Mechanical, Energy, Management and Transportation Engineering (DIME) in Genova University (Italy) since 2012. He has devoted himself to flow analyses and experimental techniques for flow measurements in turbo machines (HW, LDA, PDA, and PIV), and has published more than 150 international scientific papers for Power Generation and Aeronautical Propulsion. He is the session chairman of many international scientific conferences, evaluator for the European Commission VI and VII Framework- aeronautical and space, and scientific responsible of European Commission Research Projects on Gas Turbines. He is the manager for industrial research contracts on turbomachinery, and Gas Turbine Design Specialists team leader.
Abstract：Research activities on aerothermodynamics and combustion of gas turbines, developed at the Laboratory of Turbomachinery of the Department of Mechanical, Energy, Management and Transportation Engineering of University of Genova are summarized, then more details are given on the recent systematic experimental study concerning the boundary layer development and loss production in adverse pressure gradient flows of axial compressor and turbine profiles.
Profile losses in axial compressors and turbines mainly depend on the boundary layer development on the suction side of the blade and vane profiles. For compressors and high lift turbine profiles, adverse pressure gradient conditions play the main role in the boundary layer development and the occurrence of the related phenomena of laminar turbulent transition and possible separation. Indeed, with the most severe adverse pressure gradients, depending on Re number and turbulent intensity conditions, laminar separation bubble may not reattach or even turbulent boundary layer separation may occur. Furthermore wake induced unsteady conditions and free stream turbulent intensity have a significant additional influence on the boundary layer development on turbomachinery components. The boundary layer developing under adverse pressure gradient conditions, simulating the operation of axial compressors and turbines, has been studied by means of complementary measurement techniques at the Aerodynamics and Turbomachinery Laboratory of the University of Genova.