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ISSN Online: 2377-424X

ISBN Print: 978-1-56700-474-8

ISBN Online: 978-1-56700-473-1

International Heat Transfer Conference 16
August, 10-15, 2018, Beijing, China

TURBINE BLADE COOLING AT BUAA

Get access (open in a dialog) DOI: 10.1615/IHTC16.kn.000027
467 pages

Résumé

Gas turbine is one of the most important power source for military plane, aircraft, airplanes, warships, and so on. With the development of gas turbine, the turbine inlet temperature has been increased significantly, which is far beyond the allowable metal temperatures. In order to ensure the operation of turbine blades safely, turbine blade cooling technology must be development. With the increase of turbine inlet temperature, turbine blade cooling technology facing serious challenges. Beihang (BUAA) starts to investigate the turbine blade cooling technology since 1990's. For turbine blade cooling, it contains internal cooling and film cooling. We investigated the internal cooling from three aspects: pin-fin cooling in trailing edge, ribs cooling in the mid-zone, and impingement cooling in leading edge. We developed three different rotating rigs with advanced measurement technology to carry out the experimental investigations at rotating conditions. For film cooling, we developed a 1.5 stage turbine blade rotating rig to investigate the film cooling at rotating conditions. Now days, we are carrying out a investigation on the boundary layer flow at rotating conditions, hoping to improve the simulation accuracy of flow and heat transfer at rotating conditions. We measured the boundary layer flow using hot-wire, and developed a rotating correction function to replace the standard log law, which has been used hundreds of years. We also measured the thermal boundary flow, and obtained the turbulent Prandtl number (Prt) at rotating conditions. Using these rotating correction functions, the accuracy of the simulation has been improved.