Open AccessFlow Integrating Section for a Gas Turbine Engine in Which Turbine Blades are Cooled by Full Compressor Flow
Author(s) -
W. G. Steward
Publication year - 1999
Language(s) - English
Resource type - Reports
DOI - 10.2172/764563
Subject(s) - diffuser (optics) , gas compressor , axial compressor , turbine blade , mechanical engineering , flow (mathematics) , inlet , turbine , section (typography) , gas turbines , engineering , mechanics , marine engineering , computer science , physics , operating system , light source , optics
Routing of full compressor flow through hollow turbine blades achieves unusually effective blade cooling and allows a significant increase in turbine inlet gas temperature and, hence, engine efficiency. The invention, ''flow integrating section'' alleviates the turbine dissipation of kinetic energy of air jets leaving the hollow blades as they enter the compressor diffuser