![]() ![]() Feng, Design and numerical analysis of a new type of pre-swirl nozzle, Proceedings of the ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. Kim, Pre-swirl system design including inlet duct shape by using CFD analysis, Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Cookie swirl c ph free#Nishimura, Measurement and analysis of an efficient turbine rotor pump work reduction system incorporating pre-swirl nozzles and a free vortex pressure augmentation chamber, ASME Turbo Expo, Vienna, Austria (2004) GT-2004–53090. Morris, High pressure turbine low radius radial TOBI discharge coefficient validation process, ASME. Willocq, Automatic optimisation of pre-swirl nozzle design, ASME Turbo Expo, Barcelona, Spain (2006) GT-2006–90249.Ī. Bauer, Measurement and analysis of aerodynamic and thermodynamic losses in pre-swirl system arrangements, ASME Turbo Expo, Montreal, Canada (2007) GT-2007–27191.į. Hills, A comparative study of cascade vanes and drilled nozzle design for pre-swirl, ASME Turbo Expo (2011) No. Wittig, Discharge coefficients of a preswirl system in secondary air systems, ASME J. Rolls-Royce, The JET ENGINE, Rolls-Royce plc, 5th Edition (1996) 85–88. Straznicky, Gas Turbine Theory, 6th Edition, Prentice Hall, London (2009) 366–376. Rotational Reynolds number = ( Ω r p 2)/ v S E By improving the discharge coefficient the pre-swirl system reduced aerodynamic losses, and the mass flow rate was increased at certain pressure ratios or satisfied the pressure margin for blade cooling. The optimized model showed a discharge coefficient of 0.846, which was 31.7 % higher than the baseline condition. The total temperature in pre-swirl system could be characterized as the reduction in temperature by nozzle acceleration and elevation by aerodynamic losses due to friction and viscous effects in the system. Total temperature drop effectiveness was increased from 0.07 to 0.29. Results showed that the optimized nozzle reduced total pressure losses and increased mass flow rate. The single-objective optimization was performed to maximize the discharge coefficient. The optimization process included the optimal Latin hypercube design sampling method with the Kriging surrogate model and genetic algorithm. Four design variables were considered in the optimization process: Nozzle inlet length ( L), outlet length ( l), inlet diameter ( D), and radial location ( r p). CFD methodologies were validated by comparing the CFD results with experiments. ![]() Hole-type pre-swirl nozzle was optimized using CFD analysis and experiments. ![]()
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |