Global ETD Search

Search theses and dissertations gathered from participating repositories worldwide. Every result links back to the library that holds it. No account is needed.

Results

Showing 1 to 4 of 4 for “"Optimized Blade"”.

  1. Studies of Multipoint Optimization of Transonic Stators

    … and 17% faster than K-ε. Variable stator blades were added to an optimized blade geometry and compared to a design case where the stator blade angle was a part of the design vector. The optimized blade without variable stator blades was able to reduce total pressure loss to be 66.5% of the …

    ku Repository record for Studies of Multipoint Optimization of Transonic Stators (opens in a new tab)

  2. 3D Aerodynamic Optimization of NREL VI Wind Turbine Blade for Increased Power Output and Visualization of Flow Characteristics

    … aspect of optimization of NREL VI wind turbine blade for increased power output using commercial solver ANSYS 14.5. The power curve obtained from BEMT, Baseline NREL VI CFD Simulations and Optimized Blade Simulations are compared with experimental results. Over prediction is observed in the …

    embry-riddle Repository record for 3D Aerodynamic Optimization of NREL VI Wind Turbine Blade for Increased Power Output and Visualization of Flow Characteristics (opens in a new tab)

  3. Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade

    … process is defined for a composite wind turbine blade to optimize its aerodynamic and structural performance by developing a fluid-structural interaction (FSI) system. The objectives are to maximize aerodynamic efficiency and structural robustness while reducing blade mass and total cost. In the …

    embry-riddle Repository record for Fluid-structure Interaction and Multidisciplinary Design Analysis Optimization of Composite Wind Turbine Blade (opens in a new tab)

  4. Experimental and Numerical Investigations of Optimized High-Turning Supercritical Compressor Blades

    … of three high-turning supercritical compressor blades were conducted. The blades were designed at an inlet Mach number (M1) of 0.87 and inlet flow angle of 48.4 deg, with high camber angles of about 55 deg. The baseline blade was a conventional Controlled Diffusion Airfoil (CDA) design and the …

    vt Repository record for Experimental and Numerical Investigations of Optimized High-Turning Supercritical Compressor Blades (opens in a new tab)