All Stories

  1. A data-driven optimal disturbance procedure for free-stream turbulence induced transition
  2. Effect of free-stream turbulence properties on different transition routes for a zero-pressure gradient boundary layer
  3. Dynamic mode decomposition for the inspection of three-regime separated transitional boundary layers using a least squares method
  4. Coherent Structures Formation During Wake-Boundary Layer Interaction on a LP Turbine Blade
  5. Unsteady Flow Evolution Through a Turning Midturbine Frame Part 2: Spectral Analysis
  6. Unsteady Flow Evolution Through a Turning Midturbine Frame Part 1: Time-Resolved Flow
  7. Recognition of coherent structures in the boundary layer of a low-pressure-turbine blade for different free-stream turbulence intensity levels
  8. On Turbulence Measurements and Analyses in a Two-Stage Two-Spool Turbine Rig
  9. Investigation of the Dynamics of an Ultra Low NO x Injection System by POD Data Post-Processing
  10. Dynamics and Turbulence Characteristics of Wake-Boundary Layer Interaction in a Low Pressure Turbine Blade
  11. Experimental investigation of the vortex breakdown in a lean premixing prevaporizing burner
  12. POD analysis of the unsteady behavior of a laminar separation bubble
  13. Comparison of a State of the Art and a High Stage Loading Rotor
  14. Development of a Turning Mid Turbine Frame With Embedded Design—Part II: Unsteady Measurements
  15. Development of a Turning Mid Turbine Frame With Embedded Design—Part I: Design and Steady Measurements
  16. Measurement and decomposition of periodic flow structures downstream of a test turbine
  17. Developement of a Turning Mid Turbine Frame With Embedded Design: Part I — Design and Steady Measurements
  18. Development of a Turning Mid Turbine Frame With Embedded Design: Part II — Unsteady Measurements
  19. Experimental Investigation of the Noise Generation and Propagation for Different Turning Mid Turbine Frame Setups in a Two-Stage Two-Spool Test Turbine
  20. Analysis tools for the unsteady interactions in a counter-rotating two-spool turbine rig
  21. Aerodynamic Effects of an Unshrouded Low Pressure Turbine on a Low Aspect Ratio Exit Guide Vane
  22. Analysis of the Unsteady Flow Field in Turbines by Means of Modal Decomposition
  23. Experimental Investigation of the Unsteady Flow Field Downstream of a Counter-Rotating Two-Spool Turbine Rig
  24. A method for the determination of turbulence intensity by means of a fast response pressure probe and its application in a LP turbine
  25. Identification of Spinning Mode in the Unsteady Flow Field of a Low Pressure Turbine
  26. Heat Transfer and Film Cooling of Blade Tips and Endwalls
  27. An Experimental Investigation of the Separated-Flow Transition Under High-Lift Turbine Blade Pressure Gradients
  28. Turbulent boundary layer separation control and loss evaluation of low profile vortex generators
  29. Validation of an Integrated Acoustic Absorber in a Turbine Exit Guide Vane
  30. Application of a Synthetic Jet to Control Boundary Layer Separation under Ultra-High-Lift Turbine Pressure Distribution
  31. Identification of Spinning Mode in the Unsteady Flow Field of a LP Turbine
  32. Near Wall Measurements in a Separating Turbulent Boundary Layer with and without Passive Flow Control
  33. Comparison of a Conventional Thermal Analysis of a Turbine Cascade to a Full Conjugate Heat Transfer Computation
  34. Radial Swirlers and Mixing Tube Assembly Aerodynamics and Performance Parameters Evaluation: Part 1—Hot-Wire Measurements in the Swirler Exit Plane
  35. Radial Swirlers and Mixing Tube Assembly Aerodynamics and Performance Parameters Evaluation: Part 2—LDV Measurements at the Mixing Tube Outlet
  36. Influence of Aerodynamic Loading on Rotor-Stator Aerodynamic Interaction in a Two-Stage Low Pressure Research Turbine
  37. Boundary Layer Separation Control on a Flat Plate With Adverse Pressure Gradients Using Vortex Generators
  38. Influence of Aerodynamic Loading on Rotor-Stator Aerodynamic Interaction in a Two-Stage Low Pressure Research Turbine