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Posts
- Category: UNSTEADY AERODYNAMICS, AEROACOUSTICS AND AEROELASTICITY OF TURBOMACHINES (continued)
- Experimental Results
- Instrumentation
- Test Facility
- EXPERIMENTAL OFF-DESIGN INVESTIGATION OF UNSTEADY SECONDARY FLOW PHENOMENA IN A THREE-STAGE AXIAL COMPRESSOR AT 100% NOMINAL SPEED
- Measuring techniques
- Test facility
- Experimental setup
- EXPERIMENTAL INVESTIGATION OF WAKE-INDUCED TRANSITION IN A HIGHLY LOADED LINEAR COMPRESSOR CASCADE
- Mass Flow Rate and Net Thrust
- Rear Flow Separation
- Recirculation Margin and Engine Performance
- Flow Pattern Simulation Computational Model
- Control Sequences
- Turbo-Ram Mode Transition Variable Engine Geometry
- BYPASS FLOW PATTERN CHANGES AT TURBO-RAM TRANSIENT OPERATION OF A COMBINED CYCLE ENGINE
- Effect of Roughness Location
- Effect of Roughness Type
- Effect of Roughness Height
- Measurement Results with Roughness
- Measurement Results on Smooth Surface
- Measurement Techniques and Data Presentation
- Experimental Methods Experimental Facilities
- PARAMETRIC STUDY OF SURFACE ROUGHNESS AND WAKE UNSTEADINESS ON A FLAT PLATE WITH LARGE PRESSURE GRADIENT
- 6-bladerow studies
- Case study
- Structural model and calculation of the aeroelastic response
- Overview of the forced response methodology Flow model
- CORE-COMPRESSOR ROTATING STALL SIMULATION WITH A MULTI-BLADEROW MODEL
- Surge cycle at 105% Speed
- Recovery
- Rotating Stall Event at 60% Speed
- Experimental Procedure The Test Facility
- ANALYSIS OF UNSTEADY CASING PRESSURE MEASUREMENTS DURING SURGE AND ROTATING STALL
- Non-linear propagation of plane-wave mode in an axisymteric lined duct
- Non-linear propagation of plane wave in a 2D duct
- Results NASA flow impedance tube case
- Boundary conditions
- Methodology of the linear solver Governing equations
- A FREQUENCY-DOMAIN SOLVER FOR THE NON-LINEAR PROPAGATION AND RADIATION OF FAN NOISE
- Flow pulsations on the rotor blades and intensity of free vortexes
- Noise in an entrance plenum
- INFLUENCE OF MUTUAL CIRCUMFERENTIAL SHIFT OF STATORS ON THE NOISE GENERATED BY SYSTEM OF ROWS STATOR-ROTOR-STATOR OF THE AXIAL COMPRESSOR
- Sound Transmission Through a Cascade
- Effect of Mean Flow Variation on the Scattering
- Effect of Hub-Tip Ratio
- Inflow/Outflow Representation
- Mathematical Formulation
- INTERACTION OF ACOUSTIC AND VORTICAL DISTURBANCES WITH AN ANNULAR CASCADE IN A SWIRLING FLOW
- . Noise Control by Vane Sweep
- Noise Control by Vane Lean
- Numerical Procedure
- Numerical Domain and Boundary Conditions
- Problem Formulation Governing Equations
- PASSIVE NOISE CONTROL BY VANE LEAN AND SWEEP
- Modern Front Stage Compressor
- Three-Dimensional Results (Torsion)
- Three-Dimensional Results (Bending)
- Numerical Results Two-Dimensional Results
- Theory
- MULTISTAGE COUPLING FOR UNSTEADY FLOWS IN TURBOMACHINERY
- CLT2 Profile
- Datum Profiles
- Inlet conditions to the cascade
- Instrumentation
- Wake generators
- Test Facilities and Instrumentation
- Design Process
- THE EFFECT OF MACH NUMBER ON LP TURBINE WAKE-BLADE INTERACTION
- Comparison of experimental and theoretical results
- Model of free vortexes diffusion
- STRUCTURE OF UNSTEADY VORTICAL WAKES BEHIND BLADES OF MUTUAL-MOVING ROWS OF AN AXIAL TURBOMACHINE
- Critical Flutter Velocity
- Numerical Results and Discussion
- Unsteady Aerodynamic Force and Work
- Solution Philosophy
- Acoustic Modes and Frequencies
- Multiplication of Blade Loading Frequency
- Outline of the Analytical Method
- UNSTEADY AERODYNAMIC WORK ON OSCILLATING ANNULAR CASCADES IN COUNTER ROTATION
- Results
- Measurements and Data Analysis
- Trailing Edge Blowing System
- Wake Generators
- Description of Experiment Stage Matching Investigation Rig
- EXPERIMENTAL REDUCTION OF TRANSONIC FAN FORCED RESPONSE BY IGV FLOW CONTROL
- Conclusions and Future Work
- Results Space resolved data
- Modeling Approaches
- Boundary conditions
- Experimental data and boundary conditions Experiments
- COMPARISON OF MODELS TO PREDICT LOW ENGINE ORDER EXCITATION IN A HIGH PRESSURE TURBINE STAGE
- Results
- Configuration
- Numerical Method
- EVALUATION OF THE PRINCIPLE OF AERODYNAMIC SUPERPOSITION IN FORCED RESPONSE CALCULATIONS
- Case Study: Transonic Compressor Rotor
- Case Study: High Pressure Turbine Rotor
- Validation: High Pressure Turbine Rotor
- Forced Response Analysis
- Eigenvalue Analysis