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Posts
- Category: UNSTEADY AERODYNAMICS, AEROACOUSTICS AND AEROELASTICITY OF TURBOMACHINES (continued)
- Position of Unsteady Boundary Layer
- Measurement Techniques
- Low-Speed Axial Compressor
- ROTOR-STATOR INTERACTION IN A HIGHLY-LOADED, SINGLE-STAGE, LOW-SPEED AXIAL COMPRESSOR: UNSTEADY MEASUREMENTS IN THE ROTOR RELATIVE FRAME
- On influence of stators clocking on losses of total pressure in a compressor
- Structure of unsteady flow in system of rows stator-rotor-stator of the axial compressor
- Results of research Overall compressor parameters
- The purpose and volume of experiments
- Calculation Methods
- Technique of experiment and data processing
- Methods and means of research Experimental installation and measurements
- EFFECTS OF STATOR CLOCKINGIN SYSTEMOF ROWS STATOR-ROTOR-STATOROF THE SUBSONIC AXIAL COMPRESSOR
- Structure Model
- Aerodynamic Model
- STATOR-ROTOR AEROELASTIC INTERACTION FOR THE TURBINE LAST STAGE IN 3D TRANSONIC FLOW
- Unsteady Force Variation
- Unsteady Temperature Variation
- Accuracy of Numerical Results
- Geometry and Flow Conditions
- Boundary Conditions
- Discretization of Governing Equations
- Numerical Model
- Chemistry Model
- Physical Model
- ANALYSIS OF UNSTEADY AEROTHERMODYNAMIC EFFECTS IN A TURBINE-COMBUSTOR
- Flow Details
- Heat Transfer Coefficients
- Blade Pressure Distribution
- Computational Performance
- Numerical Boundary Conditions
- The MT-1 Single Stage HP Turbine
- Computational Method
- UNSTEADY 3D NAVIER-STOKES CALCULATION OF A FILM-COOLED TURBINE STAGE WITH DISCRETE COOLING HOLE
- Examples
- Implementation Issues
- Theory of Tubing Transfer Function Approach
- UNSTEADY PRESSURE MEASUREMENT WITH CORRECTION ON TUBING DISTORTION
- Far Spacing
- SMI Performance
- Stage Matching Investigation Rig
- DPIV MEASUREMENTS OF THE FLOW FIELD BETWEEN A TRANSONIC ROTOR AND AN UPSTREAM STATOR
- Unsteady pressure at the diffuser outlet
- Unsteady pressure at the diffuser inlet
- Analysis of Time-Dependent Data
- Numerical Methods and Boundary Conditions
- Instrumentation
- Test Compressor
- MEASURED AND CALCULATED UNSTEADY PRESSURE FIELD IN A VANELESS DIFFUSER OF A CENTRIFUGAL COMPRESSOR
- Results and Discussion
- Numerical Method
- INTERACTION BETWEEN SHOCK WAVES AND CASCADED BLADES
- Unsteady results
- Results and discussion
- Unsteady flow conditions and data reduction
- Numerical domain
- Numerical model
- Acquisition procedure and data reduction
- Unsteady perturbation generator
- Experimental modelю Test facility
- EXPERIMENTAL AND NUMERICAL STUDY OF NONLINEAR INTERACTIONS IN TWO-DIMENSIONAL TRANSONIC NOZZLE FLOW
- CFD code
- Technical approach
- OPTIMIZED DUAL-TIME STEPPING TECHNIQUE FOR TIME-ACCURATE NAVIER-STOKES CALCULATIONS
- Computational Efficiency and Robustness
- Standard Configuration 11
- Standard Configuration 10
- Solution Method
- Linearisation and Transformation to Frequency Domain
- Flow Model
- DEVELOPMENT OF AN EFFICIENT AND ROBUST LINEARISED NAVIER-STOKES FLOW SOLVER
- 3D Navier-Stokes fan blade computations
- PGRC Cascade
- Numerical validations
- Experimental test
- Newmark scheme
- Direct dynamic coupling using dual time stepping for moving meshes
- Dual time stepping implementation
- Turbulence models
- Specific chorochronic boundary condition
- Mesh deformation techniques
- 3D Unsteady aerodynamics solver features
- NUMERICAL UNSTEADY AERODYNAMICS FOR TURBOMACHINERY AEROELASTICITY
- Unsteady pressure results
- Power spectra of pressure fluctuation, bump motion and shock wave movement
- Schlieren pictures over one period of shock wave oscillation
- Experimental results
- Objectives
- STUDY OF SHOCK MOVEMENT AND UNSTEADY PRESSURE ON 2D GENERIC MODEL
- Numerical applications
- Minimum state smoothing method
- Solution of the coupled system. Double scanning method
- Computation of the generalized aerodynamic forces
- Reduced coupled system
- FREQUENCY AND TIME DOMAIN FLUID-STRUCTURE COUPLING METHODS FOR TURBOMACHINERIES
- Rod test-case
- VKI Turbine
- Flow solver: Proust / TurbFlow
- ANALYSES OF URANS AND LES CAPABILITIES TO PREDICT VORTEX SHEDDING FOR RODS AND TURBINES
- Last Stage, Analysis in Detail
- Front Stage, Analysis in Detail