TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst
ISBN Print: 978-1-56700-263-8
Table of Contents:
TURBINE AIRFOIL LEADING EDGE STAGNATION AERODYNAMICS AND HEAT TRANSFER - A REVIEW
page 20
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.10
RECENT PROGRESS IN NUMERICAL SIMULATION OF HIGHLY THREE-DIMENSIONAL TURBULENT FLOWS AND ENDWALL HEAT TRANSFER IN TURBINE BLADE CASCADES
page 18
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.20
EXPERIMENTAL INVESTIGATION OF TURNING FLOW EFFECTS ON INNOVATIVE TRAILING EDGE COOLING CONFIGURATIONS WITH ELLIPTIC PIN FINS
page 4
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.30
HEAT TRANSFER CHARACTERISTICS ON TIP AND INNER RIM SURFACES OF A BLADEWITH SQUEALER RIM
page 8
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.40
ADVANCED AERO-THERMAL INVESTIGATION OF HIGH PRESSURE TURBINE TIP FLOWS
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.50
TRAILING EDGE FILM COOLING OF GAS TURBINE AIRFOILS – EFFECTS OF EJECTION LIP GEOMETRY ON FILM COOLING EFFECTIVENESS AND HEAT TRANSFER
page 14
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.60
AGUMENTED HEAT TRANSFER OF AN INTERNAL BLADE TIP BY FULL OR PARTIAL ARRAYS OF PIN-FINS
page 13
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.70
TURBINE AIRFOIL AEROTHERMAL CHARACTERISTICS IN FUTURE COAL-GAS BASED POWER GENERATION SYSTEMS
page 14
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.80
THERMAL-MECHANICAL LIFE PREDICTION IN AFTER SHELL SECTION OF GAS TURBINE COMBUSTION LINER
page 11
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.90
COUPLING STUDY BETWEEN HEAT TRANSFER AND AERODYNAMIC FLOW IN SQUARE-EDGED INLET
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.100
HEAT TRANSFER INVESTIGATION OF THE SUB- AND SUPERCRITICAL FUEL FLOW THROUGH A U-TURN TUBE
page 13
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.110
CALCULATION OF GAS TURBINE BLADE TEMPERATURES USING AN ITERATIVE CONJUGATE HEAT TRANSFER APPROACH
page 14
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.120
EFFECT OF INTERNAL RIB CONFIGURATIONS ON THE DISCHARGE COEFFICIENT OF A 30-DEG INCLINED FILM COOLING HOLE
page 14
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.130
INFLUENCE OF INTERNAL CYCLONE FLOW ON ADIABATIC FILM COOLING EFFECTIVENESS
page 18
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.140
STUDY ON THE THERMAL AND FLOW FIELDS OF SHAPED FILM COOLING HOLES
page 15
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.150
FILM COOLING: BREAKING THE LIMITS OF DIFFUSION SHAPED HOLES
page 22
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.160
EXPERIMENTAL DETERMINATION OF THE AERO-THERMAL PERFORMANCE OF HIGH PRESSURE GAS TURBINE BLADES
page 2
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.170
EXPERIMENTAL STUDY OF EQUIVALENCE RATIO INFLUENCE ON THERMO-ACOUSTIC INSTABILITY IN GAS TURBINES
page 8
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.180
ANALYTICAL AND EXPERIMENTAL ANALYSIS OF REACTANTS VELOCITY EFFECT ON INSTABILITY OF PREMIXED COMBUSTION CHAMBER
page 9
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.190
A COMPARATIVE STUDY OF THE FILM COOLING HOLE CONFIGURATION EFFECTS ON THE LEADING EDGE OF ASYMMETRICAL TURBINE BLADE
page 16
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.200
COMPARISON STUDY OF CLOSURE MODELS FOR MODELLING A FLOW ON CURVED AND FLAT PLATES. FILM COOLING APPLIED TO GAS TURBINE BLADE
page 14
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.210
FIRST MOMENT CLOSURE MODELING OF FILM COOLING EFFECTIVENESS IN SINGLE ROW OF CYLINDRICAL HOLES
page 15
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.220
FRONT BULKHEAD UPSTREAM EFFECT ON INLET IGV COMPRESSOR FLOW OF MS5002B GAS TURBINE
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.230
MODELING OF HEAT TRANSFER IN EXHAUST NOZZLE OF GAS TURBINES
page 9
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.240
A NEW UNSTEADY FLUID NETWORK APPROACH TO SIMULATE THE CHARACTERISTICS OF THE AIR SYSTEM OF A GAS TURBINE SYSTEM
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.250
OPTIMIZATION OF A TURBINE VANE ENDWALL USING A COMBINED NATURAL AND NUMERICAL APPROACH
page 1
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.260
EFFECTS OF STATOR/ROTOR LEAKAGE FLOW AND AXISYMMETRIC CONTOURING ON ENDWALL ADIABATIC EFFECTIVENESS AND AERODYNAMIC LOSS
page 18
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.270
EFFECT OF GAP GEOMETRY ON THE COOLING EFFECTIVENESS OF THE WHEELSPACE COOLANT INJECTION UPSTREAM OF A ROW OF ROTOR BLADES
page 17
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.280
IMPACT OF THE GEOMETRY ON THE IMPROVEMENT OF THE THERMAL TRANSFER OF THE TURBULENT FLOWS
page 11
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.290
COMBINED HEAT EXCHANGE INTENSIFICATION TECHNIQUES AS A KEY TO DEVELOPMENT OF COMPACT HEAT EXCHANGERS FOR POWER GAS TURBINE UNITS
page 13
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.300
PIV MEASUREMENTS OF THE FLOW IN A ROTATING CAVITY WITH A RADIAL INFLOW
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.310
STUDY ON INFLUENCE OF INITIAL WALL TEMPERATURE DISTRIBUTION ON THE TRANSIENT MEASUREMENT RESULTS OF FILM COOLING
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.320
COMPARISON OF FILM COOLING IN THE PRESENCE OF VARIOUS MAINSTREAM PRESSURE GRADIENTS
page 18
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.330
A CORRELATION-BASED METHODOLOGY TO PREDICT THE FLOWSTRUCTURE OF FLOWS EMANATING FROM CYLINDRICAL HOLES WITH APPLICATION TO FILM COOLING
page 10
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.340
EFFECT OF THE GEOMETRY OF FILM COOLING HOLES ON HEAT TRANSFER COEFFICIENT IN CONDITION OF VARIOUS MAINSTREAM PRESSURE GRADIENTS
page 16
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.350
TURBINE VANE CASCADE HEAT TRANSFER PREDICTIONS USING A MODIFIED VERSION OF THE γ − Reοt % LAMINAR-TURBULENT TRANSITION MODEL
page 11
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.370
LARGE EDDY SIMULATION OF NON-ISOTHERMAL FLOW IN ROTOR/STATOR CAVITY
page 14
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.380
COMPARISON OF COUNTER – ROTATING AND TRADITIONAL AXIAL AIRCRAFT LOW-PRESSURE TURBINES INTEGRAL AND DETAILED PERFORMACNES
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.390
NUMERICAL SIMULATION OF THE ENDWALL HEAT TRANSFER IN THE LANGSTON CASCADE
page 8
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.400
AN EXPERIMENTAL STUDY OF AIRFOIL AND ENDWALL HEAT TRANSFER IN A LINEAR TURBINE BLADE CASCADE − SECONDARY FLOW AND SURFACE ROUGHNESS EFFECTS
page 18
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.410
HEAT TRANSFER AND FLOW TESTING IN ENGINE HP TURBINE COOLING SYSTEM DEVELOPMENT
page 16
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.420
PREDICTING THE COOLANT FLOW AND HEAT TRANSFER IN RADIAL TURBINE BLADES
page 20
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.430
EFFECT OF ROTATION ON THE CYCLONE COOLING METHOD MASS TRANSFER MEASUREMENTS
page 17
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.440
TURBINE AIRFOIL LEADING EDGE STAGNATION AERODYNAMICS AND HEAT TRANSFER - A REVIEW
page 20
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.450
RECENT STUDIES IN TURBINE BLADE INTERNAL COOLING
page 20
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.460
INFLUENCE OF HEIGHT TO DIAMETER RATIO ON IMPINGEMENT HEAT TRANSFER ON EFFUSED CONCAVE SURFACE
page 16
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.480
EXPERIMENTAL STUDY OF HEAT TRANSFER FROM IMPINGING JET WITH UPSTREAM AND DOWNSTREAM CROSSFLOW
page 10
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.490
AN EXPERIMENTAL AND NUMERICAL INVESTIGATION OF IMPINGEMENT HEAT TRANSFER IN AIRFOILS LEADING-EDGE COOLING CHANNEL
page 10
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.500
LIQUID CRYSTAL THERMOGRAPHY FOR TRANSIENT HEAT TRANSFER MEASUREMENTS IN COMPLEX INTERNAL COOLING SYSTEMS
page 13
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.510
EXPERIMENTAL AND THEORETICAL ANALYSIS OF HEAT TRANSFER CHARACTERISTICS IN A RECTANGULAR DUCT WITH JET IMPINGEMENT
page 12
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.520
EXPERIMENTAL TURBINE AERO-HEAT TRANSFER STUDIES IN ROTATING RESEARCH FACILITIES
page 21
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.530
MIXING OF AIR AND CO2 STUDY ON A TURBINE BLADE
page 4
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.540
Investigation of Film Cooled Rough Surfaces using Large Eddy Simulation
page 13
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.550
THE EFFECT OF EMBEDDED VORTICES ON FILM COOLING WITH COMPOUND ANGLE ORIENTATIONS
page 13
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.560
A NOVEL METHOD FOR THE COMPUTATION OF CONJUGATE HEAT TRANSFER WITH COUPLED SOLVERS
page 17
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.570
APPLICATION OF ARTIFICIAL NEURAL NETWORK (ANN) METHOD TO EXERGETIC ANALYSES OF GAS TURBINES
page 15
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.580