GAS TURBINE GROUP 2012
Background The Campus Engineering Departments Laboratories Center for Reference on Gas Turbines
The Campus INSTITUTO TECNOLÓGICO DE AERONÁUTICA
The Campus INSTITUTO TECNOLÓGICO DE AERONÁUTICA
ITA Engineering Departments Aeronautical Engineering Electronic Engineering Mechanical- Aeronautical Engineering Civil Engineering (Aeronautical) Computation Engineering Aerodynamics Structures Propulsion Flight Mechanics Airplane Design Applied Eletronics Microwaves and Circuits Control Systems Telecom. Energy Design Organization Technology Gas Turbines Edifications Geotechnical Hidraulics Airports Transport Scientific Computation Software Engineering Computational Theory
Laboratories Center for Reference on Gas Turbines Created after El Paso Rio Claro granted funds under special ANEEL permission to adequate an old building to house the Gas Turbine Group and to provide computational resources to support research on gas turbines and gas turbines applications
Laboratories INSTITUTO TECNOLÓGICO DE AERONÁUTICA
Laboratories Center for Reference on Gas Turbines
Laboratories Center for Reference on Gas Turbines Professional MSc
Center for Reference on Gas Turbines Class rooms Chemical Laboratory
Center for Reference on Gas Turbines Gas Turbine (PT6) Cutview
Center for Reference on Gas Turbines Collaborative Projects with the Aeronautical and Space Institute
Center for Reference on Gas Turbines Collaborative Projects with the Aeronautical and Space Institute
Center for Reference on Gas Turbines Areas of Interest Gas Turbine Techonology and Power Plants Axial and Centrifugal Compressors Axial and Centrifugal Turbines Water Injection and Humid Air at Compressor Inlet Combustion Chambers Low Emissions Technology Gas Turbine Performance Prediction (all types) Numerical Methods in Gas Turbines - CFD Optimizations of Computational Codes Paralelization of Computational Codes Noise Prediction in Gas Turbines Turbine Blades Cooling Deterioration and Faults Identification in Gas Turbines Corrosion and Thermal Barriers
Improvements to the chemical labs Improvements to the flow machines labs Master and Doctoral Programs Test facilities for gas turbines Test facilities for compressors and turbines Test facilities for gas turbine air filters Industry Sponsored Projects of R&D Development of computational codes
Computational Codes Development: Gas Turbine Performance Prediction Steady-State and Transient Regimes Variable Geometry in Compressors, Turbines and Nozzles Compressors and Turbines Design and Performance Prediction Meanline Code - DP and ODP Streamline Curvature Code (SLC) DP and ODP CFD Internal and/or External Flows in Turbomachinery 3-D Euler, viscous and turbulent flows Combustion Chamber Design Fault Identification using GPA, NL-GPA, Neural Networks, and Fuzzy Logic
Axial Compressor Meanline Code: VIGV + VSV + BOV + Different Loss Models 14,0 0,90 12,0 0,85 Pressure ratio 10,0 8,0 6,0 4,0 Efficiency 0,80 0,75 0,70 Reference AFCC 1st Analysis 2nd Analysis 3th Analysis 4th Analysis 2,0 0,65 0,0 0,0 2,0 4,0 6,0 8,0 10,0 12 0,60 3,0 4,0 5,0 6,0 7,0 8,0 9,0 10,0 11,0 Mass flow (kg/s) Mass Flow (kg/s)
Axial Compressor Meanline Code: Optimization Model Incidence Comparison (Optimized Compressor) Incidence Comparison (Optimized Compressor) 14 12 nominal incidence 14 12 nominal incidence Incidence (º) 10 8 6 4 2 0-2 1 2 3 4 5 6 7 8 stall incidence minimum loss incidence calculated incidence Incidence (º) 10 8 6 4 2 0-2 1 2 3 4 5 6 7 8 stall incidence minimum loss incidence calculated incidence Rotor Rotor
Axial Compressor Meanline and Engine Performance Prediction Codes
Axial Compressor Meanline and Engine Performance Prediction Codes
Engine Transient Performance Prediction
3-Stage Axial Flow Compressor - SLC vs CFD % Span 100 90 80 70 60 50 40 30 20 10 0 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 R1 inlet SLC R1 inlet CFD Mach number % Span 100 90 80 70 60 50 40 30 20 10 0 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 Mach number R2 inlet SLC R2 inlet CFD % Span 100 90 80 70 60 50 40 30 20 10 0 0 0.2 0.4 0.6 0.8 1 1.2 Mach number R3 inlet SLC R3 inlet CFD
Axial Compressor Operating with Humid Air and Water Injection SLC
CFD Verification Cases
Airfoil withtransonic Flow and Nozzle with Supersonic Flow
Turbomachinery 3D CAD and Mesh Generation
Turbomachinery 3D Mesh Generation
Turbomachinery 3D Turbulent Flow Prediction Total Pressure Distribution NGV (absolute values) and Rotor (relative values) % Spanwise 100 90 80 70 60 50 40 30 20 10 0 100000 150000 200000 250000 300000 350000 400000 450000 500000 Total Pressure [Pa] NGV LE: centered NGV TE: centered Rotor LE: centered Rotor TE: centered NGV LE: FDS NGV TE: FDS Rotor LE: FDS Rotor TE: FDS
Turbomachinery 3D Turbulent Flow Prediction Total Temperature Distribution NGV (absolute values) and Rotor (relative values) 100 90 % Spanwise 80 70 60 50 40 30 20 10 0 900 925 950 975 1000 1025 1050 1075 1100 1125 1150 1175 1200 Total Temperature [k] Rotor TE: centered Rotor TE: FDS Outlet: centered Outlet: FDS
Turbomachinery 3D Turbulent Flow Prediction Mach number Distribution NGV (absolute values) and Rotor (relative values) % Spanwise 100 90 80 70 60 50 40 30 20 10 0 0 0,2 0,4 0,6 0,8 1 1,2 Mach number NGV LE: S-A NGV TE: S-A Rotor LE: S-A Rotor TE: S-A NGV LE: SST NGV TE: SST Rotor LE: SST Rotor TE: SST
Turbomachinery 3D Turbulent Flow Prediction Total Pressure Distribution - Inter-Blade Rows NGV (absolute values) and Rotor (relative values) % Spanwise 100 90 80 70 60 50 40 30 20 10 0 100000 200000 300000 400000 500000 Total Pressure [Pa] NGV MPlane: 5 div Rotor MPlane: 5 div NGV MPlane: 10 div Rotor MPlane: 10 div NGV MPlane: L-B-L Rotor MPlane: L-B-L
Turbomachinery 3D Turbulent Flow Prediction
Turbomachinery 3D CAD and Mesh Generation
Turbomachinery 3D CAD and Mesh Generation
Turbofan Nacelle = Design and 3D Turbulent Flow Prediction
Reverser Cascade Design for Turbofan Engine
Paralelization of CFD Computational Code
Paralelization of CFD Computational Code
Preliminary Centrifugal Compressor Design and Stress Prediction '
Neural Networks and Optimization Studies
Engine Performance - Variation of Turbine Blade Cooling with Different TIT
TAPP Gas Generator Vibration and Lubrification Test Stand
TAPP Data Acquisition Software
TAPP Internal View Turbojet: 5.0 KN Turboshaft: 1.2 MW
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