instituto tecnolÓgico de aeronÁutica center for …barbosa/apresent ii centro referencia em...
TRANSCRIPT
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Background
The Campus
Engineering Departments
Laboratories
Center for Reference on Gas Turbines
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
ITA Engineering DepartmentsAeronauticalEngineering
•Aerodynamics•Structures•Propulsion•Flight
Mechanics•Airplane
Design
ElectronicEngineering
Civil Engineering(Aeronautical)
•Edifications•Geotechnical•Hidraulics•Airports•Transport
Mechanical-AeronauticalEngineering
•Energy•Design•Organization•Technology•Gas Turbines
ComputationEngineering
•ScientificComputation
•SoftwareEngineering
•ComputationalTheory
•AppliedEletronics
•Microwavesand Circuits
•ControlSystems
•Telecom.
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines
Created after El Paso Rio Claro granted fundsunder special ANEEL permission to adequate anold 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 AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines
Laboratories
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines
Laboratories
Professional MSc
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Class rooms
Center for Reference on Gas Turbines
Chemical Laboratory
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines
Gas Turbine (PT6)Cutview
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines
Collaborative Projects with the Aeronautical and Space Institute
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines
Collaborative Projects with the Aeronautical and Space Institute
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
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
Center for Reference on Gas Turbines – Areas of Interest
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
• 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
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
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 FuzzyLogic
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
Axial Compressor Meanline Code: VIGV + VSV + BOV + Different Loss Models
0,60
0,65
0,70
0,75
0,80
0,85
0,90
3,0 4,0 5,0 6,0 7,0 8,0 9,0 10,0 11,0
Mass Flow (kg/s)
Effic
ienc
y
Reference
AFCC
1st Analysis
2nd Analysis
3th Analysis
4th Analysis
0,0
2,0
4,0
6,0
8,0
10,0
12,0
14,0
0,0 2,0 4,0 6,0 8,0 10,0 12
Mass flow (kg/s)
Pres
sure
ratio
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
Axial Compressor Meanline Code: Optimization Model
Incidence Comparison (Optimized Compressor)
-2
0
2
4
6
8
10
12
14
1 2 3 4 5 6 7 8
Rotor
Inci
denc
e (º
)
nominalincidence
stallincidence
minimumlossincidencecalculatedincidence
Incidence Comparison (Optimized Compressor)
-2
0
2
4
6
8
10
12
14
1 2 3 4 5 6 7 8
RotorIn
cide
nce
(º)
nominalincidence
stallincidence
minimumlossincidencecalculatedincidence
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
Axial Compressor Meanline and Engine Performance Prediction Codes
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsAxial Compressor Meanline and Engine Performance Prediction Codes
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsEngine Transient Performance Prediction
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects3-Stage Axial Flow Compressor - SLC vs CFD
0102030405060708090
100
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6
% S
pan
Mach number
R1 inlet−SLCR1 inlet−CFD
0102030405060708090
100
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6
% S
pan
Mach number
R2 inlet−SLCR2 inlet−CFD
0102030405060708090
100
0 0.2 0.4 0.6 0.8 1 1.2
% S
pan
Mach number
R3 inlet−SLCR3 inlet−CFD
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsAxial Compressor Operating with Humid Air and Water Injection – SLC
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsCFD Verification Cases
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsAirfoil withTransonic Flow and Nozzle with Supersonic Flow
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D CAD and Mesh Generation
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Mesh Generation
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Turbulent Flow Prediction
Total Pressure Distribution NGV (absolute values) and Rotor (relative values)
0
10
20
30
40
50
60
70
80
90
100
100000 150000 200000 250000 300000 350000 400000 450000 500000
Total Pressure [Pa]
% S
panw
ise
NGV LE: centered
NGV TE: centered
Rotor LE: centered
Rotor TE: centered
NGV LE: FDS
NGV TE: FDS
Rotor LE: FDS
Rotor TE: FDS
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Turbulent Flow Prediction
Total Temperature Distribution NGV (absolute values) and Rotor (relative values)
0
10
2030
40
50
60
7080
90
100
900 925 950 975 1000 1025 1050 1075 1100 1125 1150 1175 1200
Total Temperature [k]
% S
panw
ise
Rotor TE: centered
Rotor TE: FDS
Outlet: centered
Outlet: FDS
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Turbulent Flow Prediction
Mach number Distribution NGV (absolute values) and Rotor (relative values)
0
10
20
30
40
50
60
70
80
90
100
0 0,2 0,4 0,6 0,8 1 1,2
Mach number
% S
panw
ise
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
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Turbulent Flow Prediction
Total Pressure Distribution - Inter-Blade RowsNGV (absolute values) and Rotor (relative values)
0102030405060708090
100
100000 200000 300000 400000 500000
Total Pressure [Pa]
% S
panw
ise
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
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Turbulent Flow Prediction
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D CAD and Mesh Generation
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D CAD and Mesh Generation
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsTurbofan Nacelle = Design and 3D Turbulent Flow Prediction
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsReverser Cascade Design for Turbofan Engine
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsParalelization of CFD Computational Code
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsParalelization of CFD Computational Code
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsPreliminary Centrifugal Compressor Design and Stress Prediction
'
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsNeural Networks and Optimization Studies
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and ProjectsEngine Performance - Variation of Turbine Blade Cooling with Different TIT
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
TAPP – Gas Generator Vibration and Lubrification Test Stand
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
TAPP – Data Acquisition Software
INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES
Center for Reference on Gas Turbines – Activities and Projects
Turbojet: 5.0 KN Turboshaft: 1.2 MW
TAPP – Internal View