INSTITUTO TECNOLÓGICO DE AERONÁUTICA ... - turbina.ita.br

INSTITUTO TECNOLÓGICO DE AERONÁUTICACENTER FOR REFERENCE ON GAS TURBINES

GAS TURBINE GROUP

2012


Background

The Campus

Engineering Departments

Laboratories

Center for Reference on Gas Turbines


The Campus


The Campus


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.



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


Laboratories



Laboratories



Laboratories

Professional MSc


Class rooms


Chemical Laboratory



Gas Turbine (PT6)Cutview



Collaborative Projects with the Aeronautical and Space Institute



Collaborative Projects with the Aeronautical and Space Institute


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


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



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



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



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



Axial Compressor Meanline and Engine Performance Prediction Codes


Center for Reference on Gas Turbines – Activities and ProjectsAxial Compressor Meanline and Engine Performance Prediction Codes


Center for Reference on Gas Turbines – Activities and ProjectsEngine Transient Performance Prediction


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


0102030405060708090

100

0 0.2 0.4 0.6 0.8 1 1.2

% S

pan

Mach number



Center for Reference on Gas Turbines – Activities and ProjectsAxial Compressor Operating with Humid Air and Water Injection – SLC


Center for Reference on Gas Turbines – Activities and ProjectsCFD Verification Cases


Center for Reference on Gas Turbines – Activities and ProjectsAirfoil withTransonic Flow and Nozzle with Supersonic Flow


Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D CAD and Mesh Generation


Center for Reference on Gas Turbines – Activities and ProjectsTurbomachinery 3D Mesh Generation


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



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



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



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








Center for Reference on Gas Turbines – Activities and ProjectsTurbofan Nacelle = Design and 3D Turbulent Flow Prediction


Center for Reference on Gas Turbines – Activities and ProjectsReverser Cascade Design for Turbofan Engine


Center for Reference on Gas Turbines – Activities and ProjectsParalelization of CFD Computational Code


Center for Reference on Gas Turbines – Activities and ProjectsParalelization of CFD Computational Code


Center for Reference on Gas Turbines – Activities and ProjectsPreliminary Centrifugal Compressor Design and Stress Prediction

'


Center for Reference on Gas Turbines – Activities and ProjectsNeural Networks and Optimization Studies


Center for Reference on Gas Turbines – Activities and ProjectsEngine Performance - Variation of Turbine Blade Cooling with Different TIT



TAPP – Gas Generator Vibration and Lubrification Test Stand



TAPP – Data Acquisition Software



Turbojet: 5.0 KN Turboshaft: 1.2 MW

TAPP – Internal View


Thank you for your attention!

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INSTITUTO TECNOLÓGICO DE AERONÁUTICA ... - turbina.ita.br