wind tunnel team long ly nhan doan nasa grant urc ncc nnx08ba44a5/19/20151 space center faculty...
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Wind Tunnel Team
Long LyLong LyNhan DoanNhan Doan
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 11
SPACE Center
Faculty Advisors:Faculty Advisors:
Dr. Chivey WuDr. Chivey WuDr. Helen BoussalisDr. Helen BoussalisDr. Darrell GuillaumeDr. Darrell GuillaumeDr. Charles LiuDr. Charles Liu
Student Researchers:Student Researchers:
ObjectiveObjectiveBackgroundBackground
Gas Turbine EngineGas Turbine EngineRamjet EngineRamjet EngineTurbine-less Ducted Fan EngineTurbine-less Ducted Fan Engine
Analytical ModelAnalytical ModelCFD AnalysisCFD AnalysisWind Tunnel Testing and ValidationWind Tunnel Testing and ValidationPreliminary Hydrogen CombustionPreliminary Hydrogen CombustionApplicationsApplicationsFuture ObjectivesFuture ObjectivesQuestions?Questions?
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 22
Computational and Experimental Investigationof a Turbine-less Jet Engine
Motivation
Low-Cost Propulsion System for Future UAVLow-Cost Propulsion System for Future UAV
Utilization of Alternative Fuels (Hydrogen, Bio Fuel)Utilization of Alternative Fuels (Hydrogen, Bio Fuel)
Potential Application in Hybrid Propulsion SystemsPotential Application in Hybrid Propulsion Systems (Fuel Cells, Solar Photovoltaic, Lithium Batteries)(Fuel Cells, Solar Photovoltaic, Lithium Batteries)
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 33
ObjectiveDesign, Computational Simulation & Performance Tests of a Design, Computational Simulation & Performance Tests of a Turbine-less Ducted Fan Jet EngineTurbine-less Ducted Fan Jet Engine
Approach:Approach:AnalyticalAnalytical
Prediction of thrust, power required, efficiencyPrediction of thrust, power required, efficiency
ComputationalComputational Flow field & combustion simulationFlow field & combustion simulation Prediction of engine performancePrediction of engine performance
ExperimentalExperimental Wind tunnel testingWind tunnel testing
Hydrogen combustion testingHydrogen combustion testing Measurement of engine performanceMeasurement of engine performance
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 44
Background
Turbo Jet EngineTurbo Jet EngineAir InletAir InletCompressorCompressorCombustion Chamber Combustion Chamber TurbineTurbineNozzleNozzle
DisadvantagesDisadvantages Mechanical ComplexityMechanical Complexity Thermal LimitsThermal Limits Expensive to DevelopExpensive to Develop
* Image from NASA – Glenn Research Center
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 55
Background
Ramjet EngineRamjet EngineAir InletAir InletCombustorCombustor NozzleNozzle
AdvantageAdvantage No Moving PartsNo Moving Parts
DisadvantageDisadvantage Cannot Self-StartCannot Self-Start
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* Image from ThinkQuest
Turbine-less Ducted FanJet Engine Concept
FeaturesFeaturesDucted Fan, Combustor & NozzleDucted Fan, Combustor & NozzleFan driven by electric motorFan driven by electric motorElectricity from solar panels/fuel cellsElectricity from solar panels/fuel cellsCombustor & fuel cell may share same Combustor & fuel cell may share same fuel (e.g. Hydrogen)fuel (e.g. Hydrogen)
Advantages:Advantages:No need for a turbineNo need for a turbineLow costLow costSelf-startingSelf-starting
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 77
Analytical Model
Moment-of-Momentum EquationMoment-of-Momentum Equation
Simplification to obtain TorqueSimplification to obtain Torque
Shaft PowerShaft Power
Pressure RisePressure Rise
Impeller AnalysisImpeller Analysis
Guided Vane
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Combustor & Nozzle Analysis
Nozzle: 1-D Isentropic Flow Nozzle: 1-D Isentropic Flow Combustor: 1-D Heat Addition (Rayleigh Flow)Combustor: 1-D Heat Addition (Rayleigh Flow)
P2’
Po2’
M2’
T2’
T2’
P1
Po1
M1
T1
To1
P2
Po2
M2
T2
To2
P3
Po3
M3
T3
To3
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CFD SimulationFlow field: Cosmos FloworksFlow field: Cosmos Floworks
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CFD: Swirling Flow
Tangential Velocity GradientsTangential Velocity Gradients
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 1111
Combustion Simulation
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NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 1313
Combustion Simulation
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 1414
Combustion Simulation
Test Model Development
JetPro DF-70 Ducted FanJetPro DF-70 Ducted FanSpecifications:Specifications:Inner Diameter:Inner Diameter: 69 mm69 mmOuter Diameter:Outer Diameter: 72 mm72 mmRotor:Rotor: 8 Blade8 BladeMax Motor DiameterMax Motor Diameter 29 mm29 mmMotor Shaft DiameterMotor Shaft Diameter 3.17 mm3.17 mmTotal WeightTotal Weight 54.5g (1.92 oz)54.5g (1.92 oz)
Hacker B20-26L DC MotorHacker B20-26L DC MotorSpecifications:Specifications:Operating CurrentOperating Current 10 A10 APeak AmpsPeak Amps 57 A57 APeak WattsPeak Watts 220 W220 WRPM/VRPM/V 20772077Motor DiameterMotor Diameter 20 mm20 mmMotor LengthMotor Length 44.5 mm44.5 mmShaft DiameterShaft Diameter 2.3 mm2.3 mmShaft LengthShaft Length 10 mm10 mmWeightWeight 58g (2.03 oz)58g (2.03 oz)
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 1515
Test Model Development
Motor Mount Extension with Fuel injectorMotor Mount Extension with Fuel injector
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 1616
Combustor Model Development
RCLander 68mm Aluminum RCLander 68mm Aluminum Alloy Ducted Fan Alloy Ducted Fan
Specifications:Specifications:Inner Diameter:Inner Diameter: 69 mm69 mmOuter Diameter:Outer Diameter: 73 mm73 mmRotor:Rotor: 8 Blade8 BladeMax Motor DiameterMax Motor Diameter 28 mm28 mmMotor Shaft DiameterMotor Shaft Diameter 3.17 mm3.17 mmTotal WeightTotal Weight 54.5g (1.92 oz)54.5g (1.92 oz)
Elite 370 Brushless DC MotorElite 370 Brushless DC MotorSpecifications:Specifications:Operating CurrentOperating Current 10 A10 APeak AmpsPeak Amps 15 A15 AInput WattsInput Watts 125 W125 WRPM/VRPM/V 54005400Motor DiameterMotor Diameter 20 mm20 mmMotor LengthMotor Length 44.5 mm44.5 mmShaft DiameterShaft Diameter 3.17 mm3.17 mmShaft LengthShaft Length 10 mm10 mmWeightWeight 48g (1.7 oz)48g (1.7 oz)
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 1818
Instrumentation
Force TransducerForce Transducer
Pitot tubesPitot tubes
Pressure TransducersPressure Transducers
ThermocouplesThermocouples
Relative Humidity MeasurementRelative Humidity Measurement
LabVIEW Data AcquisitionLabVIEW Data Acquisition
Laser TachometerLaser Tachometer
Batteries/Power SupplyBatteries/Power Supply
Controller/Receiver/TransmitterController/Receiver/Transmitter
Multi-metersMulti-meters
Hydrogen Tank/ Pressure RegulatorHydrogen Tank/ Pressure RegulatorNASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 2020
Engine Performance Tests
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Engine Performance Tests
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Wind Tunnel Test Results
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Dynamic Test Results
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Dynamic Test Results
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Wind Tunnel Test Results
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Static Combustion Test Results
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Current Progress
Two Conference PapersTwo Conference Papers
(Fall 2009, Spring 2010)(Fall 2009, Spring 2010)
Two M.S. ThesesTwo M.S. Theses
(by June 2010)(by June 2010)
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 3131
Future Tasks
Wind Tunnel Testing with CombustionWind Tunnel Testing with Combustion
More CFD SimulationsMore CFD Simulations
Refinement of Fuel Injector DesignRefinement of Fuel Injector Design
Refinement of Combustor DesignRefinement of Combustor Design
Integration of Nozzle DesignIntegration of Nozzle Design
Performance OptimizationPerformance Optimization
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 3232
Project Timeline
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 3333
2009
March April May June July August September
Long Ly
Fabrication of Dry Ice Flow Visualization
Design of Turbine-less Jet Engine
Setup CNC routerLearn and Train CNC
router operationsCFD Model
DevelopmentCFD Model Validation
Nhan Doan
Validate LabView Data Acquisition
Fabrication of Flow Test ModelAnalytical Model
DevelopmentAnalytical Model
Validation
2009 2010
October November December January February
Long Ly
CFD Static Analysis & Static Wind Tunnel Testing
Preparation for Dynamic Wind Tunnel Testing
CFD Dynamic Analysis & Dynamic Wind Tunnel Testing
Combustion CFD Model, Fabrication of Combustor Test Model, Preliminary Static
Testing
Nhan Doan
Static Analytical Analysis & Static Wind Tunnel Testing
Dynamic Analytical Analysis & Dynamic Wind Tunnel Testing
Combustion Analytical Model , Fabrication of Combustor Test Model, Preliminary
Static Testing
2010
March April May June July August September
Long Ly
CFD Model Simulation, Refinement from Static Combustion Data, Analysis of Hot
Fire Test DataPreparation for
Combustion Testing in Wind Tunnel/ Preparation for Conferences
Combustion CFD Dynamic Analysis & Dynamic Wind Tunnel Testing
Nozzle Design Nozzle Fabrication
Nhan Doan
Analytical Model Validation from Static Combustion Testing Data/ Analysis of Hot
Fire Test Data
Combustion Dynamic Analytical Analysis & Dynamic Wind Tunnel Testing
Applications
High speed UAV’s High speed UAV’s
V/STOL UAV’sV/STOL UAV’s
LADF:LADF: Lift Augmented Ducted Fan;Lift Augmented Ducted Fan;
combines high speed and VTOLcombines high speed and VTOL
HyfishHorizon Fuel Cell
NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 3434
Acknowledgement
Solomon YitagesuSolomon Yitagesu
Sara EsparzaSara Esparza
Cesar OlmedoCesar Olmedo
Johanna LopezJohanna Lopez
Alonzo PerezAlonzo Perez
Shing ChanShing Chan
04/18/2304/18/23 NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A 3535
Space Center Members:Space Center Members: