Wind Tunnel Team Long Ly Nhan Doan NASA Grant URC NCC NNX08BA44A5/19/20151 SPACE Center Faculty Advisors: Dr. Chivey Wu Dr. Helen Boussalis Dr. Darrell.

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?


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)


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


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


Background

Ramjet EngineRamjet EngineAir InletAir InletCombustorCombustor NozzleNozzle

AdvantageAdvantage No Moving PartsNo Moving Parts

DisadvantageDisadvantage Cannot Self-StartCannot Self-Start


* 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


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


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


CFD SimulationFlow field: Cosmos FloworksFlow field: Cosmos Floworks


CFD: Swirling Flow

Tangential Velocity GradientsTangential Velocity Gradients


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)


Test Model Development

Motor Mount Extension with Fuel injectorMotor Mount Extension with Fuel injector


Wind Tunnel Testing


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)


Wind Tunnel Testing


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


Engine Performance Tests


Static Test Results


Static Test Results


Static Test Results


Wind Tunnel Test Results


Dynamic Test Results


Dynamic Test Results


Wind Tunnel Test Results


Static Combustion Test Results


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)


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


Project Timeline


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


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:

?NASA Grant URC NCC NNX08BA44ANASA Grant URC NCC NNX08BA44A04/18/2304/18/23 3636

Wind Tunnel Team Long Ly Nhan Doan NASA Grant URC NCC NNX08BA44A5/19/20151 SPACE Center Faculty Advisors: Dr. Chivey Wu Dr. Helen Boussalis Dr. Darrell.

Documents

jet engine slide

thinkquest slide

ducted fan jet engine

cfd simulation flow

combustor nozzle fan

ducted fan specifications

d isentropic flow combustor

lithium batteries fuel