Computational and Experimental Investigationof a Turbine-less Jet Engine Concept

Long LyLong LyNhan DoanNhan Doan

Fall Technical MeetingWestern States Section of the Combustion Institute

University of California, Irvine, CAOctober 26-27, 2009

Space Center / Multidisciplinary Flight Dynamics and Control LaboratoryCollege of Engineering, Technology & Computer Science

California State University, Los Angeles

OverviewObjectiveObjectiveBackgroundBackground

Gas Turbine EngineGas Turbine EngineRamjet EngineRamjet EngineTurbine-less Ducted Fan EngineTurbine-less Ducted Fan Engine

PrototypePrototypeAnalytical ModelAnalytical ModelCFD AnalysisCFD AnalysisWind Tunnel Testing and ValidationWind Tunnel Testing and ValidationStatic ResultsStatic ResultsApplicationsApplicationsFuture ObjectivesFuture ObjectivesQuestions?Questions?

ObjectiveConceptual Design and Feasibility Study of a Conceptual Design and Feasibility Study of a Turbine-less Ducted Fan Jet Engine.Turbine-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 Measurement of engine performanceMeasurement of engine performance

Background

Turbo Jet EngineTurbo Jet EngineAir InletAir InletCompressorCompressorCombustion Chamber Combustion Chamber TurbineTurbineNozzleNozzle

* Image from NASA – Glenn Research Center

Background

Ramjet EngineRamjet EngineAir InletAir InletCombustorCombustor NozzleNozzle

No Moving PartsNo Moving Parts

Cannot self-startCannot self-start

* Image from ThinkQuest

Turbine-less Ducted Fan Jet Engine

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

Combustion simulation: FluentCombustion simulation: Fluent

CFD Result: Swirling Flow

Tangential Velocity GradientsTangential Velocity Gradients

Wind Tunnel 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)

Wind Tunnel Model Development

Motor Mount Extension with Fuel injectorMotor Mount Extension with Fuel injector

Wind Tunnel Testing

Instrumentation

Force TransducerForce Transducer

Pitot tubesPitot tubes

Pressure TransducersPressure Transducers

LabVIEW Data AcquisitionLabVIEW Data Acquisition

Strobe TachometerStrobe Tachometer

Batteries/Power SupplyBatteries/Power Supply

Controller/Receiver/TransmitterController/Receiver/Transmitter

Multi-metersMulti-meters

Preliminary Results

0

0.02

0.04

0.06

0.08

0.1

0.12

0.14

0 500 1000 1500 2000 2500 3000 3500

Vo

lum

etr

ic F

low

Ra

te Q

(m

3 /s)

RPM

Volumetric Flow Rate

Wind Tunnel Data

Extrapolated Points

Preliminary Results

Preliminary Results

Preliminary Results

Preliminary ResultsThrust Performance

0

2

4

6

8

10

12

0 500 1000 1500 2000 2500 3000 3500

RPM

F (

N)

Wind Tunnel Data

Factory Data

CFD Results

Theory

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

Future Objectives

Dynamic Wind Tunnel TestingDynamic Wind Tunnel Testing

Continue Analytical ModelContinue Analytical Model

CFD AnalysisCFD Analysis

Dynamic SimulationDynamic Simulation

Combustion ProcessCombustion Process

with Ansys / Fluentwith Ansys / Fluent

Design NozzleDesign Nozzle

More Simulations and TestingMore Simulations and Testing

Thank You

AdvisorsDr. Boussalis

Dr. Wu

Dr. Guillaume

Dr. Pham

SupportSolomon Yitagesu

Shing Chi Chan

Sara Esparza

NASA University Research Center Grant #NNX08BA44A.NASA University Research Center Grant #NNX08BA44A.

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