Turbine-less Ducted Fan Jet Engine Subsonic Propulsion Wind Tunnel Team Long Ly Garrick Gregory

Overview Objective Background Turbine Engine Turbine-less Ducted Fan Engine Prototype CFD Analysis Wind Tunnel Testing and Validation Applications Future Objectives Questions?

Objective To perform simulation, testing, and validation of a conceptual Turbine-less Ducted Fan Jet Engine design. Analyze: Axial Flow Patterns Pressure Differences Thrust, Performance, and Efficiency Design: Outlet Nozzle

Background Conventional Turbine engine Air Inlet Compressor Combustion Chamber Turbine Nozzle * Images from NASA – Glenn Research Center

Turbine-less Ducted Fan Jet Engine What is a ducted fan? A fan or compressor installed inside a duct Why Turbine-less? No need for a turbine to drive the compressor Compressor is driven by electric motor Advantages: Less fuel consumption Less expensive Not difficult to manufacture Solar panel or fuel cell for electricity Hydrogen from fuel cell for combustion Quiet propulsion; suitable for undetected surveillance

CAD Model Complete Engine & Wind Tunnel Mounting Adaptor, Stator, Streamline injector Wind Tunnel Engine Mount

Rapid Prototype Adaptor, Stator, Streamline injector Complete Engine & Wind Tunnel Mounting Wind Tunnel Engine Mount *High grade plastic for quick prototype and aerodynamic testing

CFD Analysis Computational Fluid Dynamics Solidworks /CosmosFloworks Ansys 12.0 / ICEM / Fluent Navier Stokes Equations Finite Volume Method Navier-Stokes Flow Governing Equations (General / Vector Form) Continuity Equation: Momentum Equation: Internal Energy:

Flow Governing Equations (scalar form) Axisymmetric Flow Flow Governing Equations (scalar form) Continuity Equation: r Momentum Equation: θ Momentum Equation: z Momentum Equation:

Finite Volume Method Finite Difference Equations Taylor Series Expansion

CFD Progress CosmosFloworks Ansys 12.0 Technical Difficulties Complex geometry Software Crash Overnight Simulations Ansys 12.0 Ease importing geometry from other CAD Software Design Modeler – Parametric Solid Modeling Gambit obsolete Replaced with ICEM CFD Mesh creation slightly different CFD Solver - Fluent

Wind Tunnel Testing Static Test Subsonic Wind Tunnel Single axis force transducer 1 pitot tube, 2 pressure transducers T-fitting: dynamic & static pressure LabVIEW Data Acquisition A Pratt and Whitney turbofan engine for the F-15 Eagle

Pressure Pitot Tube Pressure Transducers Bernoulli’s Equation: Static pressure + dynamic pressure = Stagnation pressure *Pitot tube image from NASA – Glenn Research Center

Power Input Electrical Power Input 2 Digital Multi-meters Voltage Current Brushless Motor Controller Battery Receiver DMM V (v) I (A) + + + - + - Transmitter

RPM measurement

Photo Sensor Tachometer Impeller RPMs Photo Sensor Tachometer Laser Tachometer Strobe Tachometer

Static Test – Voltage Input

Static Test – Power Input

Static Test – Exit Velocities

Static Test - Thrust Test 1 Test 2

Thrust = F = ṁeVe - ṁiVi + (Pe-Pi)Ae Nozzle Design Pi ṁi Vi Pe ṁe Ve Ae Thrust = F = ṁeVe - ṁiVi + (Pe-Pi)Ae

Applications High speed UAV’s V/STOL UAV’s LADF: Lift Augmented Ducted Fan; combines high speed and VTOL Bell X-22A Aero-web.org

Future Objectives Complete CFD Analysis Dynamic Wind Tunnel Testing Design Nozzle More Testing

Thank You Advisors Support Dr. Boussalis Dr. Wu Dr. Guillaume Dr. Pham Nhan Doan Solomon Yitagesu Yacine Sahnoun Shing Chan Johanna Lopez Sara Esparza Roland Chen

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