Fall Technical Meeting

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Presentation transcript:

Computational and Experimental Investigation of a Turbine-less Jet Engine Concept Fall Technical Meeting Western States Section of the Combustion Institute University of California, Irvine, CA October 26-27, 2009 Long Ly Nhan Doan Space Center / Multidisciplinary Flight Dynamics and Control Laboratory College of Engineering, Technology & Computer Science California State University, Los Angeles

Overview Objective Background Gas Turbine Engine Ramjet Engine Turbine-less Ducted Fan Engine Prototype Analytical Model CFD Analysis Wind Tunnel Testing and Validation Static Results Applications Future Objectives Questions?

Objective Conceptual Design and Feasibility Study of a Turbine-less Ducted Fan Jet Engine. Approach: Analytical Prediction of thrust, power required, efficiency Computational Flow field & combustion simulation Prediction of engine performance Experimental Wind tunnel testing Measurement of engine performance

Background Turbo Jet Engine Air Inlet Compressor Combustion Chamber Turbine Nozzle * Image from NASA – Glenn Research Center

Background Ramjet Engine Air Inlet Combustor Nozzle No Moving Parts Cannot self-start * Image from ThinkQuest

Turbine-less Ducted Fan Jet Engine Advantages: No need for a turbine Low cost Self-starting Features Ducted Fan, Combustor & Nozzle Fan driven by electric motor Electricity from solar panels/fuel cells Combustor & fuel cell may share same fuel (e.g. Hydrogen)

Analytical Model Impeller Analysis Moment-of-Momentum Equation Simplification to obtain Torque Shaft Power Pressure Rise Guided Vane

Combustor & Nozzle Analysis P2’ Po2’ M2’ T2’ P1 Po1 M1 T1 To1 P2 Po2 M2 T2 To2 P3 Po3 M3 T3 To3 Combustor: 1-D Heat Addition (Rayleigh Flow) Nozzle: 1-D Isentropic Flow

CFD Simulation Flow field: Cosmos Floworks Combustion simulation: Fluent 9

CFD Result: Swirling Flow Tangential Velocity Gradients 10

Wind Tunnel Model Development JetPro DF-70 Ducted Fan Specifications: Inner Diameter: 69 mm Outer Diameter: 72 mm Rotor: 8 Blade Max Motor Diameter 29 mm Motor Shaft Diameter 3.17 mm Total Weight 54.5g (1.92 oz) Hacker B20-26L DC Motor Specifications: Operating Current 10 A Peak Amps 57 A Peak Watts 220 W RPM/V 2077 Motor Diameter 20 mm Motor Length 44.5 mm Shaft Diameter 2.3 mm Shaft Length 10 mm Weight 58g (2.03 oz)

Wind Tunnel Model Development Motor Mount Extension with Fuel injector

Wind Tunnel Testing

Instrumentation Force Transducer Pitot tubes Pressure Transducers LabVIEW Data Acquisition Strobe Tachometer Batteries/Power Supply Controller/Receiver/Transmitter Multi-meters

Preliminary Results

Preliminary Results

Preliminary Results

Preliminary Results

Preliminary Results

Applications High speed UAV’s V/STOL UAV’s LADF: Lift Augmented Ducted Fan; combines high speed and VTOL Hyfish Horizon Fuel Cell

Future Objectives Dynamic Wind Tunnel Testing Continue Analytical Model CFD Analysis Dynamic Simulation Combustion Process with Ansys / Fluent Design Nozzle More Simulations and Testing

NASA University Research Center Grant #NNX08BA44A. Thank You Advisors Dr. Boussalis Dr. Wu Dr. Guillaume Dr. Pham Support Solomon Yitagesu Shing Chi Chan Sara Esparza NASA University Research Center Grant #NNX08BA44A.

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