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Computational and Experimental Investigation of a Turbine-less Jet Engine Concept

Computational and Experimental Investigation of a Turbine-less Jet Engine Concept. Long Ly Nhan Doan. Fall Technical Meeting Western States Section of the Combustion Institute University of California, Irvine, CA October 26-27, 2009.

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Computational and Experimental Investigation of a Turbine-less Jet Engine Concept

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

  2. 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?

  3. 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

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

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

  6. Advantages: • No need for a turbine • Low cost • Self-starting Turbine-less Ducted Fan Jet Engine • 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)

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

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

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

  10. CFD Result: Swirling Flow Tangential Velocity Gradients

  11. 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)

  12. Wind Tunnel Model Development Motor Mount Extension with Fuel injector

  13. Wind Tunnel Testing

  14. Instrumentation • Force Transducer • Pitottubes • Pressure Transducers • LabVIEW Data Acquisition • Strobe Tachometer • Batteries/Power Supply • Controller/Receiver/Transmitter • Multi-meters

  15. Preliminary Results

  16. Preliminary Results

  17. Preliminary Results

  18. Preliminary Results

  19. Preliminary Results

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

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

  22. 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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