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Wind Tunnel Team

Wind Tunnel Team. Long Ly Nhan Doan. Faculty Advisors:. Student Researchers:. Dr. Chivey Wu Dr. Helen Boussalis Dr. Darrell Guillaume Dr. Charles Liu. SPACE Center. Computational and Experimental Investigation of a Turbine-less Jet Engine. Objective Background Gas Turbine Engine

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Wind Tunnel Team

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  1. Wind Tunnel Team Long Ly Nhan Doan Faculty Advisors: Student Researchers: Dr. Chivey Wu Dr. Helen Boussalis Dr. Darrell Guillaume Dr. Charles Liu SPACE Center NASA Grant URC NCC NNX08BA44A

  2. Computational and Experimental Investigationof a Turbine-less Jet Engine • Objective • Background • Gas Turbine Engine • Ramjet Engine • Turbine-less Ducted Fan Engine • Analytical Model • CFD Analysis • Wind Tunnel Testing and Validation • Preliminary Hydrogen Combustion • Applications • Future Objectives • Questions? NASA Grant URC NCC NNX08BA44A

  3. Motivation • Low-Cost Propulsion System for Future UAV • Utilization of Alternative Fuels (Hydrogen, Bio Fuel) • Potential Application in Hybrid Propulsion Systems (Fuel Cells, Solar Photovoltaic, Lithium Batteries) NASA Grant URC NCC NNX08BA44A

  4. Objective • Design, Computational Simulation & Performance Tests 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 Hydrogen combustion testing Measurement of engine performance NASA Grant URC NCC NNX08BA44A

  5. Background Turbo Jet Engine Air Inlet Compressor Combustion Chamber Turbine Nozzle Disadvantages Mechanical Complexity Thermal Limits Expensive to Develop * Image from NASA – Glenn Research Center NASA Grant URC NCC NNX08BA44A

  6. Background Ramjet Engine Air Inlet Combustor Nozzle Advantage No Moving Parts Disadvantage Cannot Self-Start * Image from ThinkQuest NASA Grant URC NCC NNX08BA44A

  7. Advantages: • No need for a turbine • Low cost • Self-starting Turbine-less Ducted FanJet Engine Concept • 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) NASA Grant URC NCC NNX08BA44A

  8. Analytical Model • Impeller Analysis • Moment-of-Momentum Equation • Simplification to obtain Torque • Shaft Power • Pressure Rise Guided Vane NASA Grant URC NCC NNX08BA44A

  9. 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 NASA Grant URC NCC NNX08BA44A

  10. CFD Simulation • Flow field: Cosmos Floworks NASA Grant URC NCC NNX08BA44A

  11. CFD: Swirling Flow Tangential Velocity Gradients NASA Grant URC NCC NNX08BA44A

  12. Combustion Simulation NASA Grant URC NCC NNX08BA44A

  13. Combustion Simulation NASA Grant URC NCC NNX08BA44A

  14. Combustion Simulation NASA Grant URC NCC NNX08BA44A

  15. Test 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) NASA Grant URC NCC NNX08BA44A

  16. Test Model Development Motor Mount Extension with Fuel injector NASA Grant URC NCC NNX08BA44A

  17. Wind Tunnel Testing NASA Grant URC NCC NNX08BA44A

  18. Combustor Model Development • RCLander 68mm Aluminum Alloy Ducted Fan • Specifications: • Inner Diameter: 69 mm • Outer Diameter: 73 mm • Rotor: 8 Blade • Max Motor Diameter 28 mm • Motor Shaft Diameter 3.17 mm • Total Weight 54.5g (1.92 oz) • Elite 370 Brushless DC Motor • Specifications: • Operating Current 10 A • Peak Amps 15 A • Input Watts 125 W • RPM/V 5400 • Motor Diameter 20 mm • Motor Length 44.5 mm • Shaft Diameter 3.17 mm • Shaft Length 10 mm • Weight 48g (1.7 oz) 9/3/2014 NASA Grant URC NCC NNX08BA44A 18

  19. Wind Tunnel Testing NASA Grant URC NCC NNX08BA44A

  20. Instrumentation • Force Transducer • Pitot tubes • Pressure Transducers • Thermocouples • Relative Humidity Measurement • LabVIEW Data Acquisition • Laser Tachometer • Batteries/Power Supply • Controller/Receiver/Transmitter • Multi-meters • Hydrogen Tank/ Pressure Regulator NASA Grant URC NCC NNX08BA44A

  21. Engine Performance Tests NASA Grant URC NCC NNX08BA44A

  22. Engine Performance Tests NASA Grant URC NCC NNX08BA44A

  23. Static Test Results NASA Grant URC NCC NNX08BA44A

  24. Static Test Results NASA Grant URC NCC NNX08BA44A

  25. Static Test Results NASA Grant URC NCC NNX08BA44A

  26. Wind Tunnel Test Results NASA Grant URC NCC NNX08BA44A

  27. Dynamic Test Results NASA Grant URC NCC NNX08BA44A

  28. Dynamic Test Results NASA Grant URC NCC NNX08BA44A

  29. Wind Tunnel Test Results NASA Grant URC NCC NNX08BA44A

  30. Static Combustion Test Results NASA Grant URC NCC NNX08BA44A

  31. Current Progress • Two Conference Papers • (Fall 2009, Spring 2010) • Two M.S. Theses • (by June 2010) NASA Grant URC NCC NNX08BA44A

  32. Future Tasks • Wind Tunnel Testing with Combustion • More CFD Simulations • Refinement of Fuel Injector Design • Refinement of Combustor Design • Integration of Nozzle Design • Performance Optimization NASA Grant URC NCC NNX08BA44A

  33. Project Timeline NASA Grant URC NCC NNX08BA44A

  34. Applications Hyfish Horizon Fuel Cell High speed UAV’s V/STOL UAV’s LADF:Lift Augmented Ducted Fan; combines high speed and VTOL NASA Grant URC NCC NNX08BA44A

  35. Acknowledgement Solomon Yitagesu Sara Esparza Cesar Olmedo Johanna Lopez Alonzo Perez Shing Chan Space Center Members: NASA Grant URC NCC NNX08BA44A

  36. ? NASA Grant URC NCC NNX08BA44A

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