2. The Team Lincoln Cummings (IE) – Project Manager Joe Calkins (ME) – Chief Engineer Mark Fazzio (ME) – Technical Writer Allison Studley (ME) – Minutes Taker Dr. Kozak – Faculty Advisor Dr. Walter – Faculty Coordinator Sponsor – RIT Mechanical Engineering Dept.

3. Team Assignments 05002 Micro-Turbine Project Leader – Cliff Cummings Mentor – Prof. Jeff Kozak Fuel Systems Lead – Mark Asst. - Cliff PDR/ CDR Paper Lead – Mark Presentation Lead - Joe Turbine and Housing Leads – Joe/Allison

4. Mission Statement We will design and build a micro- turbine/generator that can be integrated onto a micro-air-vehicle airframe and power the vehicle’s accessories. The micro-turbine will be a continuation of the previous team’s project with the application of their design to be used for MAV power production.

5. Background Current battery technology causes the battery to be up to half of the weight of the MAV. Research into lighter weight power generation methods led to micro-turbine generators. Third generation RIT Senior Design project

6. Primary Objectives Produce a constant 5 watts of power Overall weight of less than 45 grams Integrated into the MAV airframe Minimum flight time of 3 minutes Additional Objectives Drive the propeller of the plane Increase efficiency of the system

7. Previous Design

8. Previous Turbine Design Senior Design Team 04013

9. Concept Considerations Smaller housing needed to integrate into MAV airframe Compressed gas containers must be integrated into MAV airframe Components capable of high rotational speeds Containment of high pressures within the system Minimum 3 minute run time Overall system weight goal of 45 grams

10. Research Methods Preliminary Research Review of last year’s design Additional Research

11. Feasibility Assessment 2 Options – Direct Comparison >2 Options – Weighted Comparison

12. Feasibility Assessment Considerations Ability to meet the objectives Overall Size Total Weight Availability of procured items Ease of Manufacture Cost of procurement/manufacture

13. Turbine Concepts 3-D Pelton Wheel Turbine 2-D Pelton Wheel Turbine Francis Turbine Axial Impulse Turbine

14. Turbine Feasibility

15. 3-D Pelton Wheel Turbine 2-D Pelton Wheel Turbine Francis Turbine Axial Impulse Turbine ?

16. Housing Concept Cross flow design 2 Inlets – 2 Outlets Tight tolerances to prevent flow from going around the turbine. 30% Fiberglass reinforced Nylon material Overall Size: 1.25” OD 0.6” Depth

17. Housing Feasibility Smaller OD Lighter weight O-Ring seal vs. Gasket seal Inlet/Outlet redesign Designed for manufacturability

18. Housing Analysis

19. Propellant System Concepts Fuel Compressed CO 2 Cartridges Compressed N 2 Cartridges Compressed Air Tanks Tubing Flexible plastic lines Rigid metal lines Regulator Bellows regulator to decrease the inlet pressure Micro nozzle to decrease the inlet pressure

20. Propellant System Feasibility Fuel Compressed CO 2 Cartridges Compressed N 2 Cartridges Compressed Air Tanks Tubing Flexible plastic lines Rigid metal lines Regulator Bellows regulator to decrease the inlet pressure Micro nozzle to decrease the inlet pressure

21. Other Design Concepts/Considerations Bearings: Sealed Air Shielded Magnetic Seals: O-Ring Gasket Use outlet flow in rear of wings/plane to reduce pressure drag

22. Other Design Concepts/Considerations Bearings: Sealed Air Shielded Magnetic Seals: O-Ring Gasket Use outlet flow in rear of wings/plane to reduce pressure drag

23. Test Setup Test initially using laboratory supplied compressed nitrogen. Canister compressed gas testing will be performed after concept is proven

24. Financial Analysis

25. Final Design

26. Design Limitations Propellant cartridge & piercing device weight is 24x higher than the design target weight Means of reducing the pressure of the propellant are inefficient Finding a generator to meet the high speed requirements

27. Schedule

28. Questions?