1. Two Phase Flow in a Microgravity Environment Team Members: Dustin Schlitt Shem Heiple Jason Mooney Brian Oneel Jim Cloer Academic Advisor Mark Weislogel

2. Mission While Two-Phase flow cycles are more efficient in the transfer of heat energy, they have been avoided in low gravity applications due to the lack of experimental data describing the behavior of the flow regimes. It was the goal of the Portland State Team to develop a reliable, inexpensive testing apparatus that would reproduce a steady slug flow regime that could be easily employed in ground based micro- gravity test facilities, such as NASA’s KC-135.

3. Two Phase Flow Over View

4. Micro-Gravity vs. Normal Gravity Fluid flows in which the effect of surface tension is significant are called capillary flows. Generally in normal gravity such flows are limited to small channels less than a few millimeters in diameter. The Bond number, Bo = ρgr 2 /σ is the ratio of the gravitational force and the surface tension of the liquid, where ρ = density of fluid, g = the gravitational acceleration, r = the radius, σ = surface tension. When Bo >> 1, the gravitational force dominates fluid behavior. For Bo<< 1, surface tension plays a significant role in the behavior of the fluid. In the absence of gravity Bond numbers for large radius tubes can remain extremely small allowing flow patterns that are totally unique and unable to attain in normal gravity.

5. Bubbly Flow: Normal Gravity vs. Micro-Gravity

6. Slug Flow: Normal Gravity vs. Zero Gravity

7. Annular Flow: Normal Gravity vs. Zero Gravity

8. Design Requirements Because the apparatus was to be used in NASA’s unique KC-135 test environment certain design criteria were imposed by NASA’s Reduced Gravity Flight Office. These deign criteria along with a weighing factor enabled the evaluation of various designs to a common metric. The design criteria provided by NASA were broken down into the following categories: Performance, Ergonomics, Installation, and Safety. The following table highlights the design specifications.

9. Performance CustomerRequirementMetricImportance 1 NASAThe device is required to withstand hard landing loads. Forward9*9.8 m/s2 Aft3*9.8 m/s2 Down6*9.8 m/s2 Lateral 2*9.8 m/s2 Up2*9.8 m/s2 10 2 NASAThe device is to withstand inadvertent contact loads that could exceed “hard landing loads” locally. 81.64 kg impacting the structure at a velocity of.6096 m/s. 556 N over a 5.08 cm radius 10 3 NASAThe device must attain steady state operation within a short period of time. Because of the limited time available to take data the device must reach steady state within 25 seconds. 10

10. Ergonomics CustomerRequirementMetricImportance 1NASAThe device must be easily transported on and off the air craft. For manual transport no one person shall carry more than 222.4 N. 10 Installation CustomerRequirementMetricImportance 1NASAThe apparatus must be secured to the floor of the aircraft The apparatus must not exceed the maximum floor loading of 9576 N/m 2. The straps that will be used to secure the device to the floor of the air craft yield when 22241 N is applied, the device should not exceed this limit for any gravitational loading with less than a safety factor of 2 10

11. Safety CustomerRequirementMetricImportance 1NASAThe device should not contain any sharp edges or points 10 2NASAThe device must have a “kill switch” for emergency shut down procedures The “kill switch” must de-energize all components in the system to a safe state. 10 3NASAAll electronic wiring and cabling must be installed to both the Johnson Space Center Safety and Health Handbook and the National Electronic Code Standards. 10 4NASALiquids approved for use in the air craft must be contained Non-hazardous liquids in volume greater than 177 ml must be doubly contained, and the containment method should be structurally sound and able to with stand the inadvertent contact loads described in the performance section of this document. 10

12. Theory The testing apparatus employs the use of four transparent flexible tubes partially filled with a fluid of known properties ( viscosity (μ), surface tension (σ), density (ρ) ). These tubes are made to rotate around two drums. The drums in turn are mounted on a large rotating disk. As the large disk rotates the liquid slugs in the tubes experience a centripetal acceleration. This centripetal acceleration is sufficient enough to drive the fluid motion while maintaining a capillary dominated flow. As the large disk is rotated the drums are made to rotate dragging the fluid from the outer edge of the drum to the linear portion of the tube path shown.

14. A force balance in the linear path can be obtained between the acceleration force ( F a ), the viscous dissipation force( F μ ), and the surface tension force ( F σ ). When these forces balance a steady slug velocity develops. Theory V R rec R adv

15. Balancing forces yields, From this force balance the governing differential equation describing this flow is, At steady state the governing differential equation reduces to,

16. Our Design 1. Aluminum Frame 2. Mounting Plate 3. Motor/Gear Box ( Large Disk ) 4. Motor/Gear Box ( Drums ) 5. Drum Pack Assembly 6. Counter Weight 7. Digital Video Camera 8. Large Disk Rotational Velocity Display 9. Back Light Switch 10.DV Monitor 11.Speed Controls ( Large Disk, Drum ) 12.Power Supply 13.Outreach Experiment Controls 14.Outreach Experiment Housing 8. Large Disk Rotational Velocity Display 9. Back Light Switch 10.DV Monitor 11.Speed Controls ( Large Disk, Drum ) 12.Power Supply 13.Outreach Experiment Controls 14.Outreach Experiment Housing

17. Our Design

19. The Zero G Experience

20. KC135 Reduced Gravity Aircraft Number of Parabolas: 32Top of Parabola : 32,000 ft Free Fall Time : 21 secondsBottom of Parabola : 24,000 ft

21. Not Zero Gravity…but free fall

22. Fluids in Reduced Gravity

23. Reduced Gravity Fun

24. Data Analysis

25. Steady state slug velocity. Steady slug length. At least one revolution of the tube loop during steady state.

27. Measuring Film Thickness

28. Average Velocity

29. Change In Slug Length

30. Comparison of Data Against Previous Correlations

31. Results Steady state flow ± 1% Prediction match Errors –Aircraft –Apparatus –Film thickness sensitivity