EDUCATION

• Ph. D. 1980, Stanford University, Mechanical Engineering.
• M. S. 1975, Stanford University, Mechanical Engineering.
• B. S. 1974, University of Texas at Austin, Mechanical Engineering.

ACADEMIC EMPLOYMENT

• Assistant Professor, von Karman Institute for Fluid Dynamics, 1979-82.
• Visiting Senior Research Fellow, Imperial College of Science and Technology, University of London, 1982-84.
• Associate Professor, U. S. Postgraduate School, Department of Mechanical Engineering, 1984-92.
• Professor, University of Utah, Department of Mechanical Engineering, 1992-present.

E-MAIL: ligrani@mech.utah.edu
VOICE TELEPHONE: (801) 581-4240
FAX TELEPHONE: (801) 585-9826

RECENT ACADEMIC DISTINCTIONS AND AWARDS

• Cited in Who's Who, International Who's Who, Who's Who in the West, the International Directory of Distinguished Leadership, and Who's Who in the International Gas Turbine Institute.
• Commendation Letters for Outstanding Teaching (Ranked in top 15% of the University of Utah College of Engineering): (i) ME3600-Thermodynamics I, Autumn Semester of 1999, (ii) ME562- Thermal Systems Design, Spring Quarter of 1998, (iii) ME665-Advanced Heat Transfer II, Winter Quarter of 1997, (iv) ME562-Thermal Systems Design, Spring Quarter of 1996, (v) ME360-Engineering Thermodynamics, Fall Quarter of 1995, (vi) ME362-Power Thermodynamics, Winter Quarter of 1995, (vii) ME362-Power Thermodynamics, Spring Quarter of 1994.
• June 2001-July 2001, Invited Visiting Scholar, National Academy of Sciences of Ukraine, Institute of Engineeirng Thermophysics, Kiev-57, 252057, Ukraine. Supported by NATO Link Grant.
• April 2000-June 2000, Guest Professor, Institut fuer Thermische Stroemungs-maschinen, Universitaet Karlsruhe, Kaiserstrasse 12, 76128 Karlsruhe, Germany.
• June 1999-August 1999, AGTSR Faculty Fellowship at General Electric Corp.-Corporate Research and Development. Funded by the SCERDC, South Carolina Energy Research and Development Center.
• June 1995, Professor of the Year Award, presented by the undergraduates of the Department of Mechanical Engineering, University of Utah for exceptional teaching.
• November 1991, NASA Space Act Tech Brief Award, ARC-12228-1, "Development of Subminiature Multi-Sensor Hot-Wire Probes."
• Naval Postgraduate School Faculty Performance Awards: (i) October 1991, (ii) October 1990, (iii) October 1989.
• December 1990, Carl E. and Jessie W. Menneken Faculty Award for Excellence in Scientific Research.
• November 1982-November 1983, Visiting Senior Research Fellowship, Department of Aeronautics, Imperial College of Science and Technology. Nomination by Professor Peter Bradshaw, Head, Aerodynamics, Department of Aeronautics.
• September 1978, Miller Research Fellowship Nomination (Adolph C. and Mary Sprague Miller Institute for Basic Research in Science, 2334 Bowditch Street, Berkeley, California 94720). Nomination by College Dean and Professor William M. Kays, Stanford University.
• September 1974-June 1975, Stanford University Fellowship.
• May 1974, Bachelor of Science Degree with Highest Honors, Department of Mechanical Engineering, University of Texas at Austin.

PUBLICATIONS

As of 2000, Dr. Ligrani is author of about 70 publications in archival journals, including the International Journal of Heat and Mass Transfer, the ASME Transactions-Journal of Turbomachinery, the ASME Transactions-Journal of Heat Transfer, the ASME Transactions-Journal of Fluids Engineering, the Journal of Fluid Mechanics, Experiments in Fluids, Physics of Fluids, Separation Science and Technology, and the Journal of Microcolumn Separations. He is also author of 5 book chapters, and about 50 conference publications. A number of these are invited conference presentations at international meetings at locations which include Korea, France, the Ukraine, and Belgium. From 1998 to 2000, he also served as Guest Editor for a Special Topical Issue on "Measuring Techniques for Turbomachinery" for the international journal Measurement Science and Technology.

CURRENT AND RECENT RESEARCH

Research areas include convective heat transfer, laminar, turbulent and transitional flows, and experimental techniques, including subminiature hot-wire anemometry. Because most of the projects involve investigations of fundamental fluid mechanics and heat transfer phenomena, each project has an engineering science aspect to it. Recent research and consulting focus on gas turbine heat transfer and cooling, film cooling, transonic flows, aerodynamic losses in turbines, and general heat transfer topics including mixed convection, turbomachinery, two-phase flows, and electronics cooling. More recently, research efforts include topics in applied analytic chemistry, including Field-Flow Fractionation, and Continuous SPLITT Fractionation.

Sponsors for research efforts at the University of Utah include: National Science Foundation, South Carolina Institute for Energy Studies (SCIES-AGTSR) of the Department of Energy, U. S. Army Aviation Research and Technology Activity-AVSCOM, NASA-Ames Research Center, NASA-Lewis Research Center, Hispanic Research Center-Arizona State University, Turbo and Power Machinery Research Center-Seoul National University, Solar Turbines Incorporated, UCON U.S.-Japan Center-Weber State University, General Electric Corporate Research and Development Center, Pratt & Whitney Corporation-Florida, and the North Atlantic Treaty Organization (NATO).

Topics (1)-(7) are applicable to heat transfer to surfaces of turbine blades, heat transfer within internal turbine blade passages, transonic flows, aerodyanmic losses in turbines, and heat exchangers. Topic (8) is applicable to the fractionation of solid particles suspended in fluid media. Continuous SPLITT Fractionation (CSF) was conceived by the late Distinguished Professor Cal Giddings of the University of Utah, who received a number of awards for his work in this area, including nominations for the Nobel Prize in Chemistry in 1984 and 1992. Topic (9) describes a number of recent investigations focussed on the development of experimental techniques.

(1) Effects of Bulk Flow Pulsations on Film Cooling.

The effects of imposed bulk flow unsteadiness on film cooling effectiveness and surface heat transfer in turbulent boundary layers are investigated as applied to the turbines of gas turbine engines. Pulsations of static pressure are important because they result in significant periodic variations of film cooling flow rates, coverage, and trajectories. Different shaped hole configurations are under investigation, including laterally-diffused-compound-angle holes, forward-diffused-compound-angle holes, and laid-back fan-shaped holes. Of particular interest are the effects of pulsating static pressure and pulsating streamwise velocity which accompany potential flow interactions and passing shock waves. A large scale test section is used in a low-speed wind tunnel so that detailed boundary layer characteristics are measured. Attention is focused on: (i) detailed direct measurements of local adiabatic film cooling effectiveness, (ii) measurements of local iso-energetic heat transfer coefficients, (iii) measurements of overall film cooling performance parameter distributions, (iv) flow structural characteristics, and (v) the effects of amplitude and frequency of the bulk flow pulsations on film cooling.

Recent publications:

1. Bulk Flow Pulsations and Film Cooling: Part 1, Injectant Behavior (P. M. Ligrani, R. Gong, J. M. Cuthrell, and J. S. Lee), International Journal of Heat and Mass Transfer, Vol. 39, No. 11, pp. 2271-2282, July 1996.

2. Bulk Flow Pulsations and Film Cooling: Part 2, Flow Structure and Film Effectiveness (P. M. Ligrani, R. Gong, J. M. Cuthrell, and J. S. Lee), International Journal of Heat and Mass Transfer, Vol. 39, No. 11, pp. 2283-2292, July 1996.

3. Effects of Bulk Flow Pulsations on Film-Cooled Boundary Layer Structure (P. M. Ligrani, R. Gong, J. M. Cuthrell, and J. S. Lee), ASME Transactions-Journal of Fluids Engineering, Vol. 119, No. 1, pp. 56-66, March 1997.

4. Bulk Flow Pulsations and Film Cooling: Flow Structure Just Downstream of the Holes (P. M. Ligrani, R. Gong, and J. M. Cuthrell), ASME Transactions-Journal of Turbomachinery, Vol. 119, No. 3, pp. 568-573, July 1997.

5. The Effect of Injection Hole Length on Film Cooling With Bulk Flow Pulsations (H. J. Seo, J. S. Lee, and P. M. Ligrani), International Journal of Heat and Mass Transfer, Vol. 41, No. 22, pp. 3515-3528, November 1998.

6. Effects of Bulk Flow Pulsations on Film Cooling From Different Length Injection Holes at Different Blowing Ratios (H. J. Seo, J. S. Lee, and P. M. Ligrani), ASME Transactions-Journal of Turbomachinery, Vol. 121, No. 3, pp. 542-550, July 1999.

7. Film Cooling Subject to Bulk Flow Pulsations: Effects of Blowing Ratio, Freestream Velocity, and Pulsation Frequency (C. M. Bell, P. M. Ligrani, W. A. Hull, and C. M. Norton), International Journal of Heat and Mass Transfer, Vol. 42, No. 23, pp. 4333-4344, December 1999.

8. Film Cooling From Shaped Holes (C. M. Bell, H. Hamakawa, and P. M. Ligrani), ASME Transactions-Journal of Heat Transfer, Vol. 122, No. 2, pp. 224-232, May 2000.

9. Film Cooling Subject to Bulk Flow Pulsations: Effects of Density Ratio, Hole Length-to-Diameter Ratio, and Pulsation Frequency (P. M. Ligrani and C. M. Bell), accepted for publication, International Journal of Heat and Mass Transfer, to appear, 2000.

10. Effects of Bulk Flow Pulsations on Phase-Averaged and Time-Averaged Film-Cooled Boundary Layer Flow Structure, (I.-S. Jung, P. M. Ligrani, and J. S. Lee), submitted to ASME Transactions-Journal of Fluids Engineering, 2000.

11. Bulk Flow Pulsations and Film Cooling: Flow Structure Just Downstream of the Holes (P. M. Ligrani, J. M. Cuthrell, and R. Gong), Paper 95-GT-44, ASME 40th International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas, June 5-8, 1995.

12. Effects of Bulk Flow Pulsations on Injectant Behavior and Film Cooling Effectiveness (J. S. Lee, R. Gong, J. M. Cuthrell, and P. M. Ligrani), Second European Thermal Sciences and 14th UIT National Heat Transfer Conference, Rome, Italy, May 29-31, 1996.

13. Effects of Bulk Flow Pulsations on Film Cooling From Different Length Injection Holes at Different Blowing Ratios (H. J. Seo, J. S. Lee, and P. M. Ligrani), Paper 98-GT-192, 43rd ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, Stockholm, Sweden, June 2-5, 1998.

14. Investigations of the Effects of Bulk Flow Pulsations on Film Cooling as Applied to Gas Turbine Engines (P. M. Ligrani, J. S. Lee, and H. J. Seo), Paper GT-7, IHTC, International Heat Transfer Congress, Kyongju, South Korea, August 23-28, 1998.

(2) Effects of Surface Roughness of Flow Structure and Surface Heat Transfer.

Surface roughness, or surface finish, is known to have a major impact on the thermal loading and pressure loss characteristics of many different types of system components, and therefore to play a significant role in the overall efficiency of most machinery which involves the movement of working fluids. A prime example of this is found in turbomachinery, such as steam turbines and gas turbines, where roughness plays major roles in augmenting heat loading and aerodynamic losses. In some cases, these changes can be greater than those due to large variations of freestream turbulence intensity (i.e. from 1 to 10 percent). Smoother flow path surfaces thus translate directly into higher performance, greater efficiency, and lower operating and maintenance costs. It is very important to understand the characteristics of surfaces manufactured by specific processes or produced by specific operating environments, thereby enhancing the ability to design equipment for better performance up-front, as well as to properly balance the many competing design requirements and functions.

In this study, new techniques are used to determine roughness geometry characteristics. These quantities are determined because of their usefulness in the design of turbomachinery components and in the analyses of turbomachinery flows. Different rough surface samples will be analyzed to determine information on the relationships between surface manufacturing techniques, and operational environment on rough surface parameters. Parallel with these efforts will be measurements of surface skin friction coefficients, Stanton numbers, and flow structure to verify magnitudes of roughness geometric parameters.

(3) Heat Transfer and Flow Phenomena in Swirl Chambers.

Flows in several different swirl chambers are investigated to understand physical mechanisms responsible for augmenting surface heat transfer rates relative to two-dimensional flow in the same passage geometry. Infrared thermography (used with in situ calibration procedures, energy balances, thermocouples, and digital image processing) is employed to measure spatially-resolved distributions of surface heat transfer coefficients and Nusselt numbers. The infrared camera views test surfaces of the swirl chamber through a custom-made, cylindrical zinc selenide window, especially constructed so that one surface contour exactly matches the inner contour of the swirl chamber wall. Because the flow in the passage is subject to strong concave curvature, arrays of counter-rotating vortex pairs develop in the flow just adjacent to the concave surface, which significantly affect surface Nusselt number distributions. Also being considered are: (i) determination of the characteristics and development of the vortices within the flow near the concave surface, (ii) the alterations to the vortices which result from the flow geometry, (iii) development of secondary flows, skewness, and unsteadiness in the vortex arrays, and (iv) effects of inlet to near-wall density ratio on local surface Nusselt number distributions.

Recent publications:

1. Flow Phenomena in Swirl Chambers (P. M. Ligrani, C. R. Hedlund, R. Thambu, B. T. Babinchak, H-K. Moon, and B. Glezer), Paper 97-GT-530, ASME 42nd International Gas Turbine and Aeroengine Congress and Exposition, Orlando, Florida, June 2-5, 1997.

2. Heat Transfer and Flow Phenomena in a Swirl Chamber Simulating Turbine Blade Internal Cooling (C. R. Hedlund, P. M. Ligrani, H.-K. Moon, B. Glezer), Paper 98-GT-466, 43rd ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, Stockholm, Sweden, June 2-5, 1998.

3. Local Swirl Chamber Heat Transfer and Flow Structure at Different Reynolds Numbers (C. R. Hedlund, and P. M. Ligrani), Paper 99-GT-164, 44th ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, Indianapolis, Indiana, June 7-10, 1999.

4. Flow Phenomena in Swirl Chambers (P. M. Ligrani, C. R. Hedlund, R. Thambu, B. T. Babinchak, H-K. Moon, and B. Glezer), Experiments in Fluids, Vol. 24, No. 3, pp. 254-264, March 1998.

5. Flow in a Simple Swirl Chamber With and Without Controlled Inlet Forcing (R. Thambu, B. T. Babinchak, P. M. Ligrani, C. R. Hedlund, H-K. Moon, and B. Glezer), Experiments in Fluids, Vol. 26, No. 4, pp. 347-357, March 1999.

6. Heat Transfer and Flow Phenomena in a Swirl Chamber Simulating Turbine Blade Internal Cooling (C. R. Hedlund, P. M. Ligrani, H.-K. Moon, B. Glezer), ASME Transactions-Journal of Turbomachinery, Vol. 121, No. 4, pp. 804-813, October 1999.

7. Heat Transfer in a Swirl Chamber at Different Temperature Ratios and Reynolds Numbers (C. R. Hedlund, P. M. Ligrani, B. Glezer, and H.-K. Moon), International Journal of Heat and Mass Transfer, Vol. 42, No. 22, pp. 4081-4091, November 1999.

8. Local Swirl Chamber Heat Transfer and Flow Structure at Different Reynolds Numbers (C. R. Hedlund, and P. M. Ligrani), ASME Transactions-Journal of Turbomachinery, Vol. 122, No. 2, pp. 375-385, April 2000.

9. Effects of Curvature on Heat Transfer in Channels and Swirl Chambers (P. M. Ligrani), Recent Research Developments in Heat, Mass, & Momentum Transfer, Vol. 2-1999, (Editor: S. G. Pandalai), Research Signpost Publishers, Vol. 2, pp. 171-183, 1999.

10. Gortler Vortex Acrobatics in a Simple Swirl Chamber (C. R. Hedlund, B. T. Babinchak, P. M. Ligrani, H. Peerhossaini, H-K. Moon, and B. Glezer), 10th Couette-Taylor Workshop, ESPCI, Paris, France, July 15-18, 1997.

(4) Investigation of Special Surfaces to Augment Nusselt Numbers in Turbine Airoil Internal Passages.

Flows along different types of especially constructed surfaces are under investigation. These include surfaces with arrays of dimples. Such surfaces are special because they provide significant augmentations of surface Nusselt number magnitudes with minimal increases in static pressure drop, compared to two-dimensional flows in channels with smooth walls. Also under investigation are pin fins and rib turbulators. Spatially-resolved distributions of surface Nusselt numbers are measured using infrared thermography used in conjunction with in situ calibration procedures, energy balances, thermocouples, and digital image processing. Also under investigation are a variety of flow characteristics using flow visualization, wall-static pressure taps, miniature five-hole pressure probes, and hot-wire anemometry.

Recent publications:

1. Local Heat Transfer and Flow Structure On and Above a Dimpled Surface in a Channel (G. I. Mahmood, M. L. Hill, D. L. Nelson, P. M. Ligrani, H.-K. Moon, and B. Glezer), accepted for publication, ASME Transactions-Journal of Turbomachinery, to appear, 2001.

2. Local Heat Transfer and Flow Structure On and Above a Dimpled Surface in a Channel (G. I. Mahmood, M. L. Hill, D. L. Nelson, P. M. Ligrani, H.-K. Moon, and B. Glezer), Paper 2000-GT-230, 45th ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, Munich, Germany, May 8-11, 2000.

3. Effects of Top Wall Protrusions on Flow Structure in a Channel With Bottom Wall Dimples, (P. M. Ligrani, G. I. Mahmood, J. Harrison, D. L. Nelson), in preparation for International Journal of Heat and Mass Transfer, 2000.

4. Effects of Top Wall Protrusions on Heat Transfer in a Channel With Bottom Wall Dimples, (G. I. Mahmood, M. Sabbagh, P. M. Ligrani, H.-K. Moon, B. Glezer), in preparation for International Journal of Heat and Mass Transfer, 2000.

5. Heat Transfer From a Dimpled Surface at Different Channel Aspect Ratios, Reynolds Numbers, and Temperature Ratios, (P. M. Ligrani, G. I. Mahmood, M. Hill, D. Nelson), in preparation for 46th ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, New Orleans, Louisiana, June 4-7, 2001, and the ASME Transactions-Journal of Turbomachinery, 2000.

(5) Transonic Film Cooling Mixing Loss Investigations.

This experimental study investigates the effects of film cooling on mixing losses from symmetric turbine airfoils in transonic flow. The University of Utah Transonic Wind Tunnel (TWT), located in the Department of Mechanical Engineering, is employed for the study. This blow-down facility has excellent performance characteristics, with uniform flow characteristics at the test section entrance, and steady testing times as long as 50 seconds. Different film cooling hole configurations are tested, including configurations with shaped holes. Freestream Mach numbers along the length of the airfoil range from 0.4 to 1.18, and exactly match the distribution on operating turbine airfoils. Using the secondary injection system, a range of film cooling flow rates, blowing ratios, and density ratios are investigated. Wakes losses, total and static pressure profiles, and Mach number profiles are measured downstream of the blades using pressure probes, especially suited for this application.

Recent publications:

1. Transonic Aerodynamic Losses Due to Turbine Airfoil, Suction Surface Film Cooling (D. J. Jackson, K. L. Lee, P. M. Ligrani, P. D. Johnson, and F. O. Soechting), Paper 99-GT-260, 44th ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, Indianapolis, Indiana, June 7-10, 1999.

2. Transonic Aerodynamic Losses Due to Turbine Airfoil, Suction Surface Film Cooling (D. J. Jackson, K. L. Lee, P. M. Ligrani, and P. D. Johnson), ASME Transactions-Journal of Turbomachinery, Vol. 122, No. 2, pp. 317-326, April 2000.

(6) Transonic Film Cooling Surface Effectiveness Investigations.

In this experimental study, spatially-resolved distributions of the adiabatic film cooling effectiveness are measured downstream of film cooling holes on the surface of symmetric turbine airfoils in transonic flow. The University of Utah Transonic Wind Tunnel (TWT), located in the Department of Mechanical Engineering, is employed for the study. Different film cooling hole configurations are tested, including configurations with shaped holes. Freestream Mach numbers along the length of the airfoil range from 0.4 to 1.18, and exactly match the distribution on operating turbine airfoils. The Mach number at the exits of the film cooling holes is 1.07. Using the secondary injection system, a range of film cooling flow rates, blowing ratios, and density ratios are investigated. Film cooling effectiveness distributions are measured along acrylic inserts installed along airfoil surfaces. Infrared thermography is employed to measure surface temperature distributions (used to determine adiabatic effectiveness magnitudes), when used with in situ calibration procedures, thermocouples, and digital image processing. The infrared camera views test surfaces as transonic flow passes through the test section through a zinc selenide window, especially constructed so that one surface contour exactly matches the nominal contour on the outer wall of the test section.

Recent publications:

1. Transonic Film Cooling From Shaped Holes on the Suction Surface of a Turbine Airfoil, (T. Fukukawa, P. M. Ligrani), in preparation for 46th ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, New Orleans, Louisiana, June 4-7, 2001, and the ASME Transactions-Journal of Turbomachinery, 2000.

2. Shock Wave - Film Cooling Interactions In Transonic Flows, (P. M. Ligrani, C. Saumweber, A. Schulz, S. Wittig), in preparation for 46th ASME Gas Turbine and Aeroengine Technical Congress, Exposition, and Users Symposium, New Orleans, Louisiana, June 4-7, 2001, and the ASME Transactions-Journal of Turbomachinery, 2000.

(7) Transitional Flows in Curved Channels.

Flows in curved channels and ducts are of interest both because of the opportunities they provide for fundamental investigations of transitional phenomena, and because of the diversity of their practical applications. For the former, environments are offered to study centrifugal instabilities which are different from boundary layers and Taylor-Couette passages. In contrast to these weakly non-parallel open flows and parallel closed flows, channels and ducts are categorized as parallel open flows. Practical applications include a variety technological and physical problems such as heat exchangers, internal turbine blade cooling passages, passages in biological systems, and ducting in internal combustion engines, among others.

The present work is focused on curved channel heat transfer and energy transport. This topic is also of fundamental interest regarding both the effects of transition on heat transfer, as well as the effects of heat transfer on transition. Results are obtained at Dean numbers from 50 to 1100 which include laminar channel flow, laminar flow with Dean vortex pairs, flow with secondary instabilities, channel flow with local regions of augmented turbulence, and turbulent channel flow. At lower Dean numbers, a new procedure is applied to deduce forced convection Nusselt numbers from Nusselt numbers measured in a mixed convection environment with relatively weak buoyancy.

Recent publications:

1. Flow Visualization of Dean Vortices in a Curved Channel with 40 to 1 Aspect Ratio (P. M. Ligrani and R. D. Niver), Physics of Fluids, Vol. 31, No. 12, pp.3605-3617, December 1988.

2. Features of Wavy Vortices in a Curved Channel from Experimental and Numerical Studies (P. M. Ligrani, W. H. Finlay, W. A. Fields, S. J. Fuqua, and C. S. Subramanian), Physics of Fluids A, Vol. 4, No. 4, pp. 695-709, April 1992.

3. Surface Heat Transfer and Flow Properties of Vortex Arrays Induced Artificially and From Centrifugal Instabilities (C. S. Subramanian, P. M. Ligrani and M. F. Tuzzolo), International Journal of Heat and Fluid Flow, Vol. 13, No. 3, pp. 210-223, September 1992.

4. Splitting, Merging and Spanwise Wavenumber Selection of Dean Vortex Pairs (P. M. Ligrani, J. E. Longest, M. R. Kendall, and W. A. Fields), Experiments in Fluids, Vol. 18, No. 1, pp. 41-58, December 1994.

5. Effects of Dean Vortex Pairs on Surface Heat Transfer in Curved Channel Flow (P. M. Ligrani, S. Choi, A. R. Schallert, and P. Skogerboe), International Journal of Heat and Mass Transfer, Vol. 39, No. 1, pp. 27-37, January 1996.

6. Mixed Convection in Straight and Curved Channels With Buoyancy Orthogonal to the Forced Flow (P. M. Ligrani and S. Choi), International Journal of Heat and Mass Transfer, Vol. 39, No. 12, pp. 2473-2484, August 1996.

7. Heat Transfer in Curved and Straight Channels With Transitional Flow (C. R. Hedlund and P. M. Ligrani), International Journal of Heat and Mass Transfer, Vol. 41, No. 3, pp. 563-573, February 1998.

8. Transition to Turbulent Flow in Curved and Straight Channels With Heat Transfer at High Dean Numbers (P. M. Ligrani and C. R. Hedlund), International Journal of Heat and Mass Transfer, Vol. 41, No. 12, pp. 1739-1748, June 1998.

9. A Study of Dean Vortex Development and Structure in a Curved Rectangular Channel With Aspect Ratio of 40 at Dean Numbers Up to 430 (P. M. Ligrani), NASA Contract Report 4607, Army Research Laboratory Contractor Report ARL-CR-144, Vehicle Propulsion Directorate, U. S. Army Research Laboratory, and NASA-Lewis Research Center, Cleveland, Ohio, July 1994.

10. A Study of Heat Transfer in a Curved Rectangular Channel Including the Effects of Dean Vortex Pairs and Transition to Turbulent Flow (P. M. Ligrani), unpublished report, November 1996.

11. Effects of Dean Vortex Pairs and Transition to Turbulence on Surface Heat Transfer in a Curved Channel (P. M. Ligrani and C. R. Hedlund), 9th Couette-Taylor Workshop, University of Colorado, Boulder, Colorado, August 7-10, 1995.

12. Transient, Oscillatory and Steady Characteristics of Dean Vortex Pairs in a Curved Rectangular Channel (P. M. Ligrani), Ordered and Turbulent Patterns in Taylor-Couette Flow (Editors: C. David Andereck and F. Hayot) , NATO Advanced Science Institutes Series Volume, Series B: Physics Vol. 297, Plenum Press Publishing Corporation, pp. 281-288, October 1992.

13. Effects of Curvature on Heat Transfer in Channels and Swirl Chambers (P. M. Ligrani), Recent Research Developments in Heat, Mass, & Momentum Transfer, Vol. 2-1999, (Editor: S. G. Pandalai), Research Signpost Publishers, Vol. 2, pp. 171-183, 1999.

(8) Investigations of Continuous SPLITT Fractionation (CSF).

Continuous SPLITT Fractionation (CSF) employs a thin, ribbon-like channel (300-800 µm in width with aspect ratio>100) with splitter plates oriented in streamwise/spanwise planes located at each end of the channel. These are designed to split or separate two different flow streams. CSF is unique as it utilizes a powerful and generic strategy for rapid and continuous separation of particles in the size range of 0.1 µm to 100 µm across the thin and precisely controlled flow laminae. By applying different kinds of fields or driving forces across the transverse direction of the cell, particulate as well as macromolecular particles can be separated. This techniques is not limited by a small load capacity and is capable of operating in a continuous mode. This characteristic is critical for many analytical studies which require larger sample amounts for subsequent analysis.

To date, CSF has been employed with a variety of different fields/gradients (imposed in the transverse direction) such as gravitational, centrifugal, electrical, crossflow, concentration, and hydrodynamic lift forces. For particles larger than 1 µm, a gravitational field provides good separation. CSF systems are advantageous for many analytical and preparative applications because of its continuous high speed, high resolution, gentle processing, theoretical tractability, simplicity, and its requirement of a relatively inexpensive infrastructure for operation. With the possibility of a scale-up, it is envisioned as an effective sample preparative tool for processing industrial, environmental, and biological samples with sample throughput rates ranging from a few grams to kilograms per hour.

Present work is focused on evaluating the limitations on performance and resolution in a thin SPLITT Fractionation channel which result when three-dimensionality from unstable density stratification is present. Lower Reynolds numbers (Re<2) than other known investigations of shear layer/density gradient interactions are employed. The effects of the flowrate ratio and density gradient magnitude on resolution are examined. The overall goal is to determine flow conditions where the operation of CSF is stable and can be optimized. Confirmation of good CSF performance within the stable region is illustrated by successful separations of different samples of solid particles using a variety of fractionation schemes.

Recent publications:

1. Resolution Deterioration and Optimal Operating Conditions in Centrifugal SPLITT Fractionation. Part I: Stable Density Gradients (S. Gupta, P. M. Ligrani, M. N. Myers, J. C. Giddings), Journal of Microcolumn Separations, Vol. 9, No. 3, pp. 213-223, March 1997.

2. Resolution Deterioration and Optimal Operating Conditions in Centrifugal SPLITT Fractionation. Part II: Unstable Density Gradients (S. Gupta, P. M. Ligrani, M. N. Myers, J. C. Giddings), Journal of Microcolumn Separations, Vol. 9, No. 6, pp. 521-532, June 1997.

3. Investigations of Performance Characteristics Including Limitations Due to Flow Instabilities in Continuous SPLITT Fractionation (S. Gupta, P. M. Ligrani, and J. C. Giddings), Separation Science and Technology, Vol. 32, No. 10, pp. 1629-1655, October 1997.

4. Onset and Effects of Instabilities From Unstable Stratification of Density on Mass Transfer in Channel Shear Layers at Low Reynolds Numbers (P. M. Ligrani, S. Gupta, and J. C. Giddings), International Journal of Heat and Mass Transfer, Vol. 41, No. 12, pp. 1667-1679, June 1998.

5. Characteristics of Flow Instabilities From Unstable Stratification of Density in Channel Shear Layers at Low Reynolds Numbers (S. Gupta, P. M. Ligrani, and J. C. Giddings), International Journal of Heat and Mass Transfer, Vol. 42, No. 6, pp. 1023-1036, March 1999.

(9) Experimental Techniques.

Recent publications:

1. Subminiature Hot-Wire Sensors: Development and Use (P. M. Ligrani and P. Bradshaw), Journal of Physics E-Scientific Instruments, Vol. 20, No. 3, pp. 323-332, March 1987.

2. Spatial Resolution and Measurement of Small-Scale Turbulence in the Viscous Sublayer Using Subminiature Hot-Wire Probes (P. M. Ligrani and P. Bradshaw), Experiments in Fluids, Vol. 5, No. 6, pp. 407-417, August 1987.

3. Spatial Resolution and Downwash Velocity Corrections for Multiple-Hole Pressure Probes in Complex Flows (P. M. Ligrani, B. A. Singer and L. R. Baun), Experiments in Fluids, Vol. 7, No. 6, pp. 424-426, 1989.

4. Fabrication and Testing of Subminiature Multi-Sensor Hot-Wire Probes (P. M. Ligrani, R. V. Westphal and F. R. Lemos), Journal of Physics E-Scientific Instruments, Vol. 22, No. 4, pp. 262-268, April 1989.

5. Miniature Five-Hole Pressure Probe for Measurement of Three Mean Velocity Components in Low Speed Flow (P. M. Ligrani, B. A. Singer and L. R. Baun), Journal of Physics E-Scientific Instruments, Vol. 22, No. 10, pp. 868-876, October 1989.

6. Subminiature Hot-Wire Probes (R. V. Westphal, P. M. Ligrani and F. R. Lemos), NASA Tech Briefs Journal, Vol. 13, No. 10, pp.40-41, October 1989.

7. An Infrared Thermography Imaging System for Convective Heat Transfer Measurements in Complex Flows (S. R. Sargent, C. R. Hedlund, and P. M. Ligrani), Measurement Science and Technology, Vol. 9, No. 12, pp. 1974-1981, December 1998.

8. Flow Visualization and Flow Tracking as Applied to Turbine Components in Gas Turbine Engines (P. M. Ligrani), Measurement Science and Technology (special topical issue), Vol. 11, No. 7, pp. 992-1006, July 2000.

TEACHING ACTIVITIES:

1. Courses taught, University Of Utah:

Winter Quarter, 1993, ME562, Thermal Systems Design, 29 students.
Spring Quarter, 1993, ME665, Advanced Heat Transfer II, 11 students.
Fall Quarter, 1993, ME360, Engineering Thermodynamics, 34 students.
Winter Quarter, 1994, ME562, Thermal Systems Design, 17 students.
Winter Quarter, 1994, ME665, Advanced Heat Transfer II, 17 students.
Spring Quarter, 1994, ME362, Power Thermodynamics, 31 students.
Fall Quarter, 1994, ME360, Engineering Thermodynamics, 69 students.
Winter Quarter, 1995, ME362, Power Thermodynamics, 48 students.
Winter Quarter, 1995, ME665, Advanced Heat Transfer II, 18 students.
Spring Quarter, 1995, ME562, Thermal Systems Design, 8 students.
Fall Quarter, 1995, ME360, Engineering Thermodynamics, 46 students.
Winter Quarter, 1996, ME362, Power Thermodynamics, 26 students.
Winter Quarter, 1996, ME665, Advanced Heat Transfer II, 9 students.
Spring Quarter, 1996, ME562, Thermal Systems Design, 12 students.
Fall Quarter, 1996, ME360, Engineering Thermodynamics, 59 students.
Winter Quarter, 1997, ME362, Power Thermodynamics, 51 students.
Winter Quarter, 1997, ME665, Advanced Heat Transfer II, 12 students.
Spring Quarter, 1997, ME562, Thermal Systems Design, 13 students.
Fall Quarter, 1997, ME364, Heat Transfer, 47 students.
Winter Quarter, 1998, ME362, Power Thermodynamics, 40 students.
Winter Quarter, 1998, ME665, Advanced Convective Heat Transfer, 13 students.
Spring Quarter, 1998, ME562, Thermal Systems Design, 11 students.
Spring Quarter, 1998, ME652, Gas Dynamics, 9 students.
Autumn Semester, 1998, ME3600, Thermodynamics II, 23 students.
Spring Semester, 1999, ME7660, Advanced Convection Heat Transfer, 10 students.
Spring Semester, 1999, ME3600, Thermodynamics II, 40 students.
Autumn Semester, 1999, ME5810 / 6810, Thermal Systems Design, 9 students.
Autumn Semester, 1999, ME3600, Thermodynamics II, 39 students.
Autumn Semester, 2000, ME3600, Thermodynamics II, 41 students.

2. Graduate students supervised (completed degrees), University Of Utah:

1. Seunghyun Choi, Master of Science, "A Study of Surface Heat Transfer in a Curved Channel at Low Dean Numbers," March 1995.
2. John Michael Cuthrell, Master of Science, "A Study of the Effects of Bulk Flow Pulsations on Film Cooling," September 1995.
3. Ruoming Gong, Doctor of Philosophy, "Structure of Film Cooled Turbulent Boundary Layers Subject to Bulk Flow Pulsations," July 1996.
4. Carl Ragnar Hedlund, Master of Science, "Effects of Transition to Turbulence and Dean Vortex Pairs on Surface Heat Transfer at Moderate and High Dean Numbers," December 1996.
5. Troy Babinchak, Master of Science, "Flow Behavior, Including Development and Structure of Gortler Vortices, in a Simple Swirl Chamber." March 1997.
6. Rajan Thambu, Master of Science, "Flow Phenomena, Including Gortler Vortices, in a Simple Swirl Chamber With Controlled Inlet Forcing." June 1997.
7. Supriya Gupta, Doctor of Philosophy, "Investigation of Resolution Deteriorating Factors and New Applications in Continuous SPLITT Fractionation." Degree through Department of Chemical and Fuels Engineering. August 1997.
8. Donald Owen Brock, Master of Science, "Spatial Development of Splitting, Merging, and Spanwise Wave Number Selection of Dean Vortex Pairs." June 1998.
9. Scott Robert Sargent, Master of Science, "Investigations of Transonic Film Cooling With Shaped and Round Holes." July 1998.
10. Kyle Leon Lee, Master of Science, "Aerodynamic Losses and Discharge Coefficients for a Transonic Turbine Blade With Film Cooling." July 1998.
11. Dale Jay Jackson, Master of Science, "Aerodynamic Mixing Losses and Discharge Coefficients Due to Film Cooling From a Symmetric Turbine Airfoil in Transonic Flow." August 1998.
12. Carl Ragnar Hedlund, Doctor of Philosophy, "Heat Transfer and Flow Behavior in a Swirl Chamber With Helical Flow." September 1998.
13. Clint Bell, Master of Science, "Effects of Bulk Flow Pulsations on Film Cooling with Different Density Ratios." October 1998.
14. Dustin Birch, Master of Science, "Adiabatic Effectiveness and Shock Wave Effects for Conical Diffused Film Cooling Holes." January 2000.
15. Michael L. Hill, Master of Science, "The Effect of Spherically Shaped Surface Cavities on Internal Cooling of Gas Turbine Blades." December 2000.
16. Mounir Zaki Sabbagh, Master of Science, "The Effect of Dimple Surface Cavities on Heat Transfer Augmentation for the Internal Cooling of Gas Turbine Blades," May 2000.
17. Donna Nelson, Master of Science, "Visualization of Flow Structure Above a Dimpled Surface," December 2000.

3. Undergraduate student projects and theses supervised, University Of Utah:

1. Johann Adam, "Development of a Heat Transfer Test Surface for Convective Heat Transfer Studies Applied to Gas Turbine Engines."
2. Hector Lora, "Continued Development of an Experimental Facility for Convective Heat Transfer Studies Applied to Gas Turbine Engines."
3. Johann Adam, "Documentation and Study of Imposed Flow Pulsations as Applied to Gas Turbine Engines."
4. Carl Hedlund, "Heat Transfer In a Curved Channel With Transitional and Turbulent Flows." ?
5. Chris Brown, "Investigation of Bulk Flow Pulsations and Film Cooling as Applied to Gas Turbine Engines."
6. Carl Hedlund, "Continued Study Of Heat Transfer In a Curved Channel With Transitional and Turbulent Flows."
7. Chris Brown, "Continued Investigation of Bulk Flow Pulsations and Film Cooling as Applied to Gas Turbine Engines."??
8. Don Brock, "Local Heat Transfer and Flow Visualization in a Curved Channel With Dean Vortex Pairs."
9. Hector Lora, "Curved Channel Studies."
10. Don Brock, "Continued Study of Local Heat Transfer and Flow Visualization in a Curved Channel With Dean Vortex Pairs."
11. Axel Eduardo Soto, "Flow Studies in a Curved Channel."
12. Craig Kilbane, "Design and Development of a Device to Produce Large Amplitude Bulk Flow Pulsations in a Wind Tunnel."
13. Wade Hull, "Design, Construction, Instrumentation, and Qualification of a Test Surface to Measure Heat Transfer Coefficients and Local Magnitudes of Film Cooling Effectiveness."
14. Kameron Leang, "Design, Construction, Instrumentation, and Qualification of a Test Surface to Measure Heat Transfer Coefficients and Local Magnitudes of Film Cooling Effectiveness."
15. Anne Tracy, "Design, Construction, Instrumentation, and Qualification of a Test Surface to Measure Heat Transfer Coefficients and Local Magnitudes of Film Cooling Effectiveness."
16. Craig Norton, "Investigation of the Effects of Bulk Flow Pulsations on Heat Transfer and Film Cooling Effectiveness in a Film Cooled Boundary Layer."
17. Don Brock, "Continued Flow Visualization Investigations in a Curved Channel With Dean Vortex Pairs."
18. Axel Eduardo Soto, "Continued Curved Channel Studies."
19. Corona Ngatuvai, "Study of Surface Heat Transfer Produced by Vortex Pairs Using Liquid Crystal Thermography."
20. Wade Hull, "Continued Investigation of Bulk Flow Pulsations and Film Cooling as Applied to Gas Turbine Engines."
21. Paul McMullin, "Transonic Film Cooling Mixing Loss Investigations as Applied to Gas Turbine Engines."
22. Lance Richman, "Transonic Film Cooling Mixing Loss Investigations as Applied to Gas Turbine Engines."
23. Glen West, "20 Ton Preconditioned Air Unit Design."
24. Mauro Oliveira, "Development of an Experimental Facility to Measure Heat Transfer in a Swirl Chamber."
25. Corey Pascal, "Development of an Experimental Facility to Measure Heat Transfer in a Swirl Chamber."
26. Craig M. Norton, Bachelor of Science (Honors Baccalaureate Degree), "Investigation of Heat Transfer and Film Effectiveness Beneath Film Cooled Boundary Layers," May 1996.
27. Wade A. Hull, Bachelor of Science (Honors Baccalaureate Degree), "Film Effectiveness and Heat Transfer Beneath Film Cooled Boundary Layers Subject to Bulk Flow Pulsations," April 1997.
28. Mike Hill, "Heat Transfer Augmentation On A Flat Surface With Dimples."
29. Scott Snider, "Development of Experimental Facilities and Data Acquisition Systems for Investigation of a Unique Internal Cooling Scheme for a Gas Turbine Blade."
30. Mounir Sabbagh, "Surface Adiabatic Film Effectiveness Measurements on a Film Cooled Turbine Blade in Transonic Flow."
31. Donna Nelson, "Investigation of Flow Structure Above a Flat Surface With Dimples."
32. Dale Clark, "Transonic Film Cooling Investigations."
33. Dustin Breuning, "Transonic Film Cooling Investigations."
34. Gary Kessler, "Effects of Pulsations on Film Cooling as Applied to Gas Turbine Engines."
35. Bill Trappett, "Effects of Pulsations and Shock Waves on Film Cooling as Applied to Gas Turbine Engines."
36. Dale Clarke, "Investigation of Film Cooling Effectiveness in Transonic Flow."
37. Ron Simonsen, "Investigation of Aerodynamic Losses Due to Turbine Airfoil, Film Cooling in Transonic Flow."
38. Jamie McCullough, "Investigation of Aerodynamic Losses Due to Turbine Airfoil, Film Cooling in Transonic Flow."
39. Blaine Hanson, "Adiabatic Film Cooling Effectiveness Investigations on Transonic Turbine Airfoils With Augmented Turbulence Intensity."
40. Curtis Cottrell, "Adiabatic Film Cooling Effectiveness Investigations on Transonic Turbine Airfoils With Augmented Turbulence Intensity."
41. Zed Kato, "Effects of Bulk Flow Pulsations on Vortex Structures Produced by Film Cooling."
42. Chris Clayton, "Investigations of Film Cooling on a Transonic Turbine Airfoil."
43. Erica Graves, "Analyses and Processing of Experimental Data From Film Cooling Investigations."
44. Ariel Fershtut, "Investigations of Film Cooling on a Transonic Turbine Airfoil."
45. Jacob Kingston, "Investigations of Internal Cooling Techniques for Turbine Airfoils."
46. Cordell Post, "Flow Visualization of Film Cooling Flows From Shaped Holes Subject to Bulk Flow Pulsations."
47. Bill Trappett, "Investigations of Internal Cooling Techniques for Turbine Airfoils."
48. Jeff Harrison, "Measurement of Flow Characteristics with a Miniature Five-Hole Pressure Probe."
49. Jeff Harrison, "Investigations of Roughness Effects and Cooling Schemes For Turbine Airfoils as Applied to Gas Turbine Engines."

4. Graduate students supervised, U. S. Naval Postgraduate School:

1. A. Ramsey, Master of Science, "A Study of Film Cooling Downstream of One and Two Rows of Holes Oriented in Spanwise/Normal Planes," September 1992.
2. A. R. Schallert, Master of Science, "A Study of Nusselt Number Distributions In a Curved Channel," June 1992.
3. S. M. Jackson, Master of Science, "Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single Rows and Two Staggered Rows of Film-Cooling Holes With Simple and Compound Angles," December 1991.
4. J. M. Wigle, Master of Science, "Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single nd Double Rows of Film-Cooling Holes With Compound Angles," December 1991.
5. B. W. Payne, Master of Science, "A Study of Spatially-Averaged Nusselt Number Distributions in a Curved Channel with 40 to 1 Aspect Ratio for Dean Numbers from 175 to 375," September 1991.
6. S. J. Fuqua, Master of Science, "Study of the Transition to Turbulence Within a Curved Rectangular Channel with 40 to 1 Aspect Ratio," September 1991.
7. M. R. Kendall, Mechanical Engineer, "Effects of Centrifugal Instabilities on Laminar/Turbulent Transition in Curved Channels With 40 to 1 Aspect Ratios," June 1991.
8. S. Ciriello, Master of Science, "Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film Cooling Holes With Simple and Compound Angles," March 1991.
9. B. J. Smith, Master of Science, "Study of Transition Phenomena in a Straight Channel With 40 to 1 Aspect Ratio With and Without Imposed Pulsations, Part Two: Reynolds Number Surveys," March 1991.
10. D. S. Morrow, Master of Science, "Transition Phenomena in a Straight Channel With a 40 to 1 Aspect Ratio With and Without Imposed Pulsations, Part One: Near-Wall and Central Region Profiles," March 1991.
11. W. A. Fields, Mechanical Engineer, "Study of the Effects of Centrifugal Instabilities on Flow in a 40 to 1 Aspect Ratio Rectangular Curved Channel for Dean Numbers from 35 to Fully Turbulent Conditions," December 1990.?
12. D. T. Bishop, Master of Science, "Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single and Double Rows of Film-Cooling Holes with Compound Angles," September 1990.?
13. S. W. Mitchell, Master of Science, "The Effects of Embedded Vortices on Heat Transfer in a Turbulent Boundary Layer with Film Cooling from Holes with Compound Angles," September 1990.
14. H. E. Koth, Master of Science, "Effects of Imposed Bulk Flow Oscillations at 1, 2, 3 and 4 Hz on Transition in a Straight Channel with 40 to 1 Aspect Ratio," June 1990.
15. P. E. Skogerboe, Master of Science, "Local and Spatially Averaged Heat Transfer Distributions in a Curved Channel with 40 to 1 Aspect Ratio for Dean Numbers from 50 to 200," March 1990.
16. W. D. Doner, Master of Science, "Further Studies of Turbulence Structure Resulting from Interactions Between Embedded Vortices and Wall Jets at High Blowing Ratios," December 1989.
17. T. M. Coumes, Master of Science, "Effects of 1 Hz Imposed Bulk Flow Unsteadiness on Laminar/Turbulent Transition in a Straight Channel," December 1989.
18. F. J. Greco, Master of Science, "Effects of 2 Hz Imposed Bulk Flow Unsteadiness on Laminar/Turbulent Transition in a Straight Channel," December 1989.
19. P. Kaisuwan, Master of Science, "Effects of Vortex Circulation on Injectant from a Single Film-Cooling Hole and a Row of Film-Cooling Holes in a Turbulent Boundary Layer, Part 2: Injection Beneath the Vortex Upwash," December 1989.
20. R. E. Hughes, Master of Science, "Development, Qualification and Measurements in Two Curved Channels with 40 to 1 Aspect Ratio," September 1989.
21. M. F. Tuzzolo, Mechanical Engineer, "Study of Vortex Arrays Induced Artificially and from Centrifugal Instabilities," June 1989.
22. J. M. Longest, Master of Science, "Flow Visualization Studies in (1) a Curved Rectangular Channel with 40 to 1 Aspect ratio and (2) a Straight Channel with Bulk Flow Unsteadiness," June 1989.
23. J. G. Green, Master of Science, "Turbulence Structure Resulting from Interactions Between an Embedded Vortex and Wall Jet," June 1989.
24. D. W. Craig, Master of Science, "Effects of Vortex Circulation on Injectant from a Single Film-Cooling Hole and a Row of Film-Cooling Holes in a Turbulent Boundary Layer, Part 1: Injection Beneath the Vortex Downwash," June 1989.
25. D. W. Bella, Master of Science, "Flow Visualization of Time-Varying Structural Characteristics of Dean Vortices in a Curved Channel," December 1988.
26. G. E. Schwartz, Master of Science, "Control of Embedded Vortices Using Wall Jets," September 1988.
27. L. R. Baun, Mechanical Engineer, "Development and Structural Characteristics of Dean Vortices in a Curved Rectangular Channel with 40 to 1 Aspect Ratio," September 1988.
28. W. W. Williams, Master of Science, "Effects of an Embedded Vortex on a Single Film-Cooling Jet in a Turbulent Boundary Layer," June 1988.
29. A. Ortiz, Mechanical Engineer, "The Thermal Behavior of Film-Cooled Turbulent Boundary Layers as Affected by Longitudinal Vortices," September 1987.?
30. R. D. Niver, Master of Science, "Structural Characteristics of Dean Vortices in a Curved Channel," June 1987.
31. D. L. Evans, Master of Science, "Study of Vortices Embedded in Boundary Layers with Film Cooling," March 1987.
32. M. A. Siedband, Master of Science, "A Flow Visualization Study of Laminar/Turbulent Transition in a Curved Channel," March 1987.
33. S. L. Joseph, Mechanical Engineer, "Effects of Embedded Vortices on Heat Transfer in Film-Cooled Turbulent Boundary Layers," December 1986.
34. A. F. Walz Jr., Master of Science, "Effects of Variable Properties in Film Cooled Turbulent Boundary Layers," March 1986.

5. Graduate students supervised, Von Karman Institute For Fluid Dynamics:

1. M. Pezzani, Von Karman Institute Diploma, "Investigation of Heat Transfer Rates on a Film Cooled Flat Plate with One and Two Rows of Injection Holes," von Karman Institute Project No. 1982-24, June 1982.
2. J. Poco, Von Karman Institute Diploma, "Laser Doppler Velocity Measurements in the Radial Vaneless Diffuser of a Centrifugal Water Pump," von Karman Institute Project No. 1981-23, June 1981.
3. M. Lotzerich, Von Karman Institute Diploma, "Heat Transfer Measurements on a Gas Turbine Blade at Low Incidence Angles," von Karman Institute Project No. 1981-27, June 1981.
4. A. Ongoren, Von Karman Institute Diploma, "Heat Transfer on the Endwall of a Turbine Cascade with Film Cooling," von Karman Institute Project No. 1981-19, June 1981.
5. C. Camci, Von Karman Institute Diploma, "Investigation of Heat Transfer Rates on a Film Cooled Flat-Plate With and Without a Pressure Gradient," von Karman Institute Project No. 1980-12, June 1980.

OTHER UNIVERSITY OF UTAH ACTIVITIES.

• Graduate Seminar Coordinator, Department of Mechanical Engineering, University of Utah, September 1992 - June 1993.
• Member, Mechanical Engineering Design Search Committee, Department of Mechanical Engineering, University of Utah, September 1992 - April 1993.
• Member, College Council, College of Engineering, University of Utah, October 1993 - October 1996.
• Member, Graduate Committee, Department of Mechanical Engineering, University of Utah, September 1994 - May 1999.
• Faculty Advisor, Pi Tau Sigma Honorary Fraternity, December 1994 - Present.
• Chairman, Mechanical Engineering Thermal Fluids and Energy Systems Search Committee, Department of Mechanical Engineering, University of Utah, October 1995-May 1996.
• Director-Graduate Admissions, and Chairman-Graduate Committee, Department of Mechanical Engineering, University of Utah, June 1996-September 1997.
• RPT Alumni Surveys and Survey Evaluations, Department of Mechanical Engineering, University of Utah, June 1997-December 1997.
• Member, Tenured Faculty Review Committees, Department of Mechanical Engineering, University of Utah, February 1998-April 1998.
• Chairman and Member, Fellowship / Scholarship & Honors Committee, Department of Mechanical Engineering, May 1999 - Present.
• RPT Alumni Surveys and Survey Evaluations, Department of Mechanical Engineering, University of Utah, June 1999-December 1999.
• Member, College Scholarship Committee, College of Engineering, University of Utah, May 1999 - Present.
• Member, Goldwater Scholarship Selection Committee, University of Utah, September 1999 - November 1999.
• Member, Academic Evaluation and Standards Committee, University of Utah, August 1, 2000 - September 30, 2003.

OTHER PROFESSIONAL ACTIVITIES:

1. International professional societies:

• ASME, American Society of Mechanical Engineering, July 1985 - Present.
• IGTI, International Gas Turbine Institute, July 1985 - Present.

2. International professional society committees:

• ASME, American Society of Mechanical Engineering, K-14 Gas Turbine Heat Transfer Committee. December 1986-Present
• IGTI, International Gas Turbine Institute Heat Transfer Committee. December 1986-Present.

EXTERNAL ACTIVITIES:

• Family, including wife, Sandra, and daughter, Janelle, born 1994.
• Four cats. Breeds: (i) Absynnian, (ii) Maine Coon Cat, (iii) Birman, (iv) American Short-Hair.
• Basement renovation.
• Snow skiing
• Skuba diving
• Travel, especially to Europe and the Far East. 

Visualized instantaneous flow images in a cross-sectional plane of a curved channel showing the merging and splitting of adjacent vortex pairs. Images are recorded at a Dean number of about 100 at a location 105 degrees from the start of curvature. Time varying images show dramatic changes to vortex pairs, where each vortex pair is identified by a "mushroom-shaped" smoke pattern. Horizontal extent of each image=4.21 channel heights. Vertical extent of each image=1.0 channel height. Channel height=1.27 cm. Results obtained in the Convective Heat Transfer Laboratory, University of Utah, under the supervision of Professor Phil Ligrani.

Visualized instantaneous flow images in a cross-sectional plane of a curved channel showing the merging of two vortex pairs together. Images are recorded at a Dean number of 100 at a location 105 degrees from the start of curvature. Time interval between sequential images is 1 / 30th of a second (or 0.0333 seconds). Horizontal extent of each image=4.21 channel heights. Vertical extent of each image=1.0 channel height. Channel height=1.27 cm.

Visualized instantaneous flow images in a cross-sectional plane of a swirl chamber with helical flow showing highly unsteady, highly distorted vortex pairs of different size as they interact with each other. Images are recorded at a Reynolds number of 5440 at a location 2.97 meters and 130 degrees from the swirl chamber inlet. Time interval between sequential images is 1 / 10th of a second (or 0.10 seconds). Horizontal extent of each image=0.52 inner diameters. Vertical extent of each image=0.21 inner diameters. Swirl chamber inner diameter=0.597 m.