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Deflected Jet Experiments in a Turbulent Combustor Flowfield

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Deflected Jet Experiments in a Turbulent Combustor Flowfield DEFLECTED JET EXPERIMENTS IN A TURBULENT COMBUSTOR FLOWFIELD By GARY BRUCE FERRELL 11 Bachelor of Science in Mechanical Engineering Oklahoma State University Stillwater, Oklahoma 1978 Master of Science Oklahoma State University Stillwater, Oklahoma 1980 Submitted to the Faculty of the Graduate College of the Oklahoma State University in partial fulfillment of the requirements for the Degree of DOCTOR OF PHILOSOPHY December, 1984 DEFLECTED JET EXPERIMENTS IN A TURBULENT COMBUSTOR FLOWFIELD Thesis Approved: ii 1218506 ACKNOWLEDGMENTS I wish to express my sincere gratitude to my colleagues and coworkers at Oklahoma State University who assisted me in this project. In particular, I am especially thankful to my major advisor, Dr. David G. Lilley, for his experienced guidance and invaluable help during this undertaking. I am also grateful for the counsel of the other committee members, Dr. John A. Wiebelt, Dr. Jan W. Wagner, Dr. Jerald D. Parker, and Dr. Peter M. Moretti. The assistance of Dr. Richard L. Lowery is also greatly appreciated. Gratitude is due M~. Lawrence H. Ong, Mr. Carl B. McMurry, Mr. Steven L. Mitchell, and Mr. John B. Rohrer for their assistance in constructing various experimental apparata. Gratitude is extended to Ms. Neisa L. Lock for her timely and skillful typing during preparation of this manuscript. Special thanks are due to NASA Lewis Research Center, Grant No. NAG 3-549, technical monitor Dr. James D. Holdeman, and to the School of Mechanical and Aerospace Engineering at Oklahoma State University for the financial support that I have received both during the course of this work and during my graduate studies. I am especially indebted to my parents whose hard work and sacrifices made it possible for me to achieve my educational goals. My mother has provided constant support and encouragement during my endeavors. The wisdom and compassion of my late father shall always be an inspiration to me, and it is to his memory that I dedicate this modest work. iii TABLE OF CONTENTS Chapter Page I. INTRODUCTION 1 1.1 Deflected Turbulent Jets • • • • • . 1 1.2 Combustor Flowfield Phenomena. • • • • • • • • • 1 1.3 Present Study Objectives • • • • • • • • 2 1.4 Outline of the Thesis 3 II. BACKGROUND 5 2.1 Review of Previous Studies in Deflected Turbulent Jets •••••••••••• 5 2.2 Past Work at Oklahoma State University •• 8 III. EXPERIMENTAL FACILITY •••••••· •• 11 3.1 Wind Tunnel ••••••••••••• 11 3.2 Test Section and Dilution Jet 12 3.3 Hot-Wire Instrumentation •• 14 3.4 Calibration Equipment •••••••••• 14 3.5 Data Acquisition and Probe Drive System. 15 IV. MEASUREMENT TECHNIQUES AND ANALYSIS •••••• 17 4.1 Flow Visualization •••••••• 17 4.1.1 Bubble Flow Visualization 17 4.1.2 Smoke Flow Visualization ••.•••• 19 4.1.3 Spark-Gap Flow Visualization 20 4.2 Quantitative Measurements • • • ••• 21 V. RESULTS AND DISCUSSION ••••• 27 5.1 Flow Visualization. • • ••• 27 5.2 Hot-Wire Measurements ••••••••• 30 5.2.1 Jet-to-Crossflow Velocity Ratio R = 2.0 ••••••••••••• 32 5.2.2 Jet-to-Crossflow Velocity Ratio R = 4.0 •••••••••••• 33 5.2.3 Jet-to-Crossflow Velocity Ratio R = 6.0 •••••••••••• 34 5.2.4 Assessment of the Measurements . 35 iv Chapter Page VI. CLOSURE 37 6.1 Conclusions ••••..••..••. 37 6.2 Recommendations for Further Study. 38 REFERENCES . 40 APPENDIX A - TABLES 46 APPENDIX B - FIGURES . 173 v LIST OF TABLES Table Page I. Previous Investigations of Jets in Cross-Flow ••••••• 47 II. Effect of Input Parameters on Turbulence Quantities in the Swirling Flow with cp = 38 deg. at a Represent.ative Flowfield Position (x/D = 1, r/D = 0.25) • • • • • • • • 48 I I I. Time-Mean and Turbulence Data for Jet to Crossflow Velocity Ratio R = 2.0 ••••••••••••• 49 IV. Time-Mean and Turbulence Data for Jet to Crossflow Velocity Ratio R = 4.0 ••••••••••••• . 85 V. Time-Mean and Turbulence Data for Jet to Crossflow Velocity Ratio R = 6.0 ••••••••••••• . 121 VI. Computer Code Listing for Data Acquisition and Probe Control on Apple II • • • • • • • • • • • • • • • 157 VII. Computer Code Listing for Reduction of Hot-Wire Voltages •••••••••••••••••• . 161 vi LIST OF FIGURES Figure Page 1. Typical Axisymmetric Gas Turbine Combustor. 174 2. Schematic of Experimental Facility. 175 3. Test Section Geometry . 176 4. Test Sections . 177 5. Dilution Jet (Photo) . 178 6. The Six Positions and Probe Coordinates . 179 7. The Three-Dimensional Hot-Wire Calibration • . 180 8. Pitch and Yaw Factors as a Function of Hot-Wire Mean Effective Voltage ••••••••••• 181 9. Schematic of Probe Drive . 182 10. Probe Drive Mounted on Test Section (Photo) . 183 11. Schematic of Data Acquisition and Probe Drive System 184 12. Data Acquisition and Probe Drive System (Photo) . 185 13. Bubble Generator and Injection Setup (Photo) . 186 14. Smoke Generator and Injection Setup (Photo) . 187 15. Spark-Gap Equipment Schematic . 188 16. Spark-Gap Equipment (Photo) . 189 17. Smoke Flow Visualization for Jet-to-Crossflow Velocity Ratio R = 2.0, 4.0, 6.0 •••••••••••••• 190 18. Bubble Flow Visualization for Jet-to-Crossflow Velocity Ratio R = 2.0, Swirl Vane Angle$= 0, 45, 70 . 191 19. Bubble Flow Visualization for Jet-to-Crossflow Velocity Ratio R = 4.0, Swirl Vane Angle$= 0, 45, 70 ••• . 192 vii Figure Page 20. Bubble Flow Visualization for Jet-to-Crossflow Velocity Ratio R = 6.0, Swirl Vane Angle~= 0, 45, 70 • • • 193 21. Spark-Gap Flow Visualization for Jet-to-Crossflow Velocity Ratio= 2.0, Swirl Vane Angle ~ = 0, 45, 70 •••••••••••••••• 194 22. Spark-Gap Flow Visualization for Jet-to-Crossflow Velocity Ratio= 4.0, Swirl Vane Angle '= 0, 45, 70 •••••••••••••••• 195 23. Spark-Gap Flow Visualization for Jet-to-Crossflow Velocity Ratio= 6.0, Swirl Vane Angle ~ = 0, 45, 70 ••••••••••••••••• 196 24. Time-Mean and Turbulent Flowfield, R = 2.0, Traverse Angle e = 270 Degrees . • • . • . • • • • . • • . 197 25. Time-Mean and Turbulent Flowfield, R = 2.0, Traverse Angle e = 300 Degrees . • • . • • . • . • 201 26. Time-Mean and Turbulent Flowfield, R = 2.0, Traverse Angle e = 330 Degrees . • • . 205 27. Time-Mean and Tu rbu 1ent Flowfield, R = 2.0, Traverse Angle e = 0 Degrees • . • • . • • • • . • . • 209 28. Time-Mean and Turbulent Flowfield, R = 2.0, Traverse Angle e = 30 Degrees •••••• . 213 29. Time-Mean and Turbulent Flowfield, R = 2.0, Traverse Angle e = 60 Degrees . • . • . 217 30. Time-Mean and Turbulent Flowfield, R = 4.0, Traverse Angle a= 270 Degrees . 221 31. Time-Mean and Turbulent Flowfield, R = 4.0, Traverse Angle e = 300 Degrees . • . • . • . 225 32. Time-Mean and Turbulent Flowfield, R = 4.0, Traverse Angle e = 330 Degrees • . • . • . 229 33. Time-Mean and Tu rbu 1ent Flowfield, R = 4.0, Traverse Angle e = O Degrees . • • . • . • 233 34. Time-Mean and Turbulent Flowfield, R = 4.0, Traverse Angle e = 30 Degrees . • . • . • . • 237 35. Time-Mean and Turbulent Flowfield, R = 4.0, Traverse Angle e = 60 Degrees . • . • • . • 241 viii Figure Page 36. Time-Mean and Turbulent Flowfield, R = 6.0, Traverse Angle e = 270 Degrees • • • • • • . 245 37. Time-Mean and Turbulent Flowfield, R = 6.0, Traverse Angle e = 300 Degrees • • • • • • 249 38. Time-Mean and Turbulent Flowfield, R = 6.0, Traverse Angle e = 330 Degrees •••••••••••••• 253 39. Time-Mean and Turbulent Flowfield, R = 6.0, Traverse Angle e = O Degrees . 257 40. Time-Mean and Turbulent Flowfield, R = 6.0, Traverse Angle e = 30 Degrees . 261 41. Time-Mean and Turbulent Flowfield, R = 6.0, Traverse Angle e = 60 Degrees . 265 42. Jet Centerline Locations for Different Jet-to-Crossflow Velocity Ratios R = 2.0, 4.0, 6.0 . 269 ix NOMENCLATURE A, 8, C calibration constants Ac cross-s~ctional area of crossflow A· cross-sectional area of jet J 0 test section diameter d inlet nozzle diameter d. jet inlet diameter J E hot-wire voltage G pitch factor K yaw factor R jet-to-crossflow velocity ratio RAM random access memory Re Reynolds number V= ( u,v,w) time-mean velocity in facility coordinates (x-, r- a-directions) x,r,a axial, radial, azimuthal coordinates y vertical distance above jet z effective cooling velocity acting on a wire "( z . correlation coefficient (estimated) between cooling zi J velocities swirl vane angle with respect to facility axis a traverse azimuthal angle x Subscripts i ,j summation indices 0 value at inlet to flowfield rms root-mean-squared Superscripts (-) time-mean average ( ) I fluctuating quantity ( "') relative to probe coordinates xi CHAPTER I INTRODUCTION 1.1 Deflected Turbulent Jets Almost all flow phenomena of practical engineering interest are turbulent and do not lend themselves easily to experimental, ana lyti cal or numerical investigation. Deflected turbulent jets are no exception, involving fully three-dimensional flow phenomena. Power plant chimney plumes, cooling holes ejecting air from turbine blades, and the airflow around V/STOL aircraft in· transition flight are examples of deflected turbulent jets. The present study emphasizes lateral injected jets into tubular cross-flow which may also possess swirl - a situation occurring in gas turbine combustion chambers, as seen in Figure 1, and a more complicated example of fully 3-D flowfields. When the disturbing jet is introduced into the crossflow, vorticity is added to the flow. The circulation of this vorticity stirs the two fluids together as the flow progresses downstream. Gas-turbine combustor designers utilize this mixing phenomenon to promote rapid combustion and evenly mix the products of combustion with cooler injected air, accomplishing this in a compact space. 1 1.2 Combustor Flowfield Phenomena High-intensity combustion takes place in gas turbine combustion chambers2• Whereas most fuel burning takes place in the primary zone, 1 2 the secondary zone is where combustion is almost completed, and the dilution zone is where further temperature reduction and uniformity is achieved. In both can and annular combustors, lateral jets of cooler air through round holes penetrate the flowfield. Some of these jets amalgamate with the swirl-induced central recirculation region of the primary zone and provide sufficient additional air for stoichiometric conditions.
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