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COMBUSTION CHARACTERISTICS of THERMALLY STRESSED HYDROCARBON FUELS by COLIN WILLIAM CURTIS B.S., University of Colorado Colorad

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COMBUSTION CHARACTERISTICS of THERMALLY STRESSED HYDROCARBON FUELS by COLIN WILLIAM CURTIS B.S., University of Colorado Colorad COMBUSTION CHARACTERISTICS OF THERMALLY STRESSED HYDROCARBON FUELS by COLIN WILLIAM CURTIS B.S., University of Colorado Colorado Springs, 2014 A thesis submitted to the Graduate Faculty of the University of Colorado Colorado Springs in partial fulfillment of the requirements for the degree of Master of Science Department of Mechanical and Aerospace Engineering 2016 © 2016 Colin William Curtis ALL RIGHTS RESERVED ii This thesis for Master of Science degree by Colin William Curtis has been approved for the Department of Mechanical and Aerospace Engineering by Dr. Bret Windom, Chair Dr. John Adams Dr. Janel Owens ______________ Date iii Curtis, Colin William (M.S., Mechanical Engineering) Combustion Characteristics of Thermally Stressed Hydrocarbon Fuels Thesis directed by Assistant Professor Bret C. Windom ABSTRACT Liquid propelled propulsion systems, which range from rocket systems to hypersonic scramjet and ramjet engines, require active cooling in order to prevent additional payload requirements. In these systems, the liquid fuel is used as a coolant and is delivered through micro- channels that surround the combustion chambers, nozzles, as well as the exterior surfaces in order to extract heat from these affected areas. During this process, heat exchange occurs through phase change, sensible heat extraction, and endothermic reactions experienced by the liquid fuel. Previous research has demonstrated the significant modifications in fuel composition and changes to the fuel’s physical properties that can result from these endothermic reactions. As a next step, we are experimentally investigating the effect that endothermic reactions have on fundamental flame behavior for real hydrocarbon fuels that are used as rocket and jet propellants. To achieve this goal, we have developed a counter-flow flame burner to measure extinction limits of the thermally stressed fuels. The counter-flow flame system is to be coupled with a high pressure reactor, capable of subjecting the fuel to 170 atm and 873 K, effectively simulating the extreme environment that cause the liquid fuel to experience endothermic reactions. The fundamental flame properties of the reacted fuels will be compared to those of unreacted fuels, allowing us to determine the role of endothermic reactions on the combustion behavior of current hydrocarbon jet and rocket propellants. To quantify the change in transport properties and chemical kinetics of the reacting mixture, simultaneous numerical simulations of the reactor portion of the experiment coupled with a counterflow flame simulation are performed using n-heptane and n-dodecane. iv For my parents and to the memory of John B. Curtis. v ACKNOWLEDGEMENTS The author wishes to sincerely thank the following individuals: Dr. Tom Bruno, for all of his help regarding the high pressure laboratory bench, words cannot express how grateful I am. Dr. Janel Owens, for all of her help with the GC/FID and GC/MS measurements. I would also like to sincerely thank her for agreeing to be on my thesis committee. Dr. John Adams for serving on my thesis committee when he didn’t have to. Dr. Bret Windom for his patience and guidance for the past two years. Brandon Patz, for his friendship and assistance throughout this study. Without your help I would have had a much more difficult time conducting this study. Steve Burke, for being a scientific soundboard and for being there for me when the times were difficult. vi TABLE OF CONTENTS CHAPTER I. INTRODUCTION ........................................................................................................... 1 II. THEORY ...................................................................................................................... 11 III. EXPERIMENTAL METHODS.................................................................................. 25 IV. NUMERICAL METHODOLOGY ............................................................................ 40 V. RESULTS .................................................................................................................... 45 VI. CONCLUSION........................................................................................................... 86 REFERENCES …………………………………………………………………………. 89 APPENDIX A ................................................................................................................... 94 vii LIST OF TABLES TABLE 5.1: This table contains the recorded mass and volume change of reacted n-heptane at a variety of pressures at a constant temperature of 873 K and reactor residence time of 1 minute. ................................................................................................................... 52 5.2: The recorded mass and volume change of reacted n-dodecane at a variety of reactor pressures at a constant temperature of 873 K and reactor residence time of 1 minute. ................................................................................................................................... 55 5.3: The recorded mass and volume change of reacted Jet A at a variety of reactor pressures at a constant temperature of 873 K and reactor residence time of 1 minute. ............ 58 5.4: Experimentally measured thermal decomposition of n-heptane at 170 atm. ............. 60 5.5: Summarized version of the actual species predicted to form during n-heptane pyrolysis at a reactor temperature of 873 K, reactor residence time of 1 minute, and a reactor pressure of 170 atm. .................................................................................................. 62 5.6: Normalized composition resulting from n-heptane pyrolysis at a reactor temperature of 873 K, reactor residence time of 1 minute, and a reactor pressure of 170 atm. This composition was used for all reacted n-heptane PREMIX and OPPDIF simulations. ................................................................................................................................... 62 5.7: Experimentally measured liquid composition following the thermal decomposition of n-dodecane at 170 atm. ............................................................................................. 65 5.8: Summarized version of the actual species predicted to form during n-dodecane pyrolysis at a reactor temperature of 873 K, reactor residence time of 1 minute, and a reactor pressure of 170 atm. ...................................................................................... 67 5.9: Normalized composition resulting from n-dodecane pyrolysis at a reactor temperature of 873 K, reactor residence time of 1 minute, and a reactor pressure of 170 atm. This composition was used for all reacted n-heptane PREMIX and OPPDIF simulations. ................................................................................................................................... 68 5.10: Experimentally measured composition of the liquid Jet A following the thermal decomposition at 100 atm, 873 K and 1 min residence time. ................................. 72 A.1: GC/FID results for thermally stressed n-heptane at a reactor pressure of 10 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................ 96 A.2: GC/FID results for thermally stressed n-heptane at a reactor pressure of 30 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................ 96 A.3: GC/FID results for thermally stressed n-heptane at a reactor pressure of 50 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................ 96 viii A.4: GC/FID results for thermally stressed n-heptane at a reactor pressure of 70 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................ 97 A.5: GC/FID results for thermally stressed n-heptane at a reactor pressure of 100 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................ 97 A.6: Predicted n-heptane decomposition for the reactor pressures 10 atm, 30 atm, 50 atm, 70 atm, 100 atm, and 170 atm. .................................................................................. 98 A.7: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 10 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................. 99 A.8: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 30 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ............................ 99 A.9: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 50 atm, a reactor temperature of 873 K, and a residence time of 1 minute. .......................... 100 A.10: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 70 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ......................... 101 A.11: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 100 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ......................... 102 A.12: Predicted n-dodecane decomposition for the reactor pressures 10 atm, 30 atm, 50 atm, 70 atm, 100 atm, and 170 atm ....................................................................... 103 A.13: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 10 atm, a reactor temperature of 873 K, and a residence time of 1 minute. ......................... 104 A.14: GC/FID results for thermally stressed n-dodecane at a reactor pressure of 30 atm, a reactor temperature of
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