1 / 23

Combustion Team High Speed Combustion

Sara Esparza Cesar Olmedo Alonzo Perez. Combustion Team High Speed Combustion. Faculty Advisors:. Student Researchers:. Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu Dr. Rad. Purpose. To achieve and sustain Mach 1.0 to 2.0 speed, induce mixing and sustain combustion for a duration.

jatin
Download Presentation

Combustion Team High Speed Combustion

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. NASA Grant URC NCC NNX08BA44A Sara Esparza Cesar Olmedo Alonzo Perez Combustion TeamHigh Speed Combustion Faculty Advisors: Student Researchers: Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu Dr. Rad

  2. NASA Grant URC NCC NNX08BA44A Purpose To achieve and sustain Mach 1.0 to 2.0 speed, induce mixing and sustain combustion for a duration

  3. NASA Grant URC NCC NNX08BA44A Converging-Diverging Nozzle • Nozzle brings air up to speed • Entry and exit nozzle views

  4. CD Nozzle Drawing 9/21/2014 NASA Grant URC NCC NNX08BA44A

  5. CD Nozzle Calculations Throat D= .13 Expansion Area Ratio Compression Area Ratio D=.22 D=.30 Isentropic flow properties Expansion Area Ratio Expansion Area Ratio Throat A 2.86 M = 2.4 A Throat Area 9/21/2014 NASA Grant URC NCC NNX08BA44A

  6. NASA Grant URC NCC NNX08BA44A Nozzle Data

  7. NASA Grant URC NCC NNX08BA44A Initial Testing • Tested nozzle design

  8. Pressure Reading at Nozzle Exit • Pressure gage reading • Anderson’s text: Mach 2.6 • Area ratio: 2.89

  9. NASA Grant URC NCC NNX08BA44A Numerical and Experimental Results Coincide • Exit pressure corresponds to 5.23 psia as seen in testing

  10. NASA Grant URC NCC NNX08BA44A Nozzle Error • 22% Error between Experimental and Numerical Calculations

  11. NASA Grant URC NCC NNX08BA44A Testing • Picture of the set up • Used hydrogen tank from MFDCLab • Combustion occurred • Below Mach one

  12. NASA Grant URC NCC NNX08BA44A Mixing Cavity & Combustor • Initial Concept • Use cavity to re-circulate fuel and air improve mixing • Produce ideal combustion environment

  13. NASA Grant URC NCC NNX08BA44A Ignition System Car distributor

  14. Overall Design Fuel inlet Fuel inlet Lab Supply Quick Release – CD Nozzle Connection Section View 9/21/2014 NASA Grant URC NCC NNX08BA44A

  15. NASA Grant URC NCC NNX08BA44A Testing Results • We developed combustion • Flow speed was not supersonic • Cavity was too big and it produced a bow shock and reduced flow

  16. NASA Grant URC NCC NNX08BA44A Final Design • Met with Dr Wu to develop • Smaller cavity • Development of hydrogen and spark plug manifold

  17. NASA Grant URC NCC NNX08BA44A

  18. NASA Grant URC NCC NNX08BA44A Pathlines and Particle Tracing

  19. NASA Grant URC NCC NNX08BA44A Final Design

  20. NASA Grant URC NCC NNX08BA44A Final Design • Solidworks assembly • Side and front views

  21. NASA Grant URC NCC NNX08BA44A Future Work • Test at supersonic speeds • Incorporate heating coil • Add insulation • Acquire silane • Purchase Gambit or ICES

  22. Textbook References Anderson, J. “Compressible Flow.” Anderson, J. “Hypersonic & High Temperature Gas Dynamics” Curran, E. T. & S. N. B. Murthy, “Scramjet Propulsion” AIAA Educational Series, Fogler, H.S. “Elements of Chemical Reaction Engineering” Prentice Hall International Studies. 3rd ed. 1999. Heiser, W.H. & D. T. Pratt “Hypersonic Airbreathing Propulsion” AIAA Educational Series. Olfe, D. B. & V. Zakkay “Supersonic Flow, Chemical Processes, & Radiative Transfer” Perry, R. H. & D. W. Green “Perry’s Chemical Engineers’ Handbook” McGraw-Hill Turns, S.R. “An Introduction to Combustion” White, E.B. “Fluid Mechanics”. 9/21/2014 NASA Grant URC NCC NNX08BA44A 22

  23. Journal References Allen, W., P. I. King, M. R. Gruber, C. D. Carter, K. Y Hsu, “Fuel-Air Injection Effects on Combustion in Cavity-Based Flameholders in a Supersonic Flow”. 41st AIAA Joint Propulsal. 2005-4105. Billig, F. S. “Combustion Processes in Supersonic Flow”. Journal of Propulsion, Vol. 4, No. 3, May-June 1988 Da Riva, Ignacio, Amable Linan, & Enrique Fraga “Some Results in Supersonic Combustion” 4th Congress, Paris, France, 64-579, Aug 1964 Esparza, S. “Supersonic Combustion” CSULA Symposium, May 2008. Grishin, A. M. & E. E. Zelenskii, “Diffusional-Thermal Instability of the Normal Combustion of a Three-Component Gas Mixture,” Plenum Publishing Corporation. 1988. Ilbas, M., “The Effect of Thermal Radiation and Radiation Models on Hydrogen-Hydrocarbon Combustion Modeling” International Journal of Hydrogen Energy. Vol 30, Pgs. 1113-1126. 2005. Qin, J, W. Bao, W. Zhou, & D. Yu. “Performance Cycle Analysis of an Open Cooling Cycle for a Scramjet” IMechE, Vol. 223, Part G, 2009. Mathur, T., M. Gruber, K. Jackson, J. Donbar, W. Donaldson, T. Jackson, F. Billig. “Supersonic Combustion Experiements with a Cavity-Based Fuel Injection”. AFRL-PR-WP-TP-2006-271. Nov 2001 McGuire, J. R., R. R. Boyce, & N. R. Mudford. Journal of Propulsion & Power, Vol. 24, No. 6, Nov-Dec 2008 Mirmirani, M., C. Wu, A. Clark, S, Choi, & B. Fidam, “Airbreathing Hypersonic Flight Vehicle Modeling and Control, Review, Challenges, and a CFD-Based Example” Neely, A. J., I. Stotz, S. O’Byrne, R. R. Boyce, N. R. Mudford, “Flow Studies on a Hydrogen-Fueled Cavity Flame-Holder Scramjet. AIAA 2005-3358, 2005. Tetlow, M. R. & C. J. Doolan. “Comparison of Hydrogen and Hydrocarbon-Fueld Scramjet Engines for Orbital Insertion” Journal of Spacecraft and Rockets, Vol 44., No. 2., Mar-Apr 2007. 9/21/2014 NASA Grant URC NCC NNX08BA44A 23

More Related