Combustion Team

1
Combustion Team
Faculty Advisors
Student Researchers

• Sara Esparza
• Cesar Olmedo

Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu
2
Agenda

• Background, Theory Input Parameters
• Supersonic Combustion
• Mach Number Operational Envelope
• Engine Design Optimization
• Design Components
• Design Component Analysis
• Numerical Analysis and Subsequent Design
  Modification
• Future Work
• Timeline

3
Governing EquationsMotion of Fluid Substances

• Conservation of Mass

• Conservation of Momentum

• Conservation of Energy

• Conservation of Species

• State Equation Ideal Gas Law

4
Combustion

• Combustion stoichiometry
• Ideal fuel/ air ratio
• Recommended fuels for scramjets
• Hydrogen - most common
• Ethylene
• Kerosene
• Only oxidizer is air
• In scramjets, combustion is often unstable
• Equivalence ratio
• Should range from 0.2 - 2.0 for combustion to
  occur with a useful time scale
• Lean mixture ratio below 1.0
• Rich mixture ratio above 1.0

5
Equivalence and Swirl RatiosSpecific to
Combustion Projects

• Equivalence Ratio, f

• Swirl Number, S

6
Supersonic Combustion
7
Supersonic CombustionResearch Product
Description

• Design, fabricate and test supersonic combustion
  ramjet in supersonic wind tunnel
• Research and improve upon high speed flow,
  mixing, and combustion stability

8
Speed of Sound
The rate of travel of a sound wave through air
under specified conditions
? adiabatic index R gas constant T air
temperature
At sea level a768 mi/hr or 343m/s
9
Mach Number Operational Regimes Subsonic,
Transonic, Supersonic Hypersonic Flight
Subsonic Boeing 747 0ltMalt1 Ma .85
Supersonic F15 Fighter Plane 1.0ltMalt3.0 Ma 1.5
Hypersonic Space Shuttle Magt3 Ma 25
10
Reversed Alligator Inlet Design Chosen
11
Integrated Scramjet Vehicle
Compressor Turn Angle 18deg
Diffuser Exit angle 12.29 deg
Variable Cowl Mach decrease from heat input
12
Exit Mach Number One Dimensional Flow
13
Shockwaves Traverse through Engine
Two-Dimensional Flow
14
Shock and Turn Angles
15
Prandtl Meyer Expansion Waves
16
Integrated Scramjet Vehicle
M8 4.5
M 2.6
M 4.2
M 2.1
17
Supersonic mixing

• Ignition and flame holding are a first order
  issue for supersonic combustion

18
Supersonic Combustion Mixing Stability

• Supersonic Mixing
• Development of mixing length
• Development of injector location
• Development of ignition location
• Development of flame holder

19
CombustionTurbulent Shear Mixing
20
Turbulent mixing at supersonics speeds
Micro-mixing
21
CombustionTurbulent Shear Mixing

• Mean velocity profile combines
• Prandtls number
• Turbulent kinematic viscosity
• Time average characteristics of turbulent shear

Micro-mixing
Fuel vortex
Fuel wave
22
CombustionTurbulent Shear Mixing

• Shear layer width Two methods

Local shear layer width for turbulent shear
mixing
Recent research Cd is a experimental constant
23
CombustionTurbulent Shear Mixing

• Density effects on shear layer growth
  compressible flow
• Based on constant but different densities
• A density ratio, s, is derived
• s can be calculated once stagnation pressure and
  stream velocities are known

24
CombustionTurbulent Shear Mixing

• Convective velocity for the vortex structures
• With compressible flow using isentropic
  stagnation density equation changes to

25
CombustionTurbulent Shear Mixing

• Density correct expression for shear layer growth
  including compressibility effects

26
CombustionTurbulent Shear Mixing
27
Supersonic Mixing Efficiency

• Mixing Efficiency

28
Fuel

• Hydrogen
• Has four times the energy of aviation fluid, less
  polluting emissions
• Safety
• Silane
• SiH4 is a pyrophoric that can be added to
  hydrogen to decrease ignition delay time of the
  fuel
• Concentrations are between 5-20 by volume
• Useful when the combustion chamber is short or
  combustion chamber temperature is low
• Safety Concerns is highly explosive easily
  ignites with air and 9.6k ppm is very lethal in
  just a four hour exposure
• JP10 Fuel
• Liquid Fuel used in First air-breathing Scramjet

29
Combustion Stability

• Flame velocity
• Flame length
• Recirculation
• Detonation
• Auto-ignition
• Back pressure

30
Design Approaches

• Mach 2
• Simple
• Mutable
• Flexible
• Rapid prototype
• ZPrinter powder, high temperature inner shell
• Cheap
• MFDCLab sufficient

• Mach 4.5
• Complex
• Fixed shape
• Not flexible
• Machining
• Stainless steel, high nickel steel, copper,
  aluminum
• Expensive
• Needs supersonic wind tunnel

31
Combustion Performance Design

• Detonation shockwave induced combustion
• Flame holder use back pressure to control flame
  stability

COSMOSWorks Flame Holder Inlet Mach 4.5 Velocity
contours shows recirculation zones
32
Injector Pressure Profile
33
Fuel Injector Holds the Flame
34
Size Coolant Delivery Mechanism according to
Pressure and Temperature
Pc Mechanism
700 tubes
1310 tubes
1378 channels/tubes
1486 channels/ablative
2994 channels/tubes
35
Proof of Concept

• Test supersonic leading edges
• Develop and simulate computational fluid dynamics
  run of overall design and individual components
• Compare and analyze test data
• Achieve supersonic combustion throughout the
  engine

36
Conclusion

• Sustain supersonic combustion
• Increase fuel and air mixing time
• Vary input parameters to create knowledge and
  testing base
• Key components
• Multiple combustion chambers
• Cavities
• Flameholders
• Development of a doctoral dissertation

37
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 Searies.
• Olfe, D. B. V. Zakkay Supersonic Flow,
  Chemical Processes, Radiative Transfer
• Perry, R. H. D. W. Green Perrys Chemical
  Engineers Handbook
• McGraw-Hill
• Turns, S.R. An Introduction to Combustion
• White, E.B. Fluid Mechanics.

38
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. OByrne, 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.

39
Acknowledgements

• Thanks to the faculty advisors
• Dr. D. Guillaume
• Dr. C. Wu
• And SPACE Center faculty
• Dr. H. Boussalis
• Dr. C. Liu

• SPACE Center Students
• Combustion Team
• Sheila Blaise
• Rebecca Winfield

40
Timeline2009 - 2010
Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010 Supersonic Combustion Team Timeline March 2009 - February 2010
2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2009 2010 2010
Student Name MAR DOCUMENTATION APR MAY JUN DOCUMENTATION JUL JUL AUG AUG SEP DOCUMENTATION OCT NOV DEC DOCUMENTATION JAN FEB
Sara Esparza Understanding Compressible Flow DOCUMENTATION Determination of Mach Speed inside Diffuser Determined Fuel Selection Hydrogen Ethylene Boundary Layer Theory DOCUMENTATION Develop shear mixing layer Develop shear mixing layer Begin research on Thesis Development Begin research on Thesis Development Fuel Selection DOCUMENTATION Presentation Begin research on fuel igniter locator Began Research on diffuser exhaust DOCUMENTATION Presentation Dr. Spanos Presentation
Sara Esparza Supersonic Diffuser Initial Design DOCUMENTATION Angle Determination of Diffuser Determined Fuel Selection Hydrogen Ethylene Shear stress in compressible non compressible flow DOCUMENTATION Determine Shear Layer in compressible non compressible flow Determine Shear Layer in compressible non compressible flow Begin writing Thesis Begin writing Thesis Determined that Ethylene is better than Hydrogen, and mixing efficiency DOCUMENTATION Begin research on fuel injection angles Using mixing layer theory, determined igniter location Design SECETA Supersonic diffuser with Prandtl-Myer expansion DOCUMENTATION Research on Flame Holder Concept Science Symposium Presentation
Sara Esparza Cosmos CFD analysis of Diffuser DOCUMENTATION CFD Analysis of Mach Speed Shock Wave Angles Determined Fuel Selection Hydrogen Ethylene Shear stress in compressible non compressible flow DOCUMENTATION Determine difference in shear layer growth between compressible non compressible flows Determine difference in shear layer growth between compressible non compressible flows Determine difference in shear layer growth between compressible non compressible flows Determined efficiency of mixing dependent of injection angle Determined efficiency of mixing dependent of injection angle DOCUMENTATION Determine the angle of injection Determined igniter should be continuous like a spark plug CFD analysis of SECETA DOCUMENTATION Research on Flame Holder Concept Paper for Colorado Conference
Cesar Olmedo Understanding Compressible Flow DOCUMENTATION CFD Analysis of Mach Speed Shock Wave Angles Determined Fuel Selection Hydrogen Ethylene Understand Supersonic Mixing DOCUMENTATION Develop shear mixing layer Develop shear mixing layer Begin research on Thesis Development and writing Thesis Begin research on Thesis Development and writing Thesis Fuel Selection DOCUMENTATION Presentation Begin research on fuel igniter locator Began Research on diffuser exhaust DOCUMENTATION Presentation Dr. Spanos Presentation
Cesar Olmedo Understanding Compressible Flow DOCUMENTATION CFD Analysis of Mach Speed Shock Wave Angles Determined Fuel Selection Hydrogen Ethylene Boundary Layer Theory DOCUMENTATION Fuel Selection Determine Shear Layer in compressible non compressible flow Determine Shear Layer in compressible non compressible flow Determine Shear Layer in compressible non compressible flow Determined that Ethylene is better than Hydrogen, and mixing efficiency DOCUMENTATION Begin research on fuel injection angles Using mixing layer theory, determined igniter location Design SECETA Supersonic diffuser with Prandtl-Myer expansion DOCUMENTATION Research on Flame Holder Concept Science Symposium Presentation
Cesar Olmedo Cosmos CFD analysis of Diffuser DOCUMENTATION CFD Analysis of Mach Speed Shock Wave Angles Determined Fuel Selection Hydrogen Ethylene Shear stress in compressible non compressible flow DOCUMENTATION Determine difference in shear layer growth between compressible non compressible flows Determine difference in shear layer growth between compressible non compressible flows Determine difference in shear layer growth between compressible non compressible flows Determined efficiency of mixing dependent of injection angle Determined efficiency of mixing dependent of injection angle DOCUMENTATION Determine the angle of injection Determined igniter should be continuous like a spark plug CFD analysis of SECETA DOCUMENTATION Design of Flame Holder Paper for Colorado Conference
41
Timeline2010 - 2011
Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011 Supersonic Combustion Team Timeline March 2010 - February 2011
2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2010 2011 2011
Student Name MAR MAR APR APR MAY MAY JUN JUN JUL JUL AUG AUG SEP OCT NOV DEC JAN FEB
Sara Esparza Duel cavity flame holder is selected Engineering Drawing of Flame Holder Material Selection for flame holder (Copper) CFD analysis of Flame holder Presentation Presentation Fabrication of Flame Holder Integration of SECETA and Flame Holder Application of Sensors on SECETA Fabricate Fuel line to Wind tunnel Supersonic Wind tunnel Testing Set up fuel lines in wind tunnel Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Sara Esparza Duel cavity flame holder is selected Engineering Drawing of Flame Holder Material Selection for flame holder (Copper) CFD analysis of Flame holder Developed cost to determined Budget Developed cost to determined Budget Fabrication of Flame Holder Integration of SECETA and Flame Holder Application of Sensors on SECETA Fabricate Fuel line to Wind tunnel Supersonic Wind tunnel Testing Set up fuel lines in wind tunnel Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Sara Esparza First cavity is adjustable First cavity is adjustable Material Selection for flame holder (Copper) CFD analysis of Flame holder Determined if Budget can be obtained Determined if Budget can be obtained Fabrication of Flame Holder Integration of SECETA and Flame Holder Application of Sensors on SECETA Fabricate Fuel line to Wind tunnel Supersonic Wind tunnel Testing Set up fuel lines in wind tunnel Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Cesar Olmedo Duel cavity flame holder is selected Engineering Drawing of Flame Holder Material Selection for flame holder (Copper) CFD analysis of Flame holder Presentation Presentation Fabrication of Flame Holder Integration of SECETA and Flame Holder Application of Sensors on SECETA Fabricate Fuel line to Wind tunnel Supersonic Wind tunnel Testing Set up fuel lines in wind tunnel Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Cesar Olmedo Duel cavity flame holder is selected Engineering Drawing of Flame Holder Material Selection for flame holder (Copper) CFD analysis of Flame holder Developed cost to determined Budget Developed cost to determined Budget Fabrication of Flame Holder Integration of SECETA and Flame Holder Application of Sensors on SECETA Fabricate Fuel line to Wind tunnel Supersonic Wind tunnel Testing Set up fuel lines in wind tunnel Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Cesar Olmedo First cavity is adjustable First cavity is adjustable Material Selection for flame holder (Copper) CFD analysis of Flame holder Determined if Budget can be obtained Determined if Budget can be obtained Fabrication of Flame Holder Integration of SECETA and Flame Holder Application of Sensors on SECETA Fabricate Fuel line to Wind tunnel Supersonic Wind tunnel Testing Set up fuel lines in wind tunnel Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Alonzo Perez Engineering Drawing of Flame Holde Engineering Drawing of Flame Holde                     Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Alonzo Perez Engineering Drawing of Flame Holde Engineering Drawing of Flame Holde Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
Alonzo Perez Engineering Drawing of Flame Holde Engineering Drawing of Flame Holde                     Attempt Supersonic Combustion Gather Data Attempt Multiple combustion Chamber Determine thrust of engine Determine Combustion time Determine Combustion time
2011 Timeline Excel