Title: Combustion Team
1Combustion Team
Faculty Advisors
Student Researchers
- Sara Esparza
- Cesar Olmedo
Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu
2Agenda
- 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
3Governing EquationsMotion of Fluid Substances
- State Equation Ideal Gas Law
4Combustion
- 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
5Equivalence and Swirl RatiosSpecific to
Combustion Projects
6Supersonic Combustion
7Supersonic 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
8Speed 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
9Mach 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
10Reversed Alligator Inlet Design Chosen
11Integrated Scramjet Vehicle
Compressor Turn Angle 18deg
Diffuser Exit angle 12.29 deg
Variable Cowl Mach decrease from heat input
12Exit Mach Number One Dimensional Flow
13Shockwaves Traverse through Engine
Two-Dimensional Flow
14Shock and Turn Angles
15Prandtl Meyer Expansion Waves
16Integrated Scramjet Vehicle
M8 4.5
M 2.6
M 4.2
M 2.1
17Supersonic mixing
- Ignition and flame holding are a first order
issue for supersonic combustion
18Supersonic Combustion Mixing Stability
- Supersonic Mixing
- Development of mixing length
- Development of injector location
- Development of ignition location
- Development of flame holder
19CombustionTurbulent Shear Mixing
20Turbulent mixing at supersonics speeds
Micro-mixing
21CombustionTurbulent Shear Mixing
- Mean velocity profile combines
- Prandtls number
- Turbulent kinematic viscosity
- Time average characteristics of turbulent shear
Micro-mixing
Fuel vortex
Fuel wave
22CombustionTurbulent Shear Mixing
- Shear layer width Two methods
Local shear layer width for turbulent shear
mixing
Recent research Cd is a experimental constant
23CombustionTurbulent 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
24CombustionTurbulent Shear Mixing
- Convective velocity for the vortex structures
- With compressible flow using isentropic
stagnation density equation changes to
25CombustionTurbulent Shear Mixing
- Density correct expression for shear layer growth
including compressibility effects
26CombustionTurbulent Shear Mixing
27Supersonic Mixing Efficiency
28Fuel
- 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
29Combustion Stability
- Flame velocity
- Flame length
- Recirculation
- Detonation
- Auto-ignition
- Back pressure
30Design 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
31Combustion 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
32Injector Pressure Profile
33Fuel Injector Holds the Flame
34Size Coolant Delivery Mechanism according to
Pressure and Temperature
Pc Mechanism
700 tubes
1310 tubes
1378 channels/tubes
1486 channels/ablative
2994 channels/tubes
35Proof 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
36Conclusion
- 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
37Textbook 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.
38Journal 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.
39Acknowledgements
- 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
40Timeline2009 - 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
41Timeline2010 - 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