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Review Meeting Agenda

National Center for Hypersonic Combined Cycle Propulsion Professor Jim McDaniel Principal Investigator University of Virginia AFOSR-NASA Hypersonics Research Review Williamsburg, VA June 16, 2011. Review Meeting Agenda. 8:15 – 8:45 Center Overview: Jim McDaniel, University of Virginia

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Review Meeting Agenda

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  1. National Center for Hypersonic Combined Cycle PropulsionProfessor Jim McDanielPrincipal InvestigatorUniversity of VirginiaAFOSR-NASA Hypersonics Research ReviewWilliamsburg, VAJune 16, 2011

  2. Review Meeting Agenda 8:15 – 8:45 Center Overview: Jim McDaniel, University of Virginia 8:45 – 9:15 Turbine/Ramjet Mode Transition: Kevin Bowcutt, Boeing 9:15 – 9:45 Ramjet/Scramjet Mode Transition (experimental): Chris Goyne, University of Virginia 9:45 – 10:00 BREAK 10:00 – 10:30 Ramjet/Scramjet Mode Transition (computational): Jack Edwards, North Carolina State University 10:30 – 11:00 Tunable Diode Laser Absorption Spectroscopy: Ron Hanson, Stanford University 11:00 – 11:30 Coherent Antistokes Raman Spectroscopy: Andrew Cutler, George Washington University 11:30 – 12:00 Hypervelocity Regime: Dan Cresci, ATK/GASL 12:00 - 1:15 LUNCH 1:15 - 1:45 Advanced Modeling: Farhad Jaberi, Michigan State University 1:45 - 2:15 Chemistry Modeling: Steve Pope, Cornell University 2:15 - 2:45 Closing Remarks: Jim McDaniel, University of Virginia END OF REVIEW MEETING 2:45 - 3:15 BREAK 3:15 - 4:00 Advisory Board Meeting (Center participants and board members only) Note: The last 5 minutes of each presentation will be reserved for Q/A

  3. Overview of Center

  4. Center Overview • Introduction • - Center Technical Roadmap • - Objectives • - Research Approach • - Center Organization • Fundamental Modeling and Experimental Synergy • 3. Examples of Year 2 Research

  5. Turbine-Based Combined Cycle Concept

  6. Center Objective The primary objective of the centeris to advance the understanding of the critical mode transitions and supersonic/hypervelocity flow regimes of combined cycle propulsion by: • Developing an advanced suite of computational modeling and simulation tools for predicting combined cycle flow physics 2. Utilizing the unique facilities available to the Center and advanced flowfield diagnostics to conduct experiments that will: a. Provide insight into the fundamental physics of the complex flow in combined cycle hypersonic propulsion systems, b. Provide detailed data sets for the development and validation of models of combined cycle flow physics, and, 3. Bringing together the modelers and experimentalists in a synergistic way to work on common problems in hypersonic combined cycle propulsion

  7. Research Approach • Develop and implement a hierarchy of novel methodologies for high fidelity simulations of various flow paths. These methodologies range from: • Current production-level Generation I RANS simulations, to • New Generation II hybrid LES/RANS and LES/S-FMDF methods, to • The most sophisticated envisioned form of LES/EPVS-FMDF for Generation III prediction of hypervelocity reacting flows, and • d. Detailed/reduced kinetics models for thermal decomposition/oxidation of relevant hydrocarbon fuels. • Conduct experiments that will: • Elucidate the fundamental flow physics of compressible, turbulent reacting flows in combined cycle systems, • Measure reacting flow turbulent statistics and novel fuel-air mixing and flameholdingapproaches through the development and application of advanced diagnostics, • Develop benchmark data sets with quantified experimental uncertainty for the purposes of developing accurate Generation I, II and III models.

  8. Technical Organization

  9. Fundamental ModelingandExperimental Synergy

  10. Experimental Capabilities and Modeling Quantities Derived

  11. Fundamental Modeling Problems and Validation Data Needed

  12. LES/RANS and LES/S-FMDF (Gen. II) Simulations of UVa Dual-Mode Combustor Isolator Combustor TDLAT Section Extender Isolator Combustor Extender LES of SBLI in Isolator (Dual-Mode) LES/RANS (top) and RANS (bottom) of Temperature in Reacting Combustor (supersonic mode, Ф = 0.34)

  13. LES/FMDF of Fuel-Air Mixing with Various UVa Injection Geometries LES Grid LES Grid LES Grid Jet Mixing and Backstep Stabilizer Jet Mixing and Cavity Stabilizer Simple Fuel Jet in Supersonic Cross Flow Sonic Fuel Jet Sonic Fuel Jet Sonic Fuel Jet

  14. Measurement Locations and Measurement Techniques 1 1 1 1 1 2 2 2 3 3 3 4 4 4 4 5 1 SPIV, CARS, Rayleigh, TDLAS 4 CARS, TDLAS SPIV, CARS, Rayleigh, TDLAS, PLIF 2 SPIV, CARS, Rayleigh, TDLAS, PLIF, TDLAT, combustion efficiency 5 SPIV, CARS, Rayleigh, TDLAS, PLIF, TDLAT, combustion efficiency 3 15

  15. Experimental Collaboration: UVa Dual-Mode Combustion Facility UVa UVa Dual-Mode Combustion Tunnel TDLAT Optical table GWU CARS/IRS/PLIF Tunnel Room TDLAT/GWU Lab Tunnel Control Room Stanford TDLAS UVa SPIV UVa SPIV Tunnel Setup Area PIV/TDLAS Lab

  16. Examples of Year 2 Research

  17. Immersed Boundary Methodology: simulating bleed flow through individual bleed holes in bleed surfaces from CAD file definition Dual-inlet Mode TransitionGeneration II IMX CFD Results CAD file rendition of IMX bleed region High-speed flowpath Supersonic flow Low-speed flowpath Bleed reserviors Mach number

  18. New Dual-Mode Combustion Facility

  19. SPIV Results at X/H = 10, F = 0.25 Fuel-air Mixing Fuel-air Combustion

  20. Flame structure using RANS Mach number (centerplane) • 2.9 deg. divergent-wall combustor • Ф = 0.4 OH contours Temperature contours 21

  21. 5 Beam Paths H2 Fuel Injector Ramp Optical Fibers Hypervelocity Regime: HYPULSE at ATK/GASL Supersonic Air Exhaust L~1”

  22. Advanced Modeling: DNS of High-Speed Turbulent Flows (Generation III) Shock-Turbulent BL Interaction Shock-Isotropic Turbulence Interaction Normal Shock Wave Temperature Incident shockβ= 30o Pressure Spatially-Developing Mixing Layer with Shock Supported by AFRL Oblique Shock Wave Supersonic Turbulent Mixing Layer with Combustion Air Inviscid Wall H2 + Air

  23. Chemistry Modeling: Detailed and Simplified Kinetic Models • Rate parameters of detailed kinetic models are associated with large uncertainty factors, whichlead to large variation in flame extinction limits, eg. extinction strain rates from 800 to 1600 s-1 • Global sensitivity analysis can yield valuable information about first-order effects and second-order effects of rate parameters • Comprehensive model reduction strategies developed have included ignition, propagation, and extinction limits and has been accomplished via PCA and QSSA • Starting from a detailed ethylene-air kinetic model containing 111 species in 784 reversible reactions, skeletal model with 37-38 species and reduced reaction model with 20-24 species have been developed • Develop computational efficient strategies of implementing reduced order models (i.e. skeletal, reduced, RCCE) using ISAT methodology. • Implementation in Partially-Stirred Reactor simulations have shown a reduction of 1000 times over direct evaluation of the detailed model.

  24. Questions ?

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