National Center for Hypersonic Combined Cycle Propulsion

Transcription

1 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

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 2

3 Overview of Center 3

4 Center Overview 1. Introduction - Center Technical Roadmap - Objectives - Research Approach - Center Organization 2. Fundamental Modeling and Experimental Synergy 3. Examples of Year 2 Research 4

5 Turbine-Based Combined Cycle Concept 5

6 6

7 Center Objective The primary objective of the center is to advance the understanding of the critical mode transitions and supersonic/hypervelocity flow regimes of combined cycle propulsion by: 1. 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

8 Research Approach 1. Develop and implement a hierarchy of novel methodologies for high fidelity simulations of various flow paths. These methodologies range from: a. Current production-level Generation I RANS simulations, to b. New Generation II hybrid LES/RANS and LES/S-FMDF methods, to c. 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. 2. Conduct experiments that will: a. Elucidate the fundamental flow physics of compressible, turbulent reacting flows in combined cycle systems, b. Measure reacting flow turbulent statistics and novel fuel-air mixing and flameholding approaches through the development and application of advanced diagnostics, c. Develop benchmark data sets with quantified experimental uncertainty for the purposes of developing accurate Generation I, II and III models.

9 Technical Organization 9

10 Fundamental Modeling and Experimental Synergy 10

11 Experimental Capabilities and Modeling Quantities Derived Measurement Technique Measured Quantities Modeling Quantities Derived CARS SPIV TDLAS TDLAT PLIF Rayleigh N 2, O 2, H 2, CO 2, CO mole fractions and temperature, single point, instantaneous Three velocity components, planar, instantaneous H 2 O, O 2, CO 2, CO, H-C and temperature, line-ofsight, khz acquisition rates H 2 O, CO 2 and temperature, planar, time averaged OH and NO, planar, instantaneous, semiquantitative 2 velocity components and density, single point, instantaneous Scatter plots of temperature and species versus mixture fraction, overall heat release, averaged and rms values of temperature and species. Planar filtered velocity, subgrid scale stress and dissipation, multiple component correlations, filtered energy components, velocity gradients, strain rates, vorticity, Comparison to line-integrated LES and DNS data for model validation Correlation of time averages species and temperature for global assessment of RANS or LES models Location of shocks and flame boundaries for validation of spatial RANS and LES solutions Favre and non-favre averaged velocity, averaged density

12 Fundamental Modeling Problems and Validation Data Needed FLOW PROBLEM PROGRESSION PHYSICAL PHENOMENA MODELING APPROACH DATA NEEDED Unbounded flows Temporally Developing Mixing Layer Compressible Inhomogeneous LES/FMDF DNS Turbulence Isotropic turbulence with normal shock 3 D vortical structure interactions with LES/FMDF DNS shock Turbulent mixing layer with oblique 3 D vortical structure interactions with LES/FMDF DNS shock shock Supersonic nonreacting & reacting Compressible Turbulence and LES/FMDF GWU Co Annular Jet, DNS mixing layer and jet Combustion Wall bounded flows (non reacting) Flow in constant area duct SBLI, corner vortices RANS, HYBRID LES RANS UVa isolator PIV Flow in constant area duct with ramp injection SBLI, shock vortex interactions RANS, LES RANS, LES/FMDF UVa non reacting combustor PIV Flow in constant area duct, ramp injection, dual mode Wall bounded flows (reacting) Flow in constant area duct with ramp injection and low Ф hydrogen combustion without isolator Flow in constant area duct with ramp Injection and high Ф hydrogen combustion, dual mode, with isolator Same as last two cases with ethylene combustion Complex flows NASA Glenn IMX HYPULSE SBLI, shock vortex interactions RANS, LES RANS, LES/FMDF UVa nonreacting combustor and isolator PIV ignition, flameholding, shock turbulencecombustion interactions RANS, LES RANS, LES/FMDF Ignition, flameholding, shock turbulencecombustion interactions, effects of RANS, LES RANS, LES/FMDF isolator Same RANS, LES RANS, LES/FMDF + reduced kinetics SBLI, 3D flow separation, boundary layer bleed Same as UVA experiments plus transient and non equilibrium effects RANS, HYBRID LES/RANS RANS, HYBRID LES/RANS UVa combustor, PIV, CARS, TDLAS, TDLAT UVa combustor and isolator PIV, CARS, TDLAS, TDLAT UVa combustor and isolator, PIV, CARS, TDLAS, TDLAT wall pressure, pitot surveys ATK/GASL TDLAS, wall pressure & heat flux, fuel plume imaging 12

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

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

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

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

17 Examples of Year 2 Research 17

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

19 New Dual-Mode Combustion Facility 19

20 SPIV Results at X/H = 10, = 0.25 Fuel-air Mixing Fuel-air Combustion 20

21 Flame structure using RANS Mach number (centerplane) 2.9 deg. divergentwall combustor Ф = 0.4 OH contours Temperature contours 21

22 Hypervelocity Regime: HYPULSE at ATK/GASL Supersonic Air L~1 Exhaust H 2 Fuel Injector Ramp 5 Beam Paths Optical Fibers 22

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

24 Chemistry Modeling: Detailed and Simplified Kinetic Models Rate parameters of detailed kinetic models are associated with large uncertainty factors, which lead 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 species and reduced reaction model with 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

25 Questions? 25