National Center for Hypersonic Combined Cycle...

National Center for Hypersonic Combined Cycle Propulsion

Professor Jim McDanielPrincipal InvestigatorUniversity of Virginia

AFOSR-NASA Hypersonics Research ReviewWilliamsburg, VA

June 16, 2011


Review Meeting Agenda

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8:15 – 8:45 Center Overview: Jim McDaniel, University of Virginia8:45 – 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 University11:00 – 11:30 Coherent Antistokes Raman Spectroscopy: Andrew Cutler, George Washington

University11:30 – 12:00 Hypervelocity Regime: Dan Cresci, ATK/GASL

12:00 ‐ 1:15 LUNCH

1:15 ‐ 1:45 Advanced Modeling: Farhad Jaberi, Michigan State University1:45 ‐ 2:15 Chemistry Modeling: Steve Pope, Cornell University2:15 ‐ 2:45 Closing Remarks: Jim McDaniel, University of Virginia

END OF REVIEW MEETING

2:45 ‐ 3:15 BREAK3:15 ‐ 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


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Overview of Center


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Center Overview

1. Introduction- Center Technical Roadmap- Objectives- Research Approach- Center Organization

2. Fundamental Modeling and Experimental Synergy

3. Examples of Year 2 Research


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Turbine-Based Combined Cycle Concept


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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


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, tob. New Generation II hybrid LES/RANS and LES/S-FMDF methods, toc. 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.


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Technical Organization


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Fundamental Modelingand

Experimental Synergy


Experimental Capabilities and Modeling Quantities DerivedMeasurementTechnique

Measured Quantities Modeling Quantities Derived

CARS N2, O2, H2, CO2, CO mole fractions and temperature, single point, instantaneous

Scatter plots of temperature and species versus mixture fraction, overall heat release, averaged and rms values of temperature and species.

SPIV Three velocity components, planar, instantaneous

Planar filtered velocity, subgrid scale stress and dissipation, multiplecomponent correlations, filtered energy components, velocity gradients, strain rates, vorticity,

TDLAS H2O, O2, CO2, CO, H-C and temperature, line-of-sight, kHz acquisitionrates

Comparison to line-integrated LES and DNS data for model validation

TDLAT H2O, CO2 and temperature, planar, time averaged

Correlation of time averages species and temperature for global assessment of RANS or LES models

PLIF OH and NO, planar, instantaneous, semi-quantitative

Location of shocks and flame boundaries for validation of spatial RANS and LES solutions

Rayleigh 2 velocity components and density, single point, instantaneous

Favre and non-Favre averaged velocity, averaged density


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FLOW PROBLEM PROGRESSION PHYSICAL PHENOMENA MODELING APPROACH DATA NEEDED

Unbounded flowsTemporally Developing Mixing Layer Compressible Inhomogeneous

TurbulenceLES/FMDF DNS

Isotropic turbulence with normal shock 3‐D vortical structure interactions with shock

LES/FMDF DNS

Turbulent mixing layer with oblique shock

3‐D vortical structure interactions with shock

LES/FMDF DNS

Supersonic nonreacting & reacting mixing layer and jet

Compressible Turbulence and Combustion

LES/FMDF GWU Co‐Annular Jet, DNS

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

SBLI, shock‐vortex interactions RANS, LES‐RANS, LES/FMDF UVa nonreacting combustor and isolator PIV

Wall‐bounded flows (reacting)

Flow in constant area duct with ramp injection and low Ф hydrogen

combustionwithout isolator

ignition, flameholding, shock‐turbulence‐combustion interactions

RANS, LES‐RANS, LES/FMDF UVa combustor, PIV, CARS, TDLAS, TDLAT

Flow in constant area duct with ramp Injection and high Ф hydrogen

combustion, dual‐mode, with isolator

Ignition, flameholding, shock‐turbulence‐combustion interactions, effects of

isolator

RANS, LES‐RANS, LES/FMDF UVa combustor and isolator PIV, CARS, TDLAS, TDLAT

Same as last two cases with ethylene combustion

Same RANS, LES‐RANS, LES/FMDF + reduced kinetics

UVa combustor and isolator, PIV, CARS, TDLAS, TDLAT

Complex flowsNASA Glenn IMX SBLI, 3D flow separation, boundary layer

bleed RANS, HYBRID LES/RANS wall pressure, pitot surveys

HYPULSE Same as UVA experiments plus transient and non‐equilibrium effects

RANS, HYBRID LES/RANS ATK/GASL TDLAS, wall pressure & heat flux, fuel

plume imaging

Fundamental Modeling Problems and Validation Data Needed


Isolator Combustor Extender

LES of SBLI in Isolator(Dual-Mode)

LES/RANS and LES/S-FMDF (Gen. II) Simulations of UVa Dual-Mode Combustor

Isolator Combustor TDLAT Section Extender

LES/RANS (top) and RANS (bottom) of Temperature in Reacting Combustor (supersonic mode, Ф = 0.34)


Simple Fuel Jet in Supersonic Cross Flow

Jet Mixing and Backstep Stabilizer Jet Mixing and Cavity Stabilizer

LES Grid LES Grid LES Grid

Sonic Fuel Jet Sonic Fuel Jet Sonic Fuel Jet

LES/FMDF of Fuel-Air Mixing with Various UVa Injection Geometries


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Measurement Locations and Measurement Techniques

1

2 SPIV, CARS, Rayleigh, TDLAS, PLIF

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4

3

5

1 222 544 4 4111 1

SPIV, CARS, Rayleigh, TDLAS

3 3

SPIV, CARS, Rayleigh, TDLAS, PLIF, TDLAT, combustion efficiency

CARS, TDLAS

SPIV, CARS, Rayleigh, TDLAS, PLIF, TDLAT, combustion efficiency


Tunnel Control Room

Tunnel Setup Area

Tunnel Room TDLAT/GWU Lab

PIV/TDLAS Lab

CARS/IRS/PLIF

TDLAS

SPIV

SPIV

TDLATUVa

GWU

UVa

UVa

Stanford

Experimental Collaboration:UVa Dual-Mode Combustion Facility

UVa Dual-Mode Combustion Tunnel Optical table


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Examples of Year 2 Research


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

Supersonic flow

High-speed flowpath

Low-speedflowpath

Bleed reserviors

Mach number


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New Dual-Mode Combustion Facility


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SPIV Results at X/H = 10, = 0.25

Fuel-air Mixing

Fuel-air Combustion


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Flame structure using RANS• 2.9 deg. divergent-

wall combustor• Ф = 0.4

Mach number (centerplane)

Temperature contoursOH contours


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Hypervelocity Regime: HYPULSE at ATK/GASL

Supersonic Air Exhaust

Optical Fibers

5 Beam PathsH2 Fuel Injector Ramp

L~1”


Incident shock β = 30o

Pressure

TemperatureNormal Shock Wave

Oblique Shock Wave Supersonic Turbulent Mixing Layer

with Combustion

Spatially-Developing Mixing Layer with Shock

Shock-Isotropic Turbulence Interaction Shock-Turbulent BL Interaction

Advanced Modeling: DNS of High-Speed Turbulent Flows (Generation III)

H2 + Air

Air

Inviscid Wall

Supported by AFRL


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

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• 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.


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Questions ?

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