FLUISTCOM Fluid Structure Interaction for Combustion Systems ( MRTN-CT ) Combustion Instability Effects and Aero-Thermal Near-Wall Response

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Institut für Verbrennungstechnik - Institute of Combustion Technology

D. Panara, R. Dannecker, B.Noll

Institut für Verbrennungstechnik

DLR Deutsches Zentrum für Luft- und Raumfahrt e.V.

Mitglied der Herrmann von Helmholtz-Gemeinschaft Deutscher Forschungszentren HGF

Stuttgart

FLUISTCOM

Fluid Structure

Interaction for Combustion Systems

( MRTN-CT-2003-504183)

Combustion Instability Effects and

Aero-Thermal Near-Wall Response

Agenda 12-Months Progress Meeting

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2

• January

2003

-

University of Florence

,

Mechanical Engineering

Diploma

• Thesis title: Finflo and Tascflow a comparison between two different

Navier-Stokes CFD codes in strong curvature applications

• Supervisors:

Prof. T.

Siikonen

( Helsinki University of Tech.)

Prof. F.

Martelli

and P.

Adami

( University of Florence )

• Jan-April

2003

-

Helsinki University of Technology

,

Researcher

• Thesis Publication, Helsinki University Laboratory Report.

• June-July

2003

-

Teknomeccanica s.r.l.

, Italy,

Control and Assembling

• July-Sept

2003

-

Nuovo Pignone GE oil & Gas

, Italy,

Quality Engineer

• Sept 2003-June 2004

-

Von Karman Institute for Fluid Dynamic

Diploma Course, Department of Turbomachinery and Propulsion

• Project title:

Quasi-3D Unsteady Numerical Investigation of Clocking Effects

in 1&1/2 Stage Transonic Turbine

• Supervisor: Prof.

R. Denos

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3 Overview



Literature Research on Pulsating Flow



Experimental Evidences



Thermal Boundary Layer



Viscous Boundary Layer



Numerical Models

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4 Near Wall Aerodynamic Response

in Pulsating Pipe Flows



Viscous Boundary Layer

• Thermal Boundary Layer

• Numerical Models

• ISAAC

Oscillating Flow:

υ

VD

c

=

Re

υ

m

w

aU

=

Re

π

2 T

U

a

m

=

ω

υ

2 =

s

l

s

l

D

R

2 =

δ

Turbulent

800 Re

Laminar

400 Re

≥

≤

s s

l

υ

s

l

U

s

0 Re

₌

Pulsating Flow:

)

sin(

)

(

t

V

U

t

U

₌

₊

_m

_ω

)

sin(

)

(

t

U

t

U

₌

_m

_ω

Source: C.R.Lodahl, et al.: J.Fluid Mech., Vol.373, 1998 Source: A.Scotti, U. Piomelli : Physics of Fluids,13(5), 2001

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5 Turbulent Flows, Characteristic Parameters

0.05

05 .

0

001 .

0

0.001 ≥

≤

+ + +

ω

2 τ

ωυ

ω

u

=

+

ρ

τ

τ w

u

=

)

,

(

)

,

(

~

)

(

)

,

(

x

t

u

x

u

x

t

u

x

t

u

r

=

r

+

r

+

r

′

r

m uc

U

V

a

=

Source: M.Gündogdu, M.Carpinlioglu : JSME int. Journal, 42(3), 1999

Oscillating Turbulent Flow:

_{Pulsating Turbulent Flow:}

)

sin(

)

(

t

V

U

t

U

₌

₊

_m

_ω

)

sin(

)

(

t

U

t

U

₌

_m

_ω

Quasi Steady Flow

Intermediate

Frequency

_{Quasi-Laminar}

=

∫

=

T

w

c

dt

T

₀

~

1 τ

τ

Source: C.R.Lodahl, et al.: J.Fluid Mech., Vol.373, 1998

•Mean parameters little affected

•Discrepancy close to bursting frequency

•Effects in the Stoke-layers

•Phase shift of _

_c

up to 45°

•Mean parameters affected

•_/_

_c

up to 4

•Strong unsteady effects

•Re-laminarization can occur

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6 Near Wall Thermal Response

• Lacking of experimental data for current dominated flow

•Contradictory results in both laminar and turbulent

flow conditions about the effect of oscillations on mean

flow quantities

•Measured a phase shift up to 180

º

_{for the wall heat transfer}

•In low-amplitude pulsating flows (source Valueva 2002)

•Frequency range 20 to 1000Hz

• Measured heat transfer increases

•In wave dominated pulsating flows (source Dec, Keller and Arpaci,1992)

• Frequency range ~100Hz

• Measured heat transfer increases up to a factor of 5 over steady flow

• The Reynolds analogy proved not to hold

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7 

Viscous Boundary Layer

• Thermal Boundary Layer



Numerical Models

• ISAAC

ε

ν

ε

σ

ν

ε

σ

ν

ε

µ

ε

~

2

1

1 k

f

C

D

E

x

k

f

c

k

f

c

x

u

t

x

k

x

k

u

t

k

t

i

t

i

k

t

i

=

+

=

+













∂













+

∂

+

−

=

∂

+

∂













∂













+

∂

+

−

=

∂

+

∂

P

2 2 2

y

k

D

y

k

w w

ν

ε

=

∂

=

•Pressure-strain

•Molecular viscosity

Non zero value of

_ε

at the wall

j

i

x

u

∂

′

−

=

P







=

≠

=

j

i

j

i

ij

for

3 for

0 δ

ij ij j i i j j i t j i

k

x

u

x

u

x

u

_υ

_δ

3

2 ~

3

2 ~

~

−













∂

−

∂

+

∂

=

′

−

•Low-Reynolds model

coefficients

•Correction for non local

isotropy

• Full Reynolds model

• Critical closure

Pressure-Strain term

(fluctuating pressure)

• Two-equation model

• Inaccurate

formulation

for pulsating flows

• Accurate formulations

for curvature and

rotation

Turbulence Modeling

Source:

Fan, Lakshminarayana

and Barnett, AIAA J.

Oct. 1993

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8 Strategy of Investigation

Navier-Stokes CFD Code: ISAAC

• High Turbulence Capabilities

• K-_ Models

:

• Low-Reynolds

•SAA : Speziale,Abid,Anderson

•ZSGS : Zhang,So,Gatski,Speziale

•ZSSL : Zhang,So,Speziale,Lai

• High-Reynolds

•HIGH RE: standard

•RNG : Renormalization Group

•ADRM: Anisotropic Dissipation Rate

• K-_ Models:

•Low-Reynolds

•K OMEGA: Wilcox

• Reynolds Stress Model

• Explicit Algebraic Reynolds Stress Model

Problems

•Code applicability to Incompressible test cases

•Proper extension of B.C. to oscillating flows



Viscous Boundary Layer

• Thermal Boundary Layer

• Numerical Models



ISAAC

• Developed by Morrison, J. H for a NASA contract

Now freely available from www.sourceforge.com

• Structured

• Multigrid

• Unsteady

• Explicit Runge-Kutta

• Implicit Pseudo Time Stepping

( up to II order)

• Implicit:

•AF3F: Diagonalized Spatially Split Approx. Factorization

• Compressible:

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9 Conclusions



An overview on experimental evidences on pulsating flow has

been presented



The necessity of a better understanding of the aero-thermal

near-wall flow behavior has been in deep analyzed



An extensive bibliography on test cases and proposed models

for unsteady flows have been acquired.



The ISAAC code has been tested for the future investigations



The limitations of the code have been addressed

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12 Turbulence Modeling

• Algebraic eddy viscosity models

• Two equations high-Reynolds model + Wall functions

• Two equations low-Reynolds model

• Full Reynolds stress models

• Two equations low Reynolds model +

Unsteady near-wall corrections

Inaccurate: Important role of transport of turbulent quantities

Inaccurate: Steady flow wall function not suited

Inaccurate: Eddy viscosity isotropy assumption

Inaccurate: Insufficient near wall treatment



Viscous Boundary Layer

• Thermal Boundary Layer



Numerical Models

• ISAAC

Source:

Fan, Lakshminarayana

and Barnett, AIAA J.

Oct. 1993

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• Sustainable Energy

• Combustion Instabilities

• Near-wall fluid structures

• Strategy of investigation

References: AERODYNAMICS

•General overview aerodynamics:

•Low amplitude

•Gundogdu and Carpinlioglu,JSME,vol42,n3,1999

•Scotti and Piomelli,physics of fluid,vol13,n5,2001

•Low and High amplitude

•Lodahl and Sumer and Fredsoe, J.Fluid Mech,vol373,1998

•Test case also (pipe water)

•Koehler and Patankar and Ibele,NASA-CR187177

•Test cases

•Cousteix and Houdeville (flat plate air)

•Tardu and Binder and Blackwelder (pipe water)

•Ideas for unsteady turbulence models:

•Fan and Lakshminarayana,AIAA,vol31,1993

•Mankbadi and Liu, J.Fluid Mech,vol238,1992

•Hanjalic and Stosic

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• Sustainable Energy

• Combustion Instabilities

• Near-wall fluid structures

• Strategy of investigation

References: HEAT TRANSFER

•Low amplitude

•Valueva,High Temperature,vol37,n5,1999

•Test case also ( oscillating, compressible incompressible)

•Ideas for unsteady turbulence model

•Ideas for unsteady Energy equation

•High amplitude

•Dec and Keller,Int.J.Heat Mass Transfer,vol35,n9,1992

•Test case also (oscillating combustor tail pipe)

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• Sustainable Energy

• Combustion Instabilities

• Near-wall fluid structures

• Strategy of investigation

•Morrison, J. H., Flux Difference Split Scheme for Turbulent Transport Equations, AIAA Paper 90-5251, October 1990.

•Morrison, J. H., A Compressible Navier-Stokes Solver with Two-Equation and Reynolds Stress Turbulence Closure Models, NASA CR-4440, May 1992.

•Morrison, J. H. and Korte, J. J., Implementation of Vigneron's Streamwise Pressure Gradient Approximation in Parabolized Navier-Stokes Equations, AIAA Journal, Vol. 30, No. 12, November 1992.

•Morrison, J. H., Gatski, T. B., Sommer, T. P., Zhang, H. S., and So, R. M. C., Evaluation of a Near-Wall Turbulent Closure Model in Predicting Compressible Ramp Flows, Near-Wall Turbulent Flows, Eds. R. M. C. So, C. G. Speziale, and B. E. Launder, Elsevier Science Publishers B.V., 1993.

•Chenault, C. F., Development and Implementation of a Scramjet Cycle Analysis Code With a Finite-Rate-Chemistry Combustion Model For Use on A Personal Computer, Masters Thesis, Air Force Institute of Technology, December 1993. AFIT/GAE/ENY/93D-7

•Abid, R., Gatski, T. B., and Morrison, J. H., Assessment of Pressure-Strain Models in Predicting Compressible, Turbulent Ramp Flows, AIAA Journal, Vol. 33, No. 1, January 1995.

•Vahala, G., Vahala, L., Morrison, J., Krasheninnikov, S., and Sigmar, D., Effects of Neutral Three-Dimensional Turbulence in the Gas Blanket Regime for Divertors, Physics Letters A, Vol. 205, 1995, pp. 266-273.

•Vahala, G., Vahala, L., Morrison, J., Krasheninnikov, S., and Sigmar, D., Toroidal Wall Heat Flux and Conductivity Profiles Due to Neutral 3D Turbulence in the Gas Blanket Regime for Divertors, Contrib. Plasma Phys., Vol. 36, No. 2/3, 1996, pp. 304-308.

•Gatski, T. B., Prediction of Airfoil Characteristics with Higher Order Turbulence Models, NASA Technical Memorandum 110246, April, 1996. Abstract | PDF | Postscript

•Gatski, T. B., Airfoil Stall Prediction Using a Two-Equation and an Explicit Algebraic Stress Model, Advances in Turbulence VI, Eds. Gavrilakis, S., Machiels, L., and Monkewitz, P. A., Kluwer Academic Publishers, 1996.

•Ristorcelli, J. R. and Morrison, J. H., The Favre-Reynolds Average Distinction and a Consistent Gradient Transport Expression for the Dissipation, Physics of Fluids, Vol. 8, No. 9, September 1996.

•Abid, R., Morrison, J. H., Gatski, T. B., and Speziale, C. G., Prediction of Aerodynamic Flows with a New Explicit Algebraic Stress Model, AIAA Journal, Vol. 34, No. 12, December 1996.

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• Sustainable Energy

• Combustion Instabilities

• Near-wall fluid structures

• Strategy of investigation

• Vahala, G., Vahala, L., Morrison, J., Krasheninnikov, S., and Sigmar, D., K-e Compressible 3D Neutral Fluid

Turbulence Modelling of the Effect of Toroidal Cavities on Flame-Front Propagation in the Gas-Blanket Regime for

Tokamak Divertors, J. Plasma Physics, Vol. 57, Part 1, 1997, pp. 155-173.

• Woodruff, S. L., Morrison, J. H., and Hussaini, M. Y., Evaluation of Several Turbulence Models in a

Multiple-Element Airfoil Computation, AIAA Paper 98-0327, January 1998.

• Chenault, C. F., Analysis of Turbulence Models as Applied to Two- and Three-Dimensional Injection Flows, Ph.D.

Dissertation, Air Force Institute of Technology, March 1998. AFIT/DS/ENY/98M-01

• Chenault, C. F., Beran, P. S., and Bowersox, R. D. W., Second-Order Reynolds Stress Turbulence Modeling of

Three-Dimensional Oblique Supersonic Injection, AIAA Paper 98-3425, July 1998.

• Chenault, C. F. and Beran, P. S., K-Epsilon and Reynolds Stress Turbulence Model Comparisons for

Two-Dimensional Injection Flows, AIAA Journal, Vol. 36, No. 8, pp. 1401-1412, August 1998.

• Morrison, J. H., Numerical Study of Turbulence Model Predictions for the MD 30P/30N and the NHLP-2D

Three-Element Highlift Configurations, NASA CR-1998-208967, December 1998. Abstract | PDF | Postscript

• Chenault, C. F., Beran, P. S., and Bowersox, R. D. W., Numerical Investigation of Supersonic Injection Using a

Reynolds-Stress Turbulence Model, AIAA Journal, Vol. 37, No. 10, October 1999.

• Woodruff, S. L., Seiner, J. M., Hussaini, M. Y., and Erlebacher, G., Evaluation of Turbulence-Model Performance in

Jet Flows, AIAA Journal, Vol. 39, No. 12, December 2001.

• Morrison, J. H., Panaras, A. G., Gatski, T. B., and Georgantopoulos, G. A., Analysis of Extensive Cross-Flow

Separation using Higher-Order RANS Closure Models, AIAA Paper 2003-3532, June 2003. Abstract | PDF |