1 Institut für Verbrennungstechnik - Institute of Combustion Technology

Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

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)

Boundary Layers Response to PulsatingCombustor Flow

Fluistcom Internal MeetingCIMNE Barcellona, June 2005

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Overview

Pulsating and Oscillatory Flows Experimental Evidences

Aerodynamic Boundary Layer Response Thermal Boundary Layer Response

Numerical Simulations High Reynolds vs. Low Reynolds Turbulence Models Near wall turbulence modeling, strategy of investigation

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Pulsating Flow Pioneering Studies:Flat Plate

J. Cousteix and R. Houdeville VKI Lecture Series 1983

Pulsating Flow •Aerodynamic response •Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Displacement thickness

dyU

yU

e

0

1

)(1

“The displacement surfacelooks like a wavy wallmoving back and forth”

Pulsating Flow •Aerodynamic response •Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Near Wall Aerodynamic Response in Pulsating Pipe Flows

Oscillating Flow:

VD

c Rem

w

aURe

2

TUa m

2slsl

DR

2

Turbulent 800Re

Laminar 400Re

s

s

l

l

s

l

lUs

0Re

Pulsating Flow:

)sin()( tUVtU m )sin()( tUtU m Source: C.R.Lodahl, et al.: J.Fluid Mech., Vol.373, 1998

Source: A.Scotti, U. Piomelli :

Physics of Fluids,13(5), 2001

•Pulsating Flow Aerodynamic response •Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Turbulent Flows, Characteristic Parameters

0.05

05.0001.0

0.001

2

u

wu

),(),(~

)(),( txutxuxutxu

muc U

Va

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

Oscillating Turbulent Flow: Pulsating Turbulent Flow:

)sin()( tUVtU m )sin()( tUtU m

Quasi Steady Flow

Intermediate FrequencyQuasi-Laminar

T

wc

dtT 0

~1

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 τc up to 45°

•Mean parameters affected•τ/τc up to 4

•Strong unsteady effects•Re-laminarization can occur

•Pulsating Flow Aerodynamic response •Thermal response •Modeling

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Near Wall Thermal Response

• Oscillation Amplitude Unknown• Air pipe Flow• Wide Range of Re number • Wide Range of frequency

Source: M.A. Habib et al. , 2004

•Pulsating Flow Aerodynamic response Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Near Wall Thermal Response Source: A.R. Barker et al. , 2000

• Low Amplitude Oscillations• Found No Heat Transfer Increase• Heated Pipe Flow• Wide Range of Re number • + Plays an Important Role• Phase Shift up to 180o

•Pulsating Flow Aerodynamic response Thermal response •Modeling

9 Institut für Verbrennungstechnik - Institute of Combustion Technology

Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Near Wall Thermal Response

• High Amplitude Pulsating Flow• Heated pipe Flow• Re-Laminarization Effects• Narrow Range of Re number • Wide Range of frequency

Source: Y. Ishino, 1996

•Pulsating Flow Aerodynamic response Thermal response •Modeling

10 Institut für Verbrennungstechnik - Institute of Combustion Technology

Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Near Wall Thermal Response

• Resonant Channel• Heated pipe Flow• Resonant Standing Wave • Frequency range 20 to 1000Hz• Low Amplitude Oscillations

Source: E. P. Valueva, 2000

•Pulsating Flow Aerodynamic response Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Near Wall Thermal Response

• Pulsating Motor Tail Pipe• Cooled pipe Flow• Frequency Range 100 Hz• High Amplitude Oscillations • Temperature Inlet Fluctuations• Flow Conditions Similar to Combustor Flow• Proved Failure of the Reynolds Analogy

Source: E. Dec et al. , 1991

•Pulsating Flow Aerodynamic response Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

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 180º for the wall heat transfer (source Barker, Ishino )• Measured Heat Transfer Increasing

• In low-amplitude resonant pulsating flows (source Valueva)• In low-frequency wave dominated pulsating flows (source Ishino)• In Temperature fluctuating pulsating Flows (100 Hz) (source Dec)

• The Reynolds analogy proved not to hold in some cases

•Pulsating Flow Aerodynamic response Thermal response •Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

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

Source:Fan, Lakshminarayanaand Barnett, AIAA J.Oct. 1993

•Pulsating Flow Aerodynamic response •Thermal response Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

Turbulence ModelingLow vs High Reynolds Turbulence Models

•Pulsating Flow Aerodynamic response •Thermal response Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

~

~

~~~~~

2

2

2211

kfC

D

Exxk

fck

fcx

ut

x

k

xx

ku

t

k

t

i

t

iii

ik

t

iii

P

P

22

2

y

kD

y

kww

•Pressure-strain•Molecular viscosity

Non zero value of at the wall

j

iii x

uuu

P

ji

jiij for 3

for 0ijij

j

i

i

j

j

itji k

x

u

x

u

x

uuu

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, Lakshminarayanaand Barnett, AIAA J.Oct. 1993

•Pulsating Flow Aerodynamic response •Thermal response Modeling

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

source:Abe et al. 1995

TkT 2

1

iiT x

TTu

P

Turbulence Modeling

iTTiTi

iT cTuk

cx

TP P21

jtj x

TTu

hT k TTh kkf /,/

source: Rogers et al. 1989 source: Gibson and Launder 1976

source:Koehler, Patankar1991

•Pulsating Flow Aerodynamic response •Thermal response Modeling

j

T

h

th

jTT

j

Tj

T

x

kf

xx

ku

t

k

P

ux

Pu

x

Pu

t

P

cTu

x

T

xt

T

jj

jj

pj

jj

1

j

Tth

i

TDD

TDD

TpT

T

Tp

j

Tj

T

xf

xkfc

k

kfc

kc

kc

xu

t

221121 PP

TTT

iTiTTj kk

kkTu

PP

P2

jt

t

jtj x

T

x

TTu

Pr

Reynolds AnalogyHypothesis

17 Institut für Verbrennungstechnik - Institute of Combustion Technology

Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

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 has been acquired The limitations of steady state wall functions have been issued

(cold flow) Hot flow unsteady simulation with different turbulent

modeling are in progress

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Questions ?

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Extras

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

source:Abe et al. 1995

TkT 2

1

iiT x

TTu

P

TTT

iTiTTj

j

Tth

i

TDD

TDD

TpT

T

Tp

j

Tj

T

j

T

h

th

jTT

j

Tj

T

jj

jj

pj

jj

kk

kkTu

xf

xkfc

k

kfc

kc

kc

xu

t

x

kf

xx

ku

t

k

ux

Pu

x

Pu

t

P

cTu

x

T

xt

T

PPP

PP

P

2

1

221121

Turbulence Modeling

iTTiTi

iT cTuk

cx

TP P21

jtj x

TTu

hT k TTh kkf /,/

source: Rogers et al. 1989 source: Gibson and Launder 1976

source:Koehler, Patankar1991

•Pulsating Flow Aerodynamic response •Thermal response Modeling

21 Institut für Verbrennungstechnik - Institute of Combustion Technology

Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

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Deutsches Zentrum für Luft- und Raumfahrt e.V. German Aerospace Center

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•Rodi and Scheuerer,J.Fluids Eng.,vol108,1986

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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

•Barker,Ffowcs Williams, Int.J.Heat and Mass Transfer 43(),2000•High amplitude

•Dec and Keller, Int.J.Heat and Mass Transfer,vol35,n9,1992•Ishino et al. Heat Transfer Japanese Research 25(5),1996

Test case also (oscillating combustor tail pipe) •Ideas for unsteady turbulence models:

•Rhee, Sung Int.J. Heat Fluid Flow 18(1),1996 •Abe et al Int.J.Heat and Mass Transfer, 38(8)