A physical approach for development of computational ...mmcp2009.jinr.ru/pdf/Martynenko_CIAM.pdf ·...
Transcript of A physical approach for development of computational ...mmcp2009.jinr.ru/pdf/Martynenko_CIAM.pdf ·...
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A physical approach for development of computational algorithms A physical approach for development of computational algorithms for solving the Navierfor solving the Navier--Stokes equations Stokes equations and its application in jet engine analysisand its application in jet engine analysis
Contents:
1) Main difficulties of the efficient algorithm development
2) Simulation of incompressible flowsa) description of unified algorithmb) solution of benchmark problemsc) solution of applied problems
3) Simulation of compressible flowsa) strong nonlinear nature of compressible Navier-Stokes equationsb) flow in Laval nozzle
4) Flows with determinate mass flow rate
Marу L. Yanovskaya, Sergey I. MartynenkoFSUE Central Institute of Aviation Motors n.a. P.I. Baranov, Moscow, Russia
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TwoTwo--dimensional incompressible Navierdimensional incompressible Navier--Stokes equationsStokes equations
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Main difficulties of numerical solution of the NavierMain difficulties of numerical solution of the Navier--Stokes equationsStokes equations
1) Nonlinear nature of the Navier-Stokes equations2) Singular perturbation of the momentum equations3) Structure of the Navier-Stokes equations
The system cannot be solved by standard methods because of a33=0.
Main difficulties of the pressure computation1) Absence of equation for the pressure computation2) Absence of boundary conditions for the pressure correction3) Required high accuracy of pressure computation
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Segregated (decoupled) algorithms Segregated (decoupled) algorithms
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Method SIMPLE (Method SIMPLE (SpaldingSpalding B.B., Patankar S., 1972), Patankar S., 1972)
Main disadvantage of similar methods consists of the artificial boundary conditions for pressure (correction).
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Method of artificial Method of artificial compressibilitycompressibility ((ChorinChorin AA., 1967)., 1967)
The method does not require some artificial boundary conditions for pressure. However convergence rate is slow.
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Coupled algorithmsCoupled algorithms
It is very difficult to apply the coupled methods for computations of compressible flows.
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Simplified NavierSimplified Navier--Stokes equationsStokes equations
Since p=p(x), very efficient numerical methods for simplified Navier-Stokes equations have been proposed and developed (for example, the secant method of Briley W, 1974).
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Basic idea: the pressure decompositionBasic idea: the pressure decomposition
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Steady flow in cavity (no directed fluid flows)Steady flow in cavity (no directed fluid flows)
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Predictor (Predictor (auxiliaryauxiliary problem)problem)
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Corrector (main problem)Corrector (main problem)
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Structure of algorithmStructure of algorithm(mass flow rate is given)(mass flow rate is given)
1. Auxiliary problem2. Main problem3. Check convergence: return to item 1 (if necessary)
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Steady flow in cavitySteady flow in cavity ((Re=100Re=100, , staggered grid staggered grid 101101××101)101)
Classical decoupled algorithm:
Proposed algorithm:Proposed algorithm:
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Distribution of Distribution of uu velocity component in vertical sectionvelocity component in vertical section
(0.5, )
0
1
0.5
Y
0 0.5
1
Yu
xvX
1
( , 0.5)
X
1
y
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Reduction of residual of the continuity equationReduction of residual of the continuity equation
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-0.115
-0.1
-0.1
-0.1-0.065
-0.065
-0.065
-0.065
-0.065
-0.015
-0.015
-0.015
-0.015
-0.015
-0.015
-0.015
-0.001
0.001
-0.001
-0.001 -0.001
-0.0
-0.001
-0.001
5E-05
5E-05
X
Y
0 0.2 0.4 0.6 0.8 10
0.2
0.4
0.6
0.8
1
Steady flow in cavitySteady flow in cavity ((Re=100Re=1000, 0, staggered grid staggered grid 301301××3301)01)Isolines of the stream function
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Steady flow in cavitySteady flow in cavity ((Re=100Re=1000, 0, staggered grid staggered grid 301301××3301)01)Isobars (p(0,0)=0)
-0.111
-0.105
-0.105
-0.09
-0.09-0.09
-0.09
-0.07
-0.07-0.07
-0.07
0.05
-0.05
-0.05
-0.05
-0.05
-0.05
-0.03
-0.03
-0.03
-0.03-0.03
-0.03
-0.01-0.01
-0.01
-0.005
-0.005
-0.005
0
0
0
0.2
X
Y
0 0.2 0.4 0.6 0.8 10
0.2
0.4
0.6
0.8
1
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Velocity components in middle sections (Re=1000)Velocity components in middle sections (Re=1000)
(0.5, )u y0.6
0.20.0-0.4
-0.2
0.2
0.0
0.4
y0.4 0.6 0.8
0.8
1.0
( , 0.5)-0.4
-0.61.0 0.0 0.2
0.0
-0.2 v
0.60.4 x 0.8
x
1.0
0.4
0.2
Reduction of the computational efforts is ∼ 30…50%.
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Remarks on the predictor Remarks on the predictor
1) Equations of auxiliary problem are solved by numerical methods developed for simplified Navier-Stokes equations.
2) Mass conservation equations are considered as a priori information about velocity components.
3) Velocity and “pressure” components (px, py, pz ) are computed in coupled manner.
4) Local nature of the algorithm for solving the auxiliary problem (without global linearization).
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Steady backward-facing step flow (Re=800, staggered grid 101 ×1401)
Reduction of the computational efforts is in ∼ 400 times.
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Steady backward-facing step flow (Re=800, staggered grid 101 ×1401)Isolines of the stream function
0 2 4 6 8 10 12 140.0
0.2
0.4
0.6
0.8
1.0
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Steady backward-facing step flow (Re=800, staggered grid 101 ×1401)Isobars
0 2 4 6 8 10 12 140.0
0.2
0.4
0.6
0.8
1.0
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Applied problemApplied problem: : flow in catalyst of micro liquidflow in catalyst of micro liquid--propellant enginepropellant engine
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Catalyst of micro liquidCatalyst of micro liquid--propellant enginepropellant engine
1 2 31
catalyst needle(iridium)
axis of symmetry
solid wall
29.2 10 m-6
.
15 10 m.
-6
300 10 m-6. 3000 10 m. -6
250
10
m.
-6
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Staggered grid in catalyst of micro liquidStaggered grid in catalyst of micro liquid--propellant engine propellant engine (385(385××3150)3150)
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IsolinesIsolines of the of the streamstream functionfunction ((Re=350)Re=350)
0.50 0.55 0.60 0.65 0.70 0.75 0.80 0.850.00
0.10
0.20
0.30
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IsolinesIsolines of the of the streamstream functionfunction ((Re=350)Re=350)
4.40 4.50 4.600.00
0.10
0.20
0.30
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Isobars (Re=350)Isobars (Re=350)
0.5 0.55 0.6 0.65 0.7 0.75 0.8 0.850.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
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Weak compressible flowsWeak compressible flowsH=500·10-6m
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Compressible flowsCompressible flows
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FLUENT softwareFLUENT software
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FLUENT softwareFLUENT software
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FLUENT softwareFLUENT software
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Compressible flow in driven cavityCompressible flow in driven cavity
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Compressible flow in driven cavity: predictorCompressible flow in driven cavity: predictor
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Compressible flow in driven cavity: correctorCompressible flow in driven cavity: corrector
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Simulation of compressible flow in Laval nozzleSimulation of compressible flow in Laval nozzle
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BodyBody--fitted coordinates fitted coordinates
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Mapping of physical domain onto computational domainMapping of physical domain onto computational domain
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Draft grid in Laval nozzleDraft grid in Laval nozzle
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Draft grid in Laval nozzle near throatDraft grid in Laval nozzle near throat
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XX--direction velocity [m/s]direction velocity [m/s]
X
Y
0 0.0005 0.001 0.0015 0.002 0.0025 0.0030
0.0005
0.001
X Velocity: 100 400 700 1000
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XX--direction velocity [m/s] near direction velocity [m/s] near throatthroat
X
Y
0.0004 0.0005 0.0006 0.0007 0.000
0.0001
0.0002
0.0003
X Velocity: 100 400 700 1000
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Pressure drop PPressure drop P00--P [Pa]P [Pa]
X
Y
0 0.0005 0.001 0.0015 0.002 0.0025 0.0030
0.0005
0.001
Pressure: -95000 -65000 -35000 -5000
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Pressure drop PPressure drop P00--P [Pa] near P [Pa] near throatthroat
X
Y
0.0004 0.0005 0.0006 0.0007 0.000
0.0001
0.0002
0.0003
Pressure: -95000 -65000 -35000 -5000
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Static temperature [K]Static temperature [K]
X
Y
0 0.0005 0.001 0.0015 0.002 0.0025 0.0030
0.0005
0.001
Temperature: 50 100 150 175 200 250 300 350 400 450
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Static temperature [K] near Static temperature [K] near throatthroat
X
Y
0.0004 0.0005 0.0006 0.0007 0.000
0.0001
0.0002
0.0003
Temperature: 50 100 200 250 275 300 350 375 385 400 425 450
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Distribution pressure [Pa] along the nozzle axisDistribution pressure [Pa] along the nozzle axisthroat
0 0.001 0.002 0.003 0.004x, m
0x100
2x104
4x104
6x104
8x104
1x105
Pres
sure
, Pa
outlet
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Flows with determinate mass flow rate Flows with determinate mass flow rate
Geometry of problem about moving plunger
1. Main problem 2. Check convergence: continue if necessary3. Auxiliary problem
Structure of algorithmStructure of algorithm(mass flow rate is determined)(mass flow rate is determined)
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Flows with Flows with determinateddeterminated mass flow rate mass flow rate
Isolines Isobars
Re=200Re=200, , staggered grid 2staggered grid 20101××24240101
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CONCLUSIONSCONCLUSIONS
Unified algorithm for solving (in)compressible Navier-Stokes equationsin primitive variables is proposed and developed. The algorithm uses physical aspects of hydrodynamics for reduction of computationalefforts. As a result, the algorithm can be incorporated with anymathematical method for solving Navier-Stokes equations. Impressive reduction of computational work is observed for directed fluid flows.
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