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8/3/2019 FENET Noordwijk Oct2003 MPA Steelant
1/22
Division of Propulsion and Aerothermodynamics
E S T E C
CFD Analysis of Rocket Engine
Combustion Chambers
J. Steelant
TOS-MPA
ESA - ESTEC
Acknowledgement: R. Schmehl
Noordwijk
The Netherlands
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
2
Division of Propulsion and Aerothermodynamics
E S T E C
Aestus (Ariane 5)
Avum (Vega)
Oxidizer dome
Fuel feed line
Cooling channels
Combustion chamber
Injectors
Application: Start-Up of Upper Stage Engines
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
3
Division of Propulsion and Aerothermodynamics
E S T E C
Multi-physical phenomena during start-up of LRE
1. Priming of feed lines and domes during start-up:
a. Waterhammer: pressure and expansion waves
b. Phase change i.c.w. cavitation
c. Absorption/desorption of pressurant (Helium)
2. Injection of liquid fuel and oxidizer into the combustion chamber:
a. Atomization evolution in near vacuum conditions
b. Vaporization modes in near vacuum conditionsc. Droplet wall impact and break-up processes
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
4
Division of Propulsion and Aerothermodynamics
E S T E C
Study: priming effects
in vacuum
1. Waterhammer with phase change
2. Unsteady injection process
3. Checking coupling with CC-
instabilities modes
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
5
Division of Propulsion and Aerothermodynamics
E S T E C
CFD-Analysis (1/3)1. Geometrical aspects
- axisymmetric fuel dome with annular injector slits
- spatial : 20K nodes; temporal: 1 sec
P9D1
P_cent
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
6
Division of Propulsion and Aerothermodynamics
E S T E C
CFD-Analysis (2/3)2. Numerical aspects
- Spatial: 3rd order Smart-scheme
- Time: backward Euler (1st order)
- Solver: Pressure-Correction method
3. Physical modelling:
- Transient laminar and isothermal Navier-Stokes equations
- Vapor transport equations:
MMH vaporization/condensation & presence of
non-condensable gas.
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
7
Division of Propulsion and Aerothermodynamics
E S T E C
CFD-Analysis (3/3)Vapor transport equation: f = vapour mass fraction
expressions for Re and Rcderived from Rayleigh-Plessetequation with:
where Ce, Cs = phase change rate coefficients
= surface tension
psat = saturation pressure
Vch = characteristic velocity
feRRffu
t
f+=+
)()(
r
)1(3
2f
ppVCR
l
satlv
chee
=
f
ppVCR
l
sat
lvch
cc
=
3
2
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
8
Division of Propulsion and Aerothermodynamics
E S T E C
Evolution of void fraction
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
9
Division of Propulsion and Aerothermodynamics
E S T E C
Spectral analysis: CFD result for 50mg N2/kg MMH
8/3/2019 FENET Noordwijk Oct2003 MPA Steelant
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
10
Division of Propulsion and Aerothermodynamics
E S T E C
Study: injection processes in near vacuum
1. Thermodynamic behaviour of a liquid jet into near vacuum
2. Atomization behaviour of a liquid jet in near vacuum
3. Transport and deformation of atomized jets (spray)
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
Thermodynamic behaviour in near vacuum: flashing
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
12
Division of Propulsion and Aerothermodynamics
E S T E C
Flash vaporization model
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
13
Division of Propulsion and Aerothermodynamics
E S T E C
Flash vaporization in near vacuum
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
15
Division of Propulsion and Aerothermodynamics
E S T E C
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
Transport and deformation of atomized jets
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
8/3/2019 FENET Noordwijk Oct2003 MPA Steelant
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
18
Division of Propulsion and Aerothermodynamics
E S T E C
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
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ESTEC, 9-10th ofOctober 2003
Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
Wall impact, deposition and rebounce
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Multi-Physics in Rocket EnginesJ. Steelant
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Division of Propulsion and Aerothermodynamics
E S T E C
Wall deposition rate
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Division of Propulsion and Aerothermodynamics
E S T E C
Conclusion
1. Multiphysical processes in LRE
a. Phase change icw waterhammer, cavitation, absorption,during priming
b. Processes during injection Flashing atomization & vaporization
Primary and secondary break-up of jets
Wall deposition/interaction of droplets
2. Modelling and numerical simulation allows qualitative and/orquantitative analysis of processes difficult to analyseexperimentally