elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Numerical simulation of cryogenic flows in rocket combustion chambers

Fechter, Stefan and Horchler, Tim and Karl, Sebastian and Hannemann, Klaus and Suslov, Dmitry and Hardi, Justin and Oschwald, Michael (2018) Numerical simulation of cryogenic flows in rocket combustion chambers. 2ND INTERNATIONAL SEMINAR ON NON-IDEAL COMPRESSIBLE-FLUID DYNAMICS FOR PROPULSION & POWER, 04.-05.10.2018, Bochum, Deutschland.

Full text not available from this repository.

Abstract

The accurate numerical simulation of combustion and atomization processes in rocket combustion chambers is a key element for the design of future space transportation vehicles. The main challenges include the consistent approximation of thermodynamic effects within a broad range from cryogenic temperatures at the injection to high temperature within the flame. This broad temperature range combined with high-pressure conditions is challenging for the stability of the numerical method. Another numerical challenge is to resolve and/or model the disimilar length scales: First to mention is the accurate prediction of the jet breakup of the propellants (e.g. cryogenic oxygen and/or cryogenic hydrogen) and the cryogenic mixture. Second to mention are disimilar length scales between the liquid injection conditions (e.g. liquid oxygen) and the gaseous gases in the flame. In literature the numerical prediction of cryogenic injection processes is an open question how cryogenic sub- and supercritical injection process can be modeled (see e.\,g. the discussion in Oefelein and Bellan) and which physical processes are important to characterize the breakup and the evaporation processes correctly. At these conditions, as found e.\,g. in rocket combustion chambers, all fluid properties have a strong sensitivity to changes in the (non-linear) equation of state. One major challenge is the strong discontinuity in the flow field due to the phase boundary. Another open question is which are the main physical processes that have to be modeled for Reynolds Averaged Navier-Stokes (RANS) based ap proaches, similar to the single-phase turbulence modeling. These turbulence models are of practical importance as they are used to design and assure rocket combustion chambers with many design-type calculations. Detailed numerical simulations (Large Eddy or Direct Numerical Simulations) are still too expensive for those simulations and are used to understand the fundamental flow physics in detail, even the computational resources increased significantly in the last years. In this talk we discuss the numerical methodology to handle cryogenic flows in combustion chambers using a RANS based method. The numerical development is based on the DLR flow solver TAU for which some extensions are proposed that handle the mixture of cryogenic fluids. This includes the numerical framework for an efficient evaluation of cryogenic mixture states as well as state of the art mixture rules for viscosity and heat transfer coefficients. A double-f lux based numerical method is included to prevent spurious numerical oscillations in cryogenic mixture states as proposed by Ma et al. for trans-critical flows. The framework is validated with experimental results for a lab-scale combustion chamber experiment conducted at the DLR branch in Lampoldshausen. During the BKC test campaign a single-injector cryogenic combustion chamber was fired at several combustion chamber pressures ranging from sub- to supercritical conditions. The combustion chamber was fully equipped with OH* and shadowgraphic imaging aiming to provide extensive validation data for numerical meth ods. In addition wall temperature and pressure measurements on the outer combustion chamber walls are available.

Item URL in elib:https://elib.dlr.de/122265/
Document Type:Conference or Workshop Item (Speech)
Title:Numerical simulation of cryogenic flows in rocket combustion chambers
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Fechter, StefanStefan.Fechter (at) dlr.deUNSPECIFIED
Horchler, Timtim.horchler (at) dlr.deUNSPECIFIED
Karl, SebastianSebastian.Karl (at) dlr.deUNSPECIFIED
Hannemann, Klausklaus.hannemann (at) dlr.deUNSPECIFIED
Suslov, DmitryDmitry.Suslov (at) dlr.deUNSPECIFIED
Hardi, JustinJustin.Hardi (at) dlr.dehttps://orcid.org/0000-0003-3258-5261
Oschwald, MichaelMichael.Oschwald (at) dlr.dehttps://orcid.org/0000-0002-9579-9825
Date:4 October 2018
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Tau, Rocket Combustion Chamber, TwoPhaseFlow
Event Title:2ND INTERNATIONAL SEMINAR ON NON-IDEAL COMPRESSIBLE-FLUID DYNAMICS FOR PROPULSION & POWER
Event Location:Bochum, Deutschland
Event Type:international Conference
Event Dates:04.-05.10.2018
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):Proj TAUROS (TAU for Rocket Thrust Chamber Simulation)
Location: Göttingen , Lampoldshausen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Institute of Space Propulsion > Rocket Propulsion
Deposited By: Fechter, Stefan
Deposited On:17 Oct 2018 08:05
Last Modified:09 Nov 2018 17:19

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.