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Measurements and modelling of wall heat fluxes in rocket combustion chamber with porous injector head

Zhukov, Victor / V. P. and Suslov, Dmitry (2016) Measurements and modelling of wall heat fluxes in rocket combustion chamber with porous injector head. Aerospace Science and Technology, 48, pp. 67-74. Elsevier. DOI: 10.1016/j.ast.2015.10.021 ISSN 1270-9638

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Abstract

A rocket combustion chamber with a porous injector head, which is a new concept for injecting propellants, is tested. The hot-fire tests are carried out using cryogenic oxygen and hydrogen at the mass ratio of oxidizer to fuel of 6 and at pressure of 80 bar. Pressures, wall temperatures, and wall heat fluxes are measured along the axis of the chamber. The wall heat fluxes are determined by the calorimetric method. The wall heat flux has a maximum at a distance of 50–100 mm from the injector plate. To interpret the experimental results, numerical simulations are performed using the commercial CFD code ANSYS CFX. The turbulent flow is modelled by the Favre-averaged Navier–Stokes equations and the shear-stress transport model. The turbulent combustion is modelled using two different models: the extended eddy-dissipation model and the extended coherent flame model. Results obtained with the different models are compared both with experimental data and with each other. The numerical results agree with the experimental data. The extended eddy-dissipation model gives the very good agreement which is achieved by applying additional parameters (‘Flame Temperature’ and ‘Extinction Temperature’) dependent on the mixture fraction.

Item URL in elib:https://elib.dlr.de/107861/
Document Type:Article
Title:Measurements and modelling of wall heat fluxes in rocket combustion chamber with porous injector head
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Zhukov, Victor / V. P.victor.zhukov (at) dlr.dehttps://orcid.org/0000-0003-0110-7419
Suslov, DmitryDmitry.Suslov (at) dlr.dehttps://orcid.org/0000-0002-5160-9292
Date:2016
Journal or Publication Title:Aerospace Science and Technology
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
Volume:48
DOI :10.1016/j.ast.2015.10.021
Page Range:pp. 67-74
Publisher:Elsevier
ISSN:1270-9638
Status:Published
Keywords:Porous injector, rocket engine, heat Transfer, CFD, RANS
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):R - Antriebsystemtechnik - Schubkammertechnologie
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Rocket Propulsion
Deposited By: Hanke, Michaela
Deposited On:23 Nov 2016 10:50
Last Modified:13 Mar 2019 12:21

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