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

Effect of Injector Wall Heat Flux on Cryogenic Injection

Banuti, Daniel and Hannemann, Klaus (2010) Effect of Injector Wall Heat Flux on Cryogenic Injection. 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 25 - 28 Jul 2010, Nashville, USA. ISBN 978-1-60086-747-7.

This is the latest version of this item.

[img]
Preview
PDF - Requires a PDF viewer such as GSview, Xpdf or Adobe Acrobat Reader
1MB

Official URL: http://www.aiaa.org

Abstract

This paper reports on numerical investigation and discussion of a cryogenic injection test case. This is a first step towards a numerical model for high pressure liquid rocket engine injection. Experiments with nitrogen injection at supercritical pressures are an accepted way of studying flow phenomena relevant for high pressure liquid rocket engines without introducing the complexities of mixing and combustion. CFD simulations of these cryogenic injection cases are found to typically agree on predicting a region of constant high density, extending some 10 injector diameters downstream into the chamber. This is in agreement with the traditional interpretation of liquid injection where instabilities on the phase boundary grow until the jet disintegrates. However, many experiments do not show this behavior: exceeding the critical pressure of the injected fluid, phase interfaces seize to exist, the jet tends to behave more like a dense gas jet with a rapid drop off of density starting at the injector exit. It is thus unclear whether the concept of a liquid core length is still true for thermodynamic states at temperatures near the critical point and supercritical pressures. To study this, experimental and numerical boundary conditions have been analyzed. Computations have been carried out using the DLR TAU code extended by a treatment for real gas thermodynamics. It has been found that the absence of a dense core, as found in experiments, can be reproduced numerically if numerical boundary conditions are chosen appropriately: taking into account heat transfer inside the injector leads to a preheating of the cryogenic stream and the development of a distinct radial density profile. This preheated jet then shows the more realistic immediate reduction of density instead of a dense core.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:Effect of Injector Wall Heat Flux on Cryogenic Injection
Authors:
AuthorsInstitution or Email of Authors
Banuti, Danieldaniel.banuti@dlr.de
Hannemann, Klausklaus.hannemann@dlr.de
Date:2010
Refereed publication:No
In ISI Web of Science:No
Page Range:pp. 1-9
Series Name:AIAA Meeting Papers on Disc, DVD-ROM
ISBN:978-1-60086-747-7
Status:Published
Keywords:propulsion, cryogenic, CFD, injection
Event Title:46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit
Event Location:Nashville, USA
Event Type:international Conference
Event Dates:25 - 28 Jul 2010
Organizer:AIAA
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Leitprojekt - Propulsion 2010 / CFD und Simulation (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Daniel Banuti
Deposited On:17 Aug 2010 15:25
Last Modified:12 Dec 2013 20:59

Available Versions of this Item

  • Effect of Injector Wall Heat Flux on Cryogenic Injection. (deposited 17 Aug 2010 15:25) [Currently Displayed]

Repository Staff Only: item control page

Browse
Search
Help & Contact
Informationen
electronic library is running on EPrints 3.3.12
Copyright © 2008-2012 German Aerospace Center (DLR). All rights reserved.