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Combustion efficiency sensitivity studies of the API injector concept

Deeken, J. and Suslov, D. and Haidn, O. and Schlechtriem, S. (2011) Combustion efficiency sensitivity studies of the API injector concept. In: Proceedings (AIAA 2011-793). 49th AIAA Aerospace Sciences Meeting, 4. - 7. Jan. 2011, Orlando, Florida, USA.

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Since a few years DLR Lampoldshausen has been engaged in the development of a new injection concept for cryogenic liquid propellant rocket engines. This concept bases on the injection of the liquid oxygen through a large number of simple tubes while the entire hydrogen is injected through the porous face plate.3, 4 The key feature of the API concept is the independency of the atomization, vaporization, mixing and combustion performance of initial injection conditions such as velocity ratio, momentum fluxratio, Weber number or other non-dimensional parameters which are generally deemed important. This statement will be supported by data optained with a 50mm subscale combustion chamber. The influence of the velocity ratio at injection will be shown through a variation of the propellant mixture ratio and/or the chamber pressure.

Document Type:Conference or Workshop Item (Speech, Paper)
Title:Combustion efficiency sensitivity studies of the API injector concept
AuthorsInstitution or Email of Authors
Deeken, J.Jan.Deeken@dlr.de
Suslov, D.Dmitry.Suslov@dlr.de
Haidn, O.Oskar.Haidn@dlr.de
Schlechtriem, S.Stefan.Schlechtriem@dlr.de
Journal or Publication Title:Proceedings
Keywords:rocket engines, combustion
Event Title:49th AIAA Aerospace Sciences Meeting
Event Location:Orlando, Florida, USA
Event Type:international Conference
Event Dates:4. - 7. Jan. 2011
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 - Antriebsystemtechnik - Schubkammertechnologie und Hochdruckverbrennung (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Raketenantriebe
Institute of Space Propulsion > Technologie
Deposited By: Michaela Hanke
Deposited On:30 Nov 2011 12:19
Last Modified:30 Nov 2011 12:19

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