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Film Cooling in a High-Pressure Subscale Combustion Chamber

Suslov, Dmitry and Haidn, Oskar and Arnold, R. (2010) Film Cooling in a High-Pressure Subscale Combustion Chamber. Journal of Propulsion and Power, Vol. 26 (no. 3), pp. 428-438. American Institute of Aeronautics and Astronautics (AIAA). DOI: 10.2514/1.47148

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By the application of film cooling in addition to regenerative cooling, a considerable reduction in thermal and structural loads of rocket combustion-chamber walls can be reached. This paper discusses important influence parameters on film cooling in terms of efficiency of the injected film and wall temperature reduction. For the experimental investigations a high-pressure subscale combustion chamber operated with the cryogenic propellant combination LOX=GH2 was used. A gaseous film with ambient tempered hydrogen was injected in the axial direction at the face plate. Typical film-cooling parameters such as film blowing rate, velocity ratio between film injection velocity and hot-gas velocity, circumferential slot positioning, and film injection slot height were investigated systematically at the European Research and Technology Test Facility P8.

Item URL in elib:https://elib.dlr.de/67447/
Document Type:Article
Title:Film Cooling in a High-Pressure Subscale Combustion Chamber
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Suslov, DmitryDmitry.Suslov (at) dlr.deUNSPECIFIED
Haidn, OskarOskar.Haidn (at) dlr.deUNSPECIFIED
Arnold, R.Astrium, OttobrunnUNSPECIFIED
Journal or Publication Title:Journal of Propulsion and Power
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In ISI Web of Science:Yes
Volume:Vol. 26
DOI :10.2514/1.47148
Page Range:pp. 428-438
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W - no assignment
DLR - Research area:Space
DLR - Program:W - no assignment
DLR - Research theme (Project):W - no assignment (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Technologie
Deposited By: Hanke, Michaela
Deposited On:15 Dec 2010 07:52
Last Modified:01 Dec 2018 19:47

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