Investigation of two dimensional thermal loads in the region near the injector head of a high pressure subscale combustion chamber

D. I. Suslov, R. Arnold, O. J. Haidn

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

19 Scopus citations

Abstract

Optimization of heat transfer management is a key issue in designing a rocket combustion chamber. This paper presents the new test specimen and the measurement technique that has been developed und successfully used by the Institute of Space Propulsion for high resolution investigations of the influence of injector-wall interactions on heat transfer in a subscale combustion chamber. The new measurement method allows obtaining two dimensional heat load distribution on the hot gas side at real rocket engine-like conditions at combustion chamber pressures up to 15 MPa. The presented investigations have been performed at the European Research and Technology Test Facility P8 for cryogenic subscale rocket engines.

Original languageEnglish
Title of host publication47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
StatePublished - 2009
Externally publishedYes
Event47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition - Orlando, FL, United States
Duration: 5 Jan 20098 Jan 2009

Publication series

Name47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition

Conference

Conference47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
Country/TerritoryUnited States
CityOrlando, FL
Period5/01/098/01/09

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