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High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes
SJR: 0.137 SNIP: 0.341 CiteScore™: 0.43

ISSN 印刷: 1093-3611
ISSN オンライン: 1940-4360

High Temperature Material Processes: An International Quarterly of High-Technology Plasma Processes

DOI: 10.1615/HighTempMatProc.v9.i3.90
pages 431-441

EXPERIMENTAL SIMULATION OF THERMO-MECHANICAL ABLATION OF CARBON/PHENOLIC COMPOSITE UNDER THE IMPACT OF LIQUID ALUMINA PARTICLES

Sebastien Bansard
SPCTS, University of Limoges, 123, Av Albert Thomas, 87060 Limoges, France
S. Plouvier
Laboratoire Sciences des Procedes Ceramiques et de Traitements de Surface, University of Limoges, Limoges, France
Michel Vardelle
LMCTS-URA 320, University of Limoges, 123 Avenue Albert Thomas -87060 Limoges Cedex - France
Pierre Fauchais
Laboratoire Sciences des Procedes Ceramiques et de Traitements de Surface UMR CNRS 6638 University of Limoges 123 avenue Albert Thomas, 87060 LIMOGES - France
J. M. Deoclezian
SNECMA Propulsion, Le Haillan, France

要約

In the Ariane V rocket, the propulsion at take-off is provided by aluminum-enriched propergol. The combustion of the propergol results in the formation of alumina droplets that form a liquid film on the nozzle wall. The liquid material reacts with the substrate giving rise to a degradation of the nozzle.
The design of the proper geometry of the nozzle requires a good knowledge of the recession behavior of the base material and heat transfer process. To validate the aerothermochimical model developed by SNECMA, an experimental simulation of the harsh conditions undergone by the nozzle material has been developed.
This work deals with the characterization and the quantification of recession behavior of an ablative composite material under both alumina and plasma jets. This paper presents the experimental setup which combines two direct current plasma torches that are used both to fuse and accelerate alumina particles. The behavior of the droplets before impact (velocity and temperature) and the plasma fields close to the target are examined. A thermal characterization of the composite is made by means of pyrometers, thermocouples and calorimetric measurements.
The recession measurement is obtained through an imaging technique and a feedback control of the position of top of the sample tested.


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