METHOD FOR MANUFACTURING COMBUSTOR OF ROCKET ENGINE, COMBUSTOR OF ROCKET ENGINE, AND ROCKET ENGINE

In the present invention, a method for manufacturing a combustor of a rocket engine comprises: a step for preparing a combustor inner tube (20) having a cooling groove (24); a step for providing an outer layer (30) on an outer circumferential surface of the combustor inner tube (20) so as to cover t...

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Bibliographische Detailangaben
Hauptverfasser:	TAKAHASHI TAKAYUKI, KAJIMA KAZUHIRO, TSUZUKI TAMAKI
Format:	Patent
Sprache:	eng ; fre ; jpn
Schlagworte:	APPARATUS THEREFOR BLASTING CASTING CHEMICAL SURFACE TREATMENT CHEMISTRY COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY IONIMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL COMBUSTION ENGINES DIFFUSION TREATMENT OF METALLIC MATERIAL ELECTROFORMING ELECTROLYTIC OR ELECTROPHORETIC PROCESSES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL JET-PROPULSION PLANTS LIGHTING MAKING METALLIC POWDER MANUFACTURE OF ARTICLES FROM METALLIC POWDER MECHANICAL ENGINEERING METALLURGY PERFORMING OPERATIONS POWDER METALLURGY PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTIONOF COATINGS SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION TRANSPORTING WEAPONS WORKING METALLIC POWDER
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Beschreibung
Zusammenfassung:	In the present invention, a method for manufacturing a combustor of a rocket engine comprises: a step for preparing a combustor inner tube (20) having a cooling groove (24); a step for providing an outer layer (30) on an outer circumferential surface of the combustor inner tube (20) so as to cover the cooling groove (24); and a step for layering an LMD layer (50) by LMD processing on an outer circumferential surface of the outer layer (30). La présente invention concerne un procédé de fabrication d'une chambre de combustion d'un moteur de fusée comprenant : une étape consistant à préparer un tube interne (20) de chambre de combustion possédant une rainure de refroidissement (24) ; une étape consistant à fournir une couche externe (30) sur une surface circonférentielle externe du tube interne (20) de chambre de combustion de manière à recouvrir la rainure de refroidissement (24) ; et une étape consistant à déposer une couche (50) de dépôt de métal au laser (LMD) par un procédé de dépôt de métal au laser (LMD) sur le surface circonférentielle externe de la couche externe (30). 　ロケットエンジンの燃焼器の製造方法は、冷却用の溝（２４）を有する燃焼器内筒（２０）を準備する工程と、冷却用の溝（２４）を覆うように、燃焼器内筒（２０）の外周面上に外層（３０）を設ける工程と、外層（３０）の外周面上に、ＬＭＤ処理によって、ＬＭＤ層（５０）を積層する工程とを具備する。