GAS TURBINE WITH COMBUSTION CHAMBER MADE OF COMPOSITE MATERIAL

FIELD: aircraft engineering; turbojet or turboprop aircraft engines. ^ SUBSTANCE: proposed annular combustion chamber 10 with walls 12,13 made of composite material with ceramet matrix is installed inside metal housing by means of connecting components 50,60 attached by soldering to chamber. Said co...

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Bibliographische Detailangaben
Hauptverfasser:	OMON KAROLIN, KONET EHRIK, EHRNANDEZ DID'E IPPOLIT, DE SUZA MARIO SEZAR
Format:	Patent
Sprache:	eng ; rus
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	FIELD: aircraft engineering; turbojet or turboprop aircraft engines. ^ SUBSTANCE: proposed annular combustion chamber 10 with walls 12,13 made of composite material with ceramet matrix is installed inside metal housing by means of connecting components 50,60 attached by soldering to chamber. Said connecting components contain inner connecting plates 50 and outer connecting plates 60 which connect combustion chamber 10, accordingly, with inner metal envelope 30 and outer metal envelope 40 of housing. Each connecting plates has first section 52,62 soldered to outer surface of wall 12,13 of combustion chamber. First sections of connecting plates are separate from each other in circumferential direction so that soldered joint between chamber and connecting components from set limited zones 53,63 separated from each other. ^ EFFECT: improved efficiency of cooling of combustion chamber walls. ^ 9 cl, 6 dwg