THERMAL INSULATION SYSTEM

A thermal insulation system (90, 190, 290) for an aerospace duct (78) through which high temperature fluid, greater than 500 F, passes. The thermal insulation system (90, 190, 290) can experience pressures less than 80 kilopascals and can be included in a turbine engine (10). The thermal insulation...

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Bibliographische Detailangaben
Hauptverfasser:	NAYAK, Mohandas, TAJIRI, Gordon, CHAKRABORTY, Soumya, GOURISHANKAR, Karthick Vilapakkam, JONNALAGADDA, Dattu Guru Venkata, PHELPS, Emily Marie, GARG, Navish
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JOINTS OR FITTINGS FOR PIPES LIGHTING MEANS FOR THERMAL INSULATION IN GENERAL MECHANICAL ENGINEERING PIPES SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	A thermal insulation system (90, 190, 290) for an aerospace duct (78) through which high temperature fluid, greater than 500 F, passes. The thermal insulation system (90, 190, 290) can experience pressures less than 80 kilopascals and can be included in a turbine engine (10). The thermal insulation system (90, 190, 290) includes at least a first foil layer (94) confronting the duct (78), an insulation layer (96, 196, 296) confronting the first foil layer (94), a second foil layer (98) confronting the insulation layer (96, 196, 296), and at least one coating (100) applied to any one of the layers (94, 96, 98, 296).