Gas turbine engine with heat recovery system

• Main Authors: SIMONETTI MICHAEL, VITT PAUL HADLEY, SHARMA ASHISH
• Format: Patent
• Language: Chinese; English
• Published: 30.09.2022
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER; DYNAMO-ELECTRIC MACHINES; ELECTRICITY; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; GENERATION; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

The gas turbine engine includes a fan located forward of the gas turbine engine, a compressor section and a turbine section arranged in series flow order. The compressor section and the turbine section together define a core airflow path. The rotating member is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. The outlet guide vane assembly includes a plurality of outlet guide vanes in the exhaust airflow path downstream of the turbine section. The plurality of outlet guide vanes are circumferentially spaced apart from one another over an angular range of about 360 degrees, and each of the plurality of outlet guide vanes defines a radial range. At least one of the plurality of outlet guide vanes includes a cold fluid passage extending at least partially radially therethrough, through which a fluid coolant flows, and another one of the plurality of guide vanes includes a heated fluid passage extending at least partially radially therethrough, through whi