Bleed flow assembly for a gas turbine engine

• Main Authors: Marrinan, Patrick Michael, Miller, Brandon Wayne, Hunter, Scott David, Schimmels, Scott Alan
• Format: Patent
• Language: English
• Published: 15.10.2024
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; AIRCRAFT; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; COSMONAUTICS; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; JET-PROPULSION PLANTS; LIGHTING; MECHANICAL ENGINEERING; PARACHUTES; PERFORMING OPERATIONS; TRANSPORTING; WEAPONS

A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.