An improved turbofan gas turbine engine

A turbofan gas turbine engine comprising, in axial flow sequence, a heat exchanger Module 110, an inlet duct, a fan assembly 130, a compressor module 140, and a turbine module 150. The fan assembly comprises a plurality of fan blades defining a fan diameter D, and the heat exchanger module comprises...

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Bibliographische Detailangaben
Hauptverfasser:	Thomas Binnington, Daniel Blacker, Natalie Wong, David Jones
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbofan gas turbine engine comprising, in axial flow sequence, a heat exchanger Module 110, an inlet duct, a fan assembly 130, a compressor module 140, and a turbine module 150. The fan assembly comprises a plurality of fan blades defining a fan diameter D, and the heat exchanger module comprises a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into the fan assembly. In use, the first fluid has a maximum temperature of 80⁰C, and the heat exchanger module transfers at least 300kW of heat energy from the first fluid to the airflow. The first fluid may have a maximum operating temperature of 150⁰C, and the heat exchanger module may transfer at least 180kW of heat energy from the first fluid to the airflow A method of operation is also claimed.