GAS TURBINE ENGINE

A cooling system for an aircraft comprises a gas turbine engine, an ancillary apparatus, and a heat exchanger. The gas turbine engine comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the tu...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	BRADBROOK, Stephen J, DAVIES, Paul R, NEWMAN, Andrew J, SELLERS, Benjamin J, MARGARY, Gordon
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS PARACHUTES PERFORMING OPERATIONS TRANSPORTING
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