GAS TURBINE ENGINE COOLING SYSTEM, CORRESPONDING GAS TURBINE ENGINE AND METHOD OF COOLING

A gas turbine engine cooling system (400,500,600) includes a gas turbine engine (100). The gas turbine engine includes a core engine (102), a cold sink (602,202,316,302,702), a core undercowl space (131), and a core cowl (130) at least partially surrounding the core engine and defining a radially ou...

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Bibliographische Detailangaben
Hauptverfasser:	RIAZ, Shahi, ELBIBARY, Mohamed
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR ELECTRICITY ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PRINTED CIRCUITS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine cooling system (400,500,600) includes a gas turbine engine (100). The gas turbine engine includes a core engine (102), a cold sink (602,202,316,302,702), a core undercowl space (131), and a core cowl (130) at least partially surrounding the core engine and defining a radially outer wall of the core undercowl space. The gas turbine engine cooling system includes an undercowl component (402) positioned in the core undercowl space. The gas turbine engine cooling system also includes a heat pipe (414) including a first end (416), a second end (418), and a conduit (420) extending therebetween. The first end is thermally coupled to the undercowl component, and the second end is thermally coupled to the cold sink. The heat pipe facilitates transfer of a quantity of heat from the undercowl component to the cold sink.