GAS TURBINE ENGINE

A gas turbine engine is provided defining a radial direction (R). The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath (42). The gas turbine engine also includes a sump positioned inward...

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Bibliographische Detailangaben
Hauptverfasser:	MILLER, Brandon Wayne, SNOW, Kyle Robert, FRANER, Matthew Timothy
Format:	Patent
Sprache:	eng ; fre ; ger
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 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 gas turbine engine is provided defining a radial direction (R). The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath (42). The gas turbine engine also includes a sump positioned inward of the core air flowpath (42) along the radial direction (R). An air pump (124) is positioned inward of the core air flowpath (42) along the radial direction (R) for providing a flow of air from the sump to lower an internal pressure of the sump and reduce a likelihood of lubrication leaking from the sump.