Gas turbine engine forward bearing compartment architecture

A gas turbine engine includes a propulsor section, a compressor section including a first compressor, a front center body case structure that defines a first core flow path for core airflow into the first compressor, an intermediate case structure, a geared architecture, a propulsor shaft, a first b...

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Bibliographische Detailangaben
Hauptverfasser:	Munsell, Peter M, Stripinis, Philip S
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 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine includes a propulsor section, a compressor section including a first compressor, a front center body case structure that defines a first core flow path for core airflow into the first compressor, an intermediate case structure, a geared architecture, a propulsor shaft, a first bearing structure mounted to the front center body case structure, a bearing compartment passage structure in communication with the first bearing structure through the front center body case structure, and a turbine section.