Gas turbine engine fan stage with bearing cooling

An aero gas turbine engine with a fan stage and a bearing rotatably supporting the fan stage, where the bearing is cooled by passing cooling air through the bearing, and the spent bearing cooling air is re-injected into the air flow path at a location where the effect is minimalized. The location is...

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Bibliographic Details
Main Authors Peterson, Ross H, Ress, Jr., Robert A, Orosa, John A
Format Patent
LanguageEnglish
Published 14.01.2020
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BEARINGS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
ELEMENTS OR CRANKSHAFT MECHANISMS
ENGINEERING ELEMENTS AND UNITS
FLEXIBLE SHAFTS
GAS-TURBINE PLANTS
GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
ROTARY BODIES OTHER THAN GEARING ELEMENTS
SHAFTS
THERMAL INSULATION IN GENERAL
WEAPONS
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Summary:An aero gas turbine engine with a fan stage and a bearing rotatably supporting the fan stage, where the bearing is cooled by passing cooling air through the bearing, and the spent bearing cooling air is re-injected into the air flow path at a location where the effect is minimalized. The location is just downstream from a leading edge of a stator vane and along a pressure side surface of the vane. A fine mist of oil can be discharged into the bearing cooling air to also lubricate the bearing, where both the oil and the spent cooling air is reintroduced into the air flow path.
Bibliography:Application Number: US201815967684