STRADDLE MOUNTED LOW PRESSURE COMPRESSOR

A gas turbine engine (20) includes a fan section (22) including a fan (42) with fan blades (43). The fan section (22) drives air along a bypass flow path (B) in a bypass duct (13). A gear reduction (48) is in driving engagement with the fan (42). The gear reduction (48) is a planetary gear system (4...

Full description

Saved in:
Bibliographic Details
Main Author MULDOON, Marc J
Format Patent
LanguageEnglish
French
German
Published 26.04.2023
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary:A gas turbine engine (20) includes a fan section (22) including a fan (42) with fan blades (43). The fan section (22) drives air along a bypass flow path (B) in a bypass duct (13). A gear reduction (48) is in driving engagement with the fan (42). The gear reduction (48) is a planetary gear system (48). A low spool (30) includes a low pressure turbine (46) that drives a low pressure compressor (44) and drives the gear reduction (48) to drive the fan (42) at a speed slower than the low pressure turbine (46). A high spool (32) includes a high pressure turbine (54) that drives a high pressure compressor (52). A first low spool support bearing (38A) is located axially between the low pressure compressor (44) and the gear reduction (48). A second low spool support bearing (38B) is located axially between the low pressure compressor (44) and the high pressure compressor (52).
Bibliography:Application Number: EP20220202508