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...
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Main Author | |
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Format | Patent |
Language | English French German |
Published |
26.04.2023
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Subjects | |
Online Access | Get full text |
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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). |
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Bibliography: | Application Number: EP20220202508 |