GEARED GAS TURBINE ENGINE
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United States of America
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Issued Date -
Jan 30, 2025
app pub date -
Feb 6, 2024
filing date -
Feb 6, 2024
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Abstract
Gas turbine engine for aircraft includes: an engine core including a turbine, compressor, and core shaft connecting the turbine to the compressor; a fan located upstream of the core; a gearbox; and a gearbox support arranged to at least partially support the gearbox. The fan has a mass in a range of 150 kg to 1200 kg. A moment of inertia of the fan is greater than or equal to 7.40×107 kgmm2. A radial bending stiffness to moment of inertia ratio of:
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