Geared gas turbine engine
US12297779B2 · kind B2 · utility
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15References
20Claims
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Assignee
Inventor
Key dates
| Filing date | Feb 6, 2024 |
| Grant date | May 13, 2025 |
| Priority date | — |
| Expiry date | Feb 6, 2044 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
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: may be greater than or equal to 2.5×10−2 Nkg−1m−1mm−2. A tilt stiffness to moment of inertia ratio of: may be greater than or equal to 4.0×10−4 Nmrad−1kg−1mm−2.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.