Gas turbine engine forward bearing compartment architecture
US10465549B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 9, 2018 |
| Grant date | Nov 5, 2019 |
| Priority date | — |
| Expiry date | Apr 28, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a low pressure compressor, and a high pressure compressor axially aft of the low pressure compressor. A first case structure defines a core flow path for core airflow into the low pressure compressor and has a forward end and an aft end. A second case structure defines a core flow path for core airflow into the high pressure compressor and is mounted to the aft end of the first case structure. A geared architecture is at least partially supported by the first case structure. A first bearing structure is mounted to the first case structure to rotationally support a fan shaft that connects with the geared architecture to drive the fan. A flex support provides a flexible attachment of the geared architecture within the first case structure. A fan drive turbine drives the geared architecture to drive the fan at a speed lower than a speed of the fan drive turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.