Gas turbine engine with an air cooled bearing
US7997057B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 19, 2009 |
| Grant date | Aug 16, 2011 |
| Priority date | — |
| Expiry date | Jan 16, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S384/90
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A small gas turbine engine where the compressor and turbine are supported on a rotary shaft, and a main bearing is supported on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is used to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.