Gas turbine engine rotor disc with cooling fluid passage
US5888049A · kind A · utility
9Cited by
6References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 9, 1997 |
| Grant date | Mar 30, 1999 |
| Priority date | — |
| Expiry date | Jun 9, 2017 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine rotor disc (20) is provided with a plurality of cooling air supply passages (32) which are generally radially extending but are inclined in the downstream direction. Each passage (32) has a cross-sectional configuration which renders the ends (34) of the passages (32) less likely than normal to act as the site of hoop-stress induced cracks.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.