Cooling airflow vortex spoiler
US5997244A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 27, 1998 |
| Grant date | Dec 7, 1999 |
| Priority date | — |
| Expiry date | Feb 27, 2018 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D29/321
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine cooling airflow pickup and delivery system which radially inwardly traverses the torque transmittal path of the compressor section at a relatively large radius location, then extends substantially farther inwardly to a significantly smaller radius location, all with minimal static pressure loss to the cooling airflow. Pressurized, substantially non-swirling air from the compressor stage is supplied to a collector, and from the collector thru pickup holes arranged at an angle of 45 degrees reversely to the direction of rotation of the shaft. The pressurized air is then lead into a vortex spoiler which has a plurality of blades smoothly curved reversely to the direction of rotation of the shaft, the radially outer end of each blade being inclined in matching relation to the pickup holes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.