Gas turbine engine turbine impeller pressurization
US10072585B2 · kind B2 · utility
6Cited by
6References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 10, 2014 |
| Grant date | Sep 11, 2018 |
| Priority date | — |
| Expiry date | Mar 31, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.