Radial cooling system for gas turbine engine compressors
US10767485B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 8, 2018 |
| Grant date | Sep 8, 2020 |
| Priority date | — |
| Expiry date | Jun 8, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/213
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.